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The full velocity profiles have been measured at a number of stations on both the suction and pressure surfaces, at conditions representative of engine operation, using a Pilot traverse technique and a large-scale (300 mm chord) linear cascade. This information has made it possible to follow the development of the boundary layers, initially laminar, through a region of natural transition to a fully developed turbulent layer. Comparisons with other, less detailed, measurements on the same profile using Pilot traverse and surface-mounted thin films confirm the essential features of the boundary layers.\u003C\u002Fjats:p>",{"EN":102},"Detailed Boundary Layer Measurements on a Transonic Turbine Cascade",{"VOID":104},"[\"15048699066907686753\"]",{"VOID":106},"10.1115\u002F1.2927980","PUBLICATION","VERIFIED","2024-10-04T20:46:26.142+00:00","Auto Verify",[112],"EN","https:\u002F\u002Fasmedigitalcollection.asme.org\u002Fturbomachinery\u002Farticle\u002F114\u002F1\u002F163\u002F420014\u002FDetailed-Boundary-Layer-Measurements-on-a",[115,136,154],{"id":116,"sortIndex":25,"researcher":24,"roles":117,"affiliations":118,"properties":127,"displayName":131,"givenName":24,"familyName":24},"d32a6792-d1b5-4011-adc6-8228c0f11fe9",[],[119],{"id":120,"sortIndex":25,"affiliation":121,"properties":24},"093b46a0-add8-46a5-8126-936f2151d43a",{"id":120,"createTime":24,"updateTime":24,"relativeEntities":122,"slug":24,"properties":123,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":126,"statistic":24},[],{"title":124},{"VI":125},"Department of Engineering Science, University of Oxford, Oxford, United Kingdom",[],{"orcid":128,"title":130,"gsAuthor":132,"openalex":134},{"VOID":129},"https:\u002F\u002Forcid.org\u002F0000-0002-9513-1833",{"EN":131},"D. 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The descriptions and explanations are based on numerical simulations, complemented and corroborated by experiments. It is found that spikes are caused by a separation at the leading edge due to high incidence. The separation gives rise to shedding of vorticity from the leading edge and the consequent formation of vortices that span between the suction surface and the casing. As seen in the rotor frame of reference, near the casing the vortex convects toward the pressure surface of the adjacent blade. The approach of the vortex to the adjacent blade triggers a separation on that blade so the structure propagates. The above sequence of events constitutes a spike. The computed structure of the spike is shown to be consistent with rotor leading edge pressure measurements from the casing of several compressors: the centre of the vortex is responsible for a pressure drop and the partially blocked passages associated with leading edge separations produce a pressure rise. The simulations show leading edge separation and shed vortices over a range of tip clearances including zero. The implication, in accord with recent experimental findings, is that they are not part of the tip clearance vortex. 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Turbomach., 122, 45, 10.1115\u002F1.555426",{"doi":427},"10.1115\u002F1.555426",{"id":24,"text":429,"url":24,"identifiers":430},"2011, An Accelerated 3D Navier–Stokes Solver for Flows in Turbomachines, ASME J. Turbomach., 133, 021025, 10.1115\u002F1.4001192",{"doi":431},"10.1115\u002F1.4001192",{"id":24,"text":433,"url":24,"identifiers":434},"2006, Improving the Performance of a Turbine With Low Aspect Ratio Stators by Aft-Loading, ASME J. Turbomach., 128, 492, 10.1115\u002F1.2182000",{"doi":435},"10.1115\u002F1.2182000",{"id":24,"text":437,"url":24,"identifiers":438},"1977, Core Compressor Exit Stage Study: Vol. 1—Blading Design",{},{"id":24,"text":440,"url":24,"identifiers":441},"1955, Compressor Surge and Stall Propagation, Trans. ASME, 79, 455",{},{"id":24,"text":443,"url":24,"identifiers":444},"1995, On the Identification of a Vortex, J. Fluid Mech., 285, 69, 10.1017\u002FS0022112095000462",{"doi":445},"10.1017\u002FS0022112095000462",{"id":24,"text":447,"url":24,"identifiers":448},"2001, Comparative Studies on Short and Long Length-Scale Stall Cell Propagating in Axial Compressor Rotor, ASME J. Turbomach., 123, 24, 10.1115\u002F1.1326085",{"doi":449},"10.1115\u002F1.1326085",{"id":24,"text":451,"url":24,"identifiers":452},"2002, Short and Long Length-Scale Disturbances Leading to Rotating Stall in an Axial Compressor Stage With Different Stator\u002FRotor Gaps, ASME J. Turbomach., 124, 376, 10.1115\u002F1.1458022",{"doi":453},"10.1115\u002F1.1458022",{"id":24,"text":455,"url":24,"identifiers":456},"2004, Effect of Tip Clearance on Stall Evolution Process in a Low-Speed Axial Compressor Stage, ASME",{},{"id":24,"text":458,"url":24,"identifiers":459},"2013, An Explanation for Flow Features of Spike-Type Stall Inception in an Axial Compressor Rotor, ASME J. Turbomach., 135, 021023, 10.1115\u002F1.4007570",{"doi":460},"10.1115\u002F1.4007570",{"id":24,"text":462,"url":24,"identifiers":463},"2001, Rotating Instabilities in an Axial Compressor Originating From the Fluctuating Blade Tip Vortex, ASME J. Turbomach., 123, 453, 10.1115\u002F1.1370160",{"doi":464},"10.1115\u002F1.1370160",{"id":24,"text":466,"url":24,"identifiers":467},"2002, An Experimental and Numerical Investigation Into the Mechanisms of Rotating Instability, ASME J. Turbomach., 124, 375, 10.1115\u002F1.1460917",{"doi":468},"10.1115\u002F1.1460917",{"id":24,"text":470,"url":24,"identifiers":471},"2012, Stall Warning by Blade Pressure Signature Analysis, ASME J. Turbomach.",{},{"id":24,"text":473,"url":24,"identifiers":474},"2006, The Importance of Shroud Leakage Modeling in Multistage Turbine Flow Calculations, ASME J. Turbomach., 128, 699, 10.1115\u002F1.2181999",{"doi":475},"10.1115\u002F1.2181999",{"id":24,"text":477,"url":24,"identifiers":478},"2005, On the Use of Atmospheric Boundary Conditions for Axial-Flow Compressor Stall Simulations, ASME J. Turbomach., 127, 349, 10.1115\u002F1.1861912",{"doi":479},"10.1115\u002F1.1861912",{"id":481,"createTime":482,"updateTime":482,"relativeEntities":483,"slug":484,"properties":485,"entityType":107,"verifyStatus":108,"verifyTime":482,"verifyNote":110,"languages":496,"translateLanguages":24,"viewCount":25,"primaryUrl":497,"fullTextUrl":24,"authors":498,"publicationType":172,"publisherRelationship":535,"citationCount":387,"citationInfo":578,"publishDate":583,"publishYear":579,"citationAnalyzeStatus":23,"lastCitationAnalyze":24,"indexDatabases":584,"openAccess":24,"references":585,"isForceReanalyzing":227},"e2f6d0b4-9429-4e7e-b88a-b5a67dcd5ae8","2025-02-06T17:51:08.965+00:00",[],"Stall-and-Recovery-Process-of-a-Transonic-Fan-With-and-Without-Inlet-Distortion",{"openalex":486,"mag":488,"abstract":490,"title":492,"doi":494},{"VOID":487},"W2990338465",{"VOID":489},"2990338465",{"EN":491},"\u003Cjats:title>Abstract\u003C\u002Fjats:title>\n               \u003Cjats:p>The aim of this research is to study the stall and recovery behavior of a transonic fan stage with and without inlet distortion. For this purpose, simulations of the stall and recovery process of NASA stage 67 are performed with clean and distorted inflow conditions. The rotor is pushed into stall by closing the exit nozzle. It is shown that in both cases, stall is initiated via spike but the subsequent development of the stall differs. In the stable rotating stall, both cases contain one stall cell traveling at 63% shaft speed. During the recovery process, when the exit nozzle is gradually opened, the size of this stall cell reduces as the corrected mass flow increases. Although the fan stalls at a larger mass flow with inlet distortion, it recovers to a similar corrected mass flow as the case with clean inflow, which indicates that inlet distortion has minor effects on the recovery process for this blade. In spite of the lack of data, detailed analysis based on past experience and physical reasoning is used to demonstrate the validity on numerical simulations. The author appreciates that a validated computational fluid dynamics (CFD) study can provide instructive results to other researchers.\u003C\u002Fjats:p>",{"EN":493},"Stall and Recovery Process of a Transonic Fan With and Without Inlet Distortion",{"VOID":495},"10.1115\u002F1.4045552",[112],"https:\u002F\u002Fasmedigitalcollection.asme.org\u002Fturbomachinery\u002Farticle\u002Fdoi\u002F10.1115\u002F1.4045552\u002F1070438\u002FStall-and-Recovery-Process-of-a-Transonic-Fan-With",[499,518],{"id":500,"sortIndex":25,"researcher":24,"roles":501,"affiliations":502,"properties":511,"displayName":515,"givenName":24,"familyName":24},"7fb59eb0-3c14-40d9-96ee-c63cce10822c",[],[503],{"id":504,"sortIndex":25,"affiliation":505,"properties":24},"98d59648-ff93-4e3f-b3f4-139aff263e9c",{"id":504,"createTime":24,"updateTime":24,"relativeEntities":506,"slug":24,"properties":507,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":510,"statistic":24},[],{"title":508},{"VI":509},"Department of Mechanical Engineering, Imperial College London, London, UK",[],{"orcid":512,"title":514,"openalex":516},{"VOID":513},"https:\u002F\u002Forcid.org\u002F0000-0001-9988-806X",{"EN":515},"Wenqiang Zhang",{"VOID":517},"A5100669250",{"id":519,"sortIndex":138,"researcher":24,"roles":520,"affiliations":521,"properties":528,"displayName":532,"givenName":24,"familyName":24},"c805bad7-f74a-4979-b609-82d74d525f98",[],[522],{"id":504,"sortIndex":25,"affiliation":523,"properties":24},{"id":504,"createTime":24,"updateTime":24,"relativeEntities":524,"slug":24,"properties":525,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":527,"statistic":24},[],{"title":526},{"VI":509},[],{"orcid":529,"title":531,"openalex":533},{"VOID":530},"https:\u002F\u002Forcid.org\u002F0000-0002-7513-1625",{"EN":532},"Mehdi Vahdati",{"VOID":534},"A5057390502",{"url":24,"publisher":536,"properties":574},{"id":6,"createTime":7,"updateTime":8,"relativeEntities":537,"slug":10,"properties":538,"entityType":22,"verifyStatus":23,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":25,"subjectFields":543,"manageAffiliations":548,"indexDatabases":559,"url":83,"thumbnailPath":24,"statistic":24,"gsStatistic":24,"type":24,"analyzePriority":24},[],{"country":539,"eissn":540,"issn":541,"title":542},{"VOID":13},{"VOID":15},{"VOID":17},{"EN":19},[544],{"id":28,"createTime":24,"updateTime":24,"relativeEntities":545,"label":546,"description":547,"parentId":24,"standard":24,"scholarHubFieldId":24},[],{"EN":31},{},[549,554],{"id":35,"createTime":24,"updateTime":24,"relativeEntities":550,"slug":24,"properties":551,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":553,"statistic":24},[],{"title":552},{"EN":39},[],{"id":42,"createTime":24,"updateTime":24,"relativeEntities":555,"slug":24,"properties":556,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":558,"statistic":24},[],{"title":557},{"EN":46},[],[560,567],{"id":50,"indexDatabase":561,"url":63,"indexYears":24,"academicFieldIds":566,"indexDatabaseRanking":24},{"id":52,"createTime":24,"updateTime":24,"relativeEntities":562,"label":563,"description":564,"key":59,"publicationTags":565,"standard":24},[],{"EN":55,"VI":55},{"EN":57,"VI":58},[61,62],[65],{"id":67,"indexDatabase":568,"url":78,"indexYears":79,"academicFieldIds":573,"indexDatabaseRanking":82},{"id":69,"createTime":24,"updateTime":24,"relativeEntities":569,"label":570,"description":571,"key":75,"publicationTags":572,"standard":24},[],{"EN":72,"VI":72},{"EN":72,"VI":74},[77],[81],{"issue":575,"volume":576},{"VOID":214},{"VOID":577},"142",{"total":387,"publishYear":579,"statisticByYear":580},2020,{"2019":138,"2020":156,"2021":581,"2022":582,"2023":138,"2024":581},5,7,"2020-01-01",[61,82],[586,590,594,598,602,606,610,614,618,621,624,628,632,636,640,643,647,651,655,659,663,667,671],{"id":24,"text":587,"url":24,"identifiers":588},"Day, 2016, Stall, Surge, and 75 Years of Research, ASME J. Turbomach., 138, 011001, 10.1115\u002F1.4031473",{"doi":589},"10.1115\u002F1.4031473",{"id":24,"text":591,"url":24,"identifiers":592},"Day, 1978, The Measurement and Interpretation of Flow Within Rotating Stall Cells in Axial Compressors, J. Mech. Eng. Sci., 20, 101, 10.1243\u002FJMES_JOUR_1978_020_017_02",{"doi":593},"10.1243\u002FJMES_JOUR_1978_020_017_02",{"id":24,"text":595,"url":24,"identifiers":596},"Small, C. J., and Lewis, J. T., 1985, “High Speed Compressor Rig as a Stall Recovery Research Tool”, AIAA-85-1428.",{"doi":597},"10.2514\u002F6.1985-1428",{"id":24,"text":599,"url":24,"identifiers":600},"Copenhaver, 1993, Rotating Stall Performance and Recoverability of a High-Speed, Ten-Stage Axial Flow Compressor, J. Propul. Power, 9, 281, 10.2514\u002F3.23620",{"doi":601},"10.2514\u002F3.23620",{"id":24,"text":603,"url":24,"identifiers":604},"Anderson, 2006, Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines, 293, 10.1007\u002F1-4020-4605-7_22",{"doi":605},"10.1007\u002F1-4020-4605-7_22",{"id":24,"text":607,"url":24,"identifiers":608},"Choi, 2011, Recovery Process From Rotating Stall in a Fan, J. Propul. Power, 27, 1161, 10.2514\u002F1.46847",{"doi":609},"10.2514\u002F1.46847",{"id":24,"text":611,"url":24,"identifiers":612},"Lee, 2018, Validation of a Numerical Model for Predicting Stalled Flows in a Low-Speed Fan—Part II: Unsteady Analysis, ASME J. Turbomach., 140, 051009, 10.1115\u002F1.4039052",{"doi":613},"10.1115\u002F1.4039052",{"id":24,"text":615,"url":24,"identifiers":616},"Lee, 2019, Effects of Inlet Disturbances on Fan Stability, ASME J. Eng. Gas Turbines Power, 141, 051014, 10.1115\u002F1.4042204",{"doi":617},"10.1115\u002F1.4042204",{"id":24,"text":619,"url":24,"identifiers":620},"Strazisar, A., Wood, J. R., Hathaway, M. D., and Suder, K. L., 1989, “Laser Anemometer Measurements in a Transonic Axial-Flow Fan Rotor,” NASA Report No. TP 2879.",{},{"id":24,"text":622,"url":24,"identifiers":623},"Zhang, 2017, Influence of the Inlet Distortion on Fan Stall Margin at Different Rotational Speed",{},{"id":24,"text":625,"url":24,"identifiers":626},"Stapelfeldt, 2015, Validation of Time-Domain Single-Passage Methods for the Unsteady Simulation of a Contra-Rotating Open Rotor, Proc. Inst. Mech. Eng. Part A J. Power Energy, 229, 443, 10.1177\u002F0957650915596279",{"doi":627},"10.1177\u002F0957650915596279",{"id":24,"text":629,"url":24,"identifiers":630},"Dodds, 2015, Rotating Stall Observations in a High Speed Compressor—Part II: Numerical Study, ASME J. Turbomach., 137, 051003, 10.1115\u002F1.4028558",{"doi":631},"10.1115\u002F1.4028558",{"id":24,"text":633,"url":24,"identifiers":634},"Zhao, 2018, Poststall Behavior of a Multistage High Speed Compressor at Off-Design Conditions, ASME J. Turbomach., 140, 121002, 10.1115\u002F1.4041142",{"doi":635},"10.1115\u002F1.4041142",{"id":24,"text":637,"url":24,"identifiers":638},"Sayma, 2000, Modeling of Three-Dimensional Viscous Compressible Turbomachinery Flows Using Unstructured Hybrid Grids, AIAA J., 38, 945, 10.2514\u002F2.1062",{"doi":639},"10.2514\u002F2.1062",{"id":24,"text":641,"url":24,"identifiers":642},"Vahdati, 2005, On the Use of Atmospheric Boundary Conditions for Axial-Flow Compressor Stall Simulations, ASME J. Turbomach., 127, 349, 10.1115\u002F1.1861912",{"doi":479},{"id":24,"text":644,"url":24,"identifiers":645},"Choi, 2011, Effects of Fan Speed on Rotating Stall Inception and Recovery, ASME J. Turbomach., 133, 041013, 10.1115\u002F1.4003243",{"doi":646},"10.1115\u002F1.4003243",{"id":24,"text":648,"url":24,"identifiers":649},"Zhang, 2018, A Parametric Study of the Effects of Inlet Distortion on Fan Aerodynamic Stability, ASME J. Turbomach., 141, 011011, 10.1115\u002F1.4041376",{"doi":650},"10.1115\u002F1.4041376",{"id":24,"text":652,"url":24,"identifiers":653},"Jahnen, 1999, Stall Inception in a 5-Stage HP-Compressor With Increased Load Due to Inlet Distortions, 10.1115\u002F99-GT-440",{"doi":654},"10.1115\u002F99-GT-440",{"id":24,"text":656,"url":24,"identifiers":657},"Perovic, 2015, Stall Inception in a Boundary Layer Ingesting Fan, 10.1115\u002FGT2015-43025",{"doi":658},"10.1115\u002FGT2015-43025",{"id":24,"text":660,"url":24,"identifiers":661},"He, 1997, Computational Study of Rotating-Stall Inception in Axial Compressors, J. Propul. Power, 13, 31, 10.2514\u002F2.5147",{"doi":662},"10.2514\u002F2.5147",{"id":24,"text":664,"url":24,"identifiers":665},"Day, 1999, Stall Inception and the Prospects for Active Control in Four High Speed Compressors, ASME J. Turbomach., 121, 18, 10.1115\u002F1.2841229",{"doi":666},"10.1115\u002F1.2841229",{"id":24,"text":668,"url":24,"identifiers":669},"Mazzawy, 1977, Multiple Segment Parallel Compressor Model for Circumferential Flow Distortion, ASME J. Eng. Power, 99, 288, 10.1115\u002F1.3446288",{"doi":670},"10.1115\u002F1.3446288",{"id":24,"text":672,"url":24,"identifiers":673},"Greitzer, 1976, Surge and Rotating Stall in Axial Flow Compressors—Part I: Theoretical Compression System Model, ASME J. Eng. Power, 98, 190, 10.1115\u002F1.3446138",{"doi":674},"10.1115\u002F1.3446138",{"id":676,"createTime":677,"updateTime":677,"relativeEntities":678,"slug":679,"properties":680,"entityType":107,"verifyStatus":108,"verifyTime":691,"verifyNote":110,"languages":692,"translateLanguages":24,"viewCount":25,"primaryUrl":693,"fullTextUrl":24,"authors":694,"publicationType":172,"publisherRelationship":755,"citationCount":799,"citationInfo":800,"publishDate":807,"publishYear":801,"citationAnalyzeStatus":23,"lastCitationAnalyze":24,"indexDatabases":808,"openAccess":24,"references":809,"isForceReanalyzing":227},"87a10917-2c42-463e-90ee-7e133d05d5d8","2025-02-06T17:51:06.817+00:00",[],"Validation-of-Numerical-Simulation-for-Rotating-Stall-in-a-Transonic-Fan",{"openalex":681,"mag":683,"abstract":685,"title":687,"doi":689},{"VOID":682},"W2145124592",{"VOID":684},"2145124592",{"EN":686},"\u003Cjats:p>This paper addresses a comparison of numerical stall simulations with experimental data at 60% (subsonic) and 95% (supersonic) of the design speed in a modern transonic fan rig. The unsteady static pressures were obtained with high frequency Kulite transducers mounted on the casing upstream and downstream of the fan. The casing pressure variation was clearly visible in the measurements when a stall cell passed below the transducers. Numerical stall simulations were conducted using an implicit, time-accurate, 3D compressible Reynolds-averaged Navier-Stokes (RANS) solver. The comparisons between the experiment and simulation mainly cover performance curves and time-domain pressure traces of Kulites during rotating stall. At two different fan speeds, the stall characteristics such as the number and rotating speed of the stall cells were well-matched to the experimental values. The mass flow rate and the loading parameter under the fully-developed rotating stall also showed good agreement with the experiment. In both the numerical and experimental results, a large stall cell was eventually formed after stall inception regardless of the fan speed. Based on the validation, the detailed flow has been evaluated to understand rotating stall in a transonic fan. In addition, it was found that the mass flow measurement using casing static pressure might be wrong during transient flow if the Kulites were mounted too close to the fan blade.\u003C\u002Fjats:p>",{"EN":688},"Validation of Numerical Simulation for Rotating Stall in a Transonic Fan",{"VOID":690},"10.1115\u002F1.4006641","2025-02-06T17:51:06.816+00:00",[112],"https:\u002F\u002Fasmedigitalcollection.asme.org\u002Fturbomachinery\u002Farticle\u002Fdoi\u002F10.1115\u002F1.4006641\u002F378523\u002FValidation-of-Numerical-Simulation-for-Rotating",[695,722,739],{"id":696,"sortIndex":25,"researcher":24,"roles":697,"affiliations":698,"properties":715,"displayName":719,"givenName":24,"familyName":24},"10905aae-944c-46bf-bfd4-46c399fc71d8",[],[699,707],{"id":700,"sortIndex":25,"affiliation":701,"properties":24},"3259febd-335c-4b8f-80a9-8f1dc6434aa1",{"id":700,"createTime":24,"updateTime":24,"relativeEntities":702,"slug":24,"properties":703,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":706,"statistic":24},[],{"title":704},{"EN":705},"#N#Imperial College London, London, UK",[],{"id":708,"sortIndex":138,"affiliation":709,"properties":24},"e6ffff3f-2ef9-4fe0-ad8a-3afe5e50145d",{"id":708,"createTime":24,"updateTime":24,"relativeEntities":710,"slug":24,"properties":711,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":714,"statistic":24},[],{"title":712},{"EN":713},"Assistant Professor Department of Mechanical Engineering, Myongji University, Yongin 449-728, South Korea e-mail:",[],{"orcid":716,"title":718,"openalex":720},{"VOID":717},"https:\u002F\u002Forcid.org\u002F0000-0002-0192-4534",{"EN":719},"Minsuk Choi",{"VOID":721},"A5052081041",{"id":723,"sortIndex":138,"researcher":24,"roles":724,"affiliations":725,"properties":734,"displayName":736,"givenName":24,"familyName":24},"eba332c6-77c5-4ed7-a1bf-d30652503f49",[],[726],{"id":727,"sortIndex":25,"affiliation":728,"properties":24},"c7247da0-a36a-4a6e-b382-83683cd7965b",{"id":727,"createTime":24,"updateTime":24,"relativeEntities":729,"slug":24,"properties":730,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":733,"statistic":24},[],{"title":731},{"EN":732},"Engineering Specialist Aerodynamics, Rolls-Royce plc, Derby DE24 8BJ, UK e-mail:",[],{"title":735,"openalex":737},{"EN":736},"Nigel Smith",{"VOID":738},"A5034687010",{"id":740,"sortIndex":156,"researcher":24,"roles":741,"affiliations":742,"properties":751,"displayName":532,"givenName":24,"familyName":24},"2667d6c1-7032-4a59-be4e-90a8c83fdb18",[],[743],{"id":744,"sortIndex":25,"affiliation":745,"properties":24},"b49d8808-90ec-4e04-b0a9-c3fbf085dfe5",{"id":744,"createTime":24,"updateTime":24,"relativeEntities":746,"slug":24,"properties":747,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":750,"statistic":24},[],{"title":748},{"EN":749},"Principal Research Fellow Department of Mechanical Engineering, Imperial College London, London SW7 2BX, UK e-mail:",[],{"orcid":752,"title":753,"openalex":754},{"VOID":530},{"EN":532},{"VOID":534},{"url":24,"publisher":756,"properties":794},{"id":6,"createTime":7,"updateTime":8,"relativeEntities":757,"slug":10,"properties":758,"entityType":22,"verifyStatus":23,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":25,"subjectFields":763,"manageAffiliations":768,"indexDatabases":779,"url":83,"thumbnailPath":24,"statistic":24,"gsStatistic":24,"type":24,"analyzePriority":24},[],{"country":759,"eissn":760,"issn":761,"title":762},{"VOID":13},{"VOID":15},{"VOID":17},{"EN":19},[764],{"id":28,"createTime":24,"updateTime":24,"relativeEntities":765,"label":766,"description":767,"parentId":24,"standard":24,"scholarHubFieldId":24},[],{"EN":31},{},[769,774],{"id":35,"createTime":24,"updateTime":24,"relativeEntities":770,"slug":24,"properties":771,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":773,"statistic":24},[],{"title":772},{"EN":39},[],{"id":42,"createTime":24,"updateTime":24,"relativeEntities":775,"slug":24,"properties":776,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":778,"statistic":24},[],{"title":777},{"EN":46},[],[780,787],{"id":50,"indexDatabase":781,"url":63,"indexYears":24,"academicFieldIds":786,"indexDatabaseRanking":24},{"id":52,"createTime":24,"updateTime":24,"relativeEntities":782,"label":783,"description":784,"key":59,"publicationTags":785,"standard":24},[],{"EN":55,"VI":55},{"EN":57,"VI":58},[61,62],[65],{"id":67,"indexDatabase":788,"url":78,"indexYears":79,"academicFieldIds":793,"indexDatabaseRanking":82},{"id":69,"createTime":24,"updateTime":24,"relativeEntities":789,"label":790,"description":791,"key":75,"publicationTags":792,"standard":24},[],{"EN":72,"VI":72},{"EN":72,"VI":74},[77],[81],{"issue":795,"volume":797},{"VOID":796},"2",{"VOID":798},"135",67,{"total":799,"publishYear":801,"statisticByYear":802},2013,{"2013":138,"2014":803,"2015":582,"2016":804,"2018":805,"2019":581,"2020":806,"2021":806,"2022":319,"2023":138,"2024":804},8,6,9,10,"2013-03-01",[61,82],[810,814,818,820,824,827,830,834,838,842,844,848,852,856,860,863,866,869],{"id":24,"text":811,"url":24,"identifiers":812},"1993, Stall Inception in Axial Compressors, ASME J. Turbomach., 115, 1, 10.1115\u002F1.2929209",{"doi":813},"10.1115\u002F1.2929209",{"id":24,"text":815,"url":24,"identifiers":816},"1993, Active Suppression of Rotating Stall and Surge in Axial Compressors, ASME J. Turbomach., 115, 40, 10.1115\u002F1.2929216",{"doi":817},"10.1115\u002F1.2929216",{"id":24,"text":392,"url":24,"identifiers":819},{"doi":394},{"id":24,"text":821,"url":24,"identifiers":822},"1998, Experiments in Active Control of Stall on an Aeroengine Gas Turbine, ASME J. Turbomach., 120, 637, 10.1115\u002F1.2841773",{"doi":823},"10.1115\u002F1.2841773",{"id":24,"text":825,"url":24,"identifiers":826},"1999, Stall Inception and the Prospects for Active Control in Four High-Speed Compressors, ASME J. Turbomach., 121, 18, 10.1115\u002F1.2841229",{"doi":666},{"id":24,"text":828,"url":24,"identifiers":829},"1997, Computational Study of Rotating-Stall Inception in Axial Compressor, J. Propul. Power, 13, 31, 10.2514\u002F2.5147",{"doi":662},{"id":24,"text":831,"url":24,"identifiers":832},"1999, Role of Blade Passage Flow Structures in Axial Compressor Rotating Stall Inception, ASME J. Turbomach., 121, 735, 10.1115\u002F1.2836727",{"doi":833},"10.1115\u002F1.2836727",{"id":24,"text":835,"url":24,"identifiers":836},"2006, Numerical Simulation of Rotating Stall in a Subsonic Compressor, Aerosp. Sci. Technol., 10, 9, 10.1016\u002Fj.ast.2005.07.006",{"doi":837},"10.1016\u002Fj.ast.2005.07.006",{"id":24,"text":839,"url":24,"identifiers":840},"2008, Role of Hub-Corner-Separation on Rotating Stall in an Axial Compressor, Trans. Jpn. Soc. Aeronaut. Space Sci., 51, 93, 10.2322\u002Ftjsass.51.93",{"doi":841},"10.2322\u002Ftjsass.51.93",{"id":24,"text":421,"url":24,"identifiers":843},{"doi":423},{"id":24,"text":845,"url":24,"identifiers":846},"2008, Unsteady Flow and Aeroelasticity Behavior of Aeroengine Core Compressors During Rotating Stall and Surge, ASME J. Turbomach., 130, 031017, 10.1115\u002F1.2777188",{"doi":847},"10.1115\u002F1.2777188",{"id":24,"text":849,"url":24,"identifiers":850},"2008, Prestall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation, ASME J. Turbomach., 130, 041014, 10.1115\u002F1.2812968",{"doi":851},"10.1115\u002F1.2812968",{"id":24,"text":853,"url":24,"identifiers":854},"2010, Simulation of Rotating Stall in a Whole Stage of an Axial Compressor, Comput. Fluids, 39, 1644, 10.1016\u002Fj.compfluid.2010.05.017",{"doi":855},"10.1016\u002Fj.compfluid.2010.05.017",{"id":24,"text":857,"url":24,"identifiers":858},"2011, Numerical Strategies for Capturing Rotating Stall, Proc. Inst. Mech. Eng., Part A, 225, 655, 10.1177\u002F0957650911403869",{"doi":859},"10.1177\u002F0957650911403869",{"id":24,"text":861,"url":24,"identifiers":862},"2011, Effects of Fan Speed on Rotating Stall Inception and Recovery, ASME J. Turbomach., 133, 041013, 10.1115\u002F1.4003243",{"doi":646},{"id":24,"text":864,"url":24,"identifiers":865},"Anderson, S. J. and Smith, N. H. S., 2003, “Analysis of Unsteady Casing Pressure Measurements during Surge and Rotating Stall,” Proceedings of ISUAAAT10, Springer, New York, pp.293–312.",{"doi":605},{"id":24,"text":867,"url":24,"identifiers":868},"2000, Modeling of 3D Viscous Compressible Turbomachinery Flows Using Hybrid Grids, AIAA J., 38, 945, 10.2514\u002F2.1062",{"doi":639},{"id":24,"text":870,"url":24,"identifiers":871},"2005, On the Use of Atmospheric Boundary Conditions for Axial-Flow Compressor Stall Simulations, ASME J. Turbomach., 127, 349",{},{"id":873,"createTime":874,"updateTime":874,"relativeEntities":875,"slug":876,"properties":877,"entityType":107,"verifyStatus":108,"verifyTime":874,"verifyNote":110,"languages":888,"translateLanguages":24,"viewCount":25,"primaryUrl":889,"fullTextUrl":24,"authors":890,"publicationType":172,"publisherRelationship":966,"citationCount":1010,"citationInfo":1011,"publishDate":1016,"publishYear":1012,"citationAnalyzeStatus":23,"lastCitationAnalyze":24,"indexDatabases":1017,"openAccess":24,"references":1018,"isForceReanalyzing":227},"d901f8ac-a73e-4fe1-bf51-8eb307e88ba5","2025-02-06T17:51:05.486+00:00",[],"The-Role-of-Tip-Leakage-Flow-in-Spike-Type-Rotating-Stall-Inception",{"openalex":878,"mag":880,"abstract":882,"title":884,"doi":886},{"VOID":879},"W2903921806",{"VOID":881},"2903921806",{"EN":883},"\u003Cjats:p>This paper describes the role of tip leakage flow in creating the leading edge separation necessary for the onset of spike-type compressor rotating stall. A series of unsteady multipassage simulations, supported by experimental data, are used to define and illustrate the two competing mechanisms that cause the high incidence responsible for this separation: blockage from a casing-suction-surface corner separation and forward spillage of the tip leakage jet. The axial momentum flux in the tip leakage flow determines which mechanism dominates. At zero tip clearance, corner separation blockage dominates. As clearance is increased, the leakage flow reduces blockage, moving the stall flow coefficient to lower flow, i.e., giving a larger unstalled flow range. Increased clearance, however, means increased leakage jet momentum and contribution to leakage jet spillage. There is thus a clearance above which jet spillage dominates in creating incidence, so the stall flow coefficient increases and flow range decreases with clearance. As a consequence, there is a clearance for maximum flow range; for the two rotors in this study, the value was approximately 0.5% chord. The chordwise distribution of the leakage axial momentum is also important in determining stall onset. Shifting the distribution toward the trailing edge increases flow range for a leakage jet dominated geometry and reduces flow range for a corner separation dominated geometry. Guidelines are developed for flow range enhancement through control of tip leakage flow axial momentum magnitude and distribution. An example is given of how this might be achieved.\u003C\u002Fjats:p>",{"EN":885},"The Role of Tip Leakage Flow in Spike-Type Rotating Stall Inception",{"VOID":887},"10.1115\u002F1.4042250",[112],"https:\u002F\u002Fasmedigitalcollection.asme.org\u002Fturbomachinery\u002Farticle\u002Fdoi\u002F10.1115\u002F1.4042250\u002F368654\u002FThe-Role-of-Tip-Leakage-Flow-in-SpikeType-Rotating",[891,908,921,938,953],{"id":892,"sortIndex":25,"researcher":24,"roles":893,"affiliations":894,"properties":903,"displayName":905,"givenName":24,"familyName":24},"cc2545fd-c20a-441f-b762-5229e3e5ee52",[],[895],{"id":896,"sortIndex":25,"affiliation":897,"properties":24},"46397d10-b8e1-4596-98a2-29a17aaaeb67",{"id":896,"createTime":24,"updateTime":24,"relativeEntities":898,"slug":24,"properties":899,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":902,"statistic":24},[],{"title":900},{"EN":901},"Whittle Laboratory, University of Cambridge, 1 JJ Thomson Avenue, Cambridge CB3 0DY, UK e-mail:",[],{"title":904,"openalex":906},{"EN":905},"M. Hewkin-Smith",{"VOID":907},"A5064010364",{"id":909,"sortIndex":138,"researcher":24,"roles":910,"affiliations":911,"properties":918,"displayName":262,"givenName":24,"familyName":24},"7d8b04ac-75cc-4c7a-8be3-617c901a04ae",[],[912],{"id":270,"sortIndex":25,"affiliation":913,"properties":24},{"id":270,"createTime":24,"updateTime":24,"relativeEntities":914,"slug":24,"properties":915,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":917,"statistic":24},[],{"title":916},{"VI":275},[],{"title":919,"openalex":920},{"EN":262},{"VOID":264},{"id":922,"sortIndex":156,"researcher":24,"roles":923,"affiliations":924,"properties":931,"displayName":935,"givenName":24,"familyName":24},"b85c34d3-858a-4f1c-a8e8-dcb7f2f2eebc",[],[925],{"id":270,"sortIndex":25,"affiliation":926,"properties":24},{"id":270,"createTime":24,"updateTime":24,"relativeEntities":927,"slug":24,"properties":928,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":930,"statistic":24},[],{"title":929},{"VI":275},[],{"orcid":932,"title":934,"openalex":936},{"VOID":933},"https:\u002F\u002Forcid.org\u002F0009-0004-0035-7816",{"EN":935},"S. D. Grimshaw",{"VOID":937},"A5090614630",{"id":939,"sortIndex":301,"researcher":24,"roles":940,"affiliations":941,"properties":950,"displayName":314,"givenName":24,"familyName":24},"7449a605-cf54-4785-8206-c35bff729a58",[],[942],{"id":943,"sortIndex":25,"affiliation":944,"properties":24},"83fbc420-15c3-4f42-95da-62ca27f986c0",{"id":943,"createTime":24,"updateTime":24,"relativeEntities":945,"slug":24,"properties":946,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":949,"statistic":24},[],{"title":947},{"EN":948},"Gas Turbine Laboratory, Massachusetts Institute of Technology, 77 Massachusetts Avenue, 41-205 L, Cambridge, MA 02139",[],{"title":951,"openalex":952},{"EN":314},{"VOID":316},{"id":954,"sortIndex":319,"researcher":24,"roles":955,"affiliations":956,"properties":963,"displayName":330,"givenName":24,"familyName":24},"f210e707-1b7d-4ad7-926d-2a72d9c2e0b9",[],[957],{"id":943,"sortIndex":25,"affiliation":958,"properties":24},{"id":943,"createTime":24,"updateTime":24,"relativeEntities":959,"slug":24,"properties":960,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":962,"statistic":24},[],{"title":961},{"EN":948},[],{"title":964,"openalex":965},{"EN":330},{"VOID":332},{"url":24,"publisher":967,"properties":1005},{"id":6,"createTime":7,"updateTime":8,"relativeEntities":968,"slug":10,"properties":969,"entityType":22,"verifyStatus":23,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":25,"subjectFields":974,"manageAffiliations":979,"indexDatabases":990,"url":83,"thumbnailPath":24,"statistic":24,"gsStatistic":24,"type":24,"analyzePriority":24},[],{"country":970,"eissn":971,"issn":972,"title":973},{"VOID":13},{"VOID":15},{"VOID":17},{"EN":19},[975],{"id":28,"createTime":24,"updateTime":24,"relativeEntities":976,"label":977,"description":978,"parentId":24,"standard":24,"scholarHubFieldId":24},[],{"EN":31},{},[980,985],{"id":35,"createTime":24,"updateTime":24,"relativeEntities":981,"slug":24,"properties":982,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":984,"statistic":24},[],{"title":983},{"EN":39},[],{"id":42,"createTime":24,"updateTime":24,"relativeEntities":986,"slug":24,"properties":987,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":989,"statistic":24},[],{"title":988},{"EN":46},[],[991,998],{"id":50,"indexDatabase":992,"url":63,"indexYears":24,"academicFieldIds":997,"indexDatabaseRanking":24},{"id":52,"createTime":24,"updateTime":24,"relativeEntities":993,"label":994,"description":995,"key":59,"publicationTags":996,"standard":24},[],{"EN":55,"VI":55},{"EN":57,"VI":58},[61,62],[65],{"id":67,"indexDatabase":999,"url":78,"indexYears":79,"academicFieldIds":1004,"indexDatabaseRanking":82},{"id":69,"createTime":24,"updateTime":24,"relativeEntities":1000,"label":1001,"description":1002,"key":75,"publicationTags":1003,"standard":24},[],{"EN":72,"VI":72},{"EN":72,"VI":74},[77],[81],{"issue":1006,"volume":1008},{"VOID":1007},"6",{"VOID":1009},"141",98,{"total":1010,"publishYear":1012,"statisticByYear":1013},2019,{"2019":319,"2020":219,"2021":381,"2022":1014,"2023":386,"2024":1015,"2025":138},25,20,"2019-06-01",[61,82],[1019,1021,1024,1027,1030,1032,1035,1038,1042,1046,1050,1054,1058,1062,1065,1069,1072,1075,1079,1082,1085,1087,1091,1095,1099,1101],{"id":24,"text":396,"url":24,"identifiers":1020},{"doi":398},{"id":24,"text":1022,"url":24,"identifiers":1023},"1993, Stall Inception in Axial Flow Compressors, ASME J. Turbomach., 115, 1, 10.1115\u002F1.2929209",{"doi":813},{"id":24,"text":1025,"url":24,"identifiers":1026},"1955, Compressor Surge and Stall Propagation, Trans. ASME, 77, 455",{},{"id":24,"text":1028,"url":24,"identifiers":1029},"2015, Origins and Structure of Spike-Type Rotating Stall, ASME J. Turbomach., 137, 051007, 10.1115\u002F1.4028494",{"doi":243},{"id":24,"text":458,"url":24,"identifiers":1031},{"doi":460},{"id":24,"text":1033,"url":24,"identifiers":1034},"2008, Criteria for Spike Initiated Rotating Stall, ASME J. Turbomach., 130, 10.1115\u002F1.2750674",{"doi":423},{"id":24,"text":1036,"url":24,"identifiers":1037},"2015, Rotating Stall Observations in a High Speed Compressor—Part II: Numerical Study, ASME J. Turbomach., 137, 051003, 10.1115\u002F1.4028558",{"doi":631},{"id":24,"text":1039,"url":24,"identifiers":1040},"1990, Tip Leakage Flow in Axial Compressors, ASME J. Turbomach., 113, 252, 10.1115\u002F1.2929095",{"doi":1041},"10.1115\u002F1.2929095",{"id":24,"text":1043,"url":24,"identifiers":1044},"1993, Loss Mechanisms in Turbomachines, ASME J. Turbomach., 115, 621, 10.1115\u002F1.2929299",{"doi":1045},"10.1115\u002F1.2929299",{"id":24,"text":1047,"url":24,"identifiers":1048},"1999, Endwall Blockage in Axial Compressors, ASME J. Turbomach., 121, 499, 10.1115\u002F1.2841344",{"doi":1049},"10.1115\u002F1.2841344",{"id":24,"text":1051,"url":24,"identifiers":1052},"1987, Three-Dimensional Flows and Loss Reduction in Axial Compressors, ASME J. Turbomach., 109, 354, 10.1115\u002F1.3262113",{"doi":1053},"10.1115\u002F1.3262113",{"id":24,"text":1055,"url":24,"identifiers":1056},"1984, Experimental Study of a High-Throughflow Transonic Axial Compressor Stage, ASME J. Eng. Gas Turbines Power, 106, 552, 10.1115\u002F1.3239606",{"doi":1057},"10.1115\u002F1.3239606",{"id":24,"text":1059,"url":24,"identifiers":1060},"1990, Stall Inception in Axial Compressors, ASME J. Turbomach., 112, 116, 10.1115\u002F1.2927406",{"doi":1061},"10.1115\u002F1.2927406",{"id":24,"text":1063,"url":24,"identifiers":1064},"Wisler, D. C., Beacher, B. F., and Shin, H.-W., 2002, “Effects of Loading and Clearance Variation on Tip Vortex and Endwall Blockage,” Ninth International Symposium in Transport Phenomena and the Dynamics of Rotating Machinery (ISROMAC), Honolulu, HI, Feb. 10–14, Paper No. FD-ABS-004.",{},{"id":24,"text":1066,"url":24,"identifiers":1067},"Zhang, Z., Yu, X., and Liu, B., 2012, “Characteristics of the Tip Leakage Vortex in a Low-Speed Axial Compressor With Different Rotor Tip Gaps,” ASME Paper No. GT2012-69148.10.1115\u002FGT2012-69148",{"doi":1068},"10.1115\u002FGT2012-69148",{"id":24,"text":1070,"url":24,"identifiers":1071},"1989, Compressor Aerodynamics, 343",{},{"id":24,"text":1073,"url":24,"identifiers":1074},"1965, Leakage and Secondary Flows in Compressor Cascades, 3483",{},{"id":24,"text":1076,"url":24,"identifiers":1077},"Gbadebo, S. A., 2003, “Three-Dimensional Separations in Axial Compressors,” Ph.D. thesis, University of Cambridge, Cambridge, UK.",{"doi":1078},"10.1115\u002FGT2004-53617",{"id":24,"text":1080,"url":24,"identifiers":1081},"1977, Core Compressor Exit Stage Study—Volume I: Blade Design",{},{"id":24,"text":1083,"url":24,"identifiers":1084},"Nolan, S. P. R., 2005, “Effect of Radial Transport on Compressor Tip Clearance Flow Structures and Enhancement of Stable Flow Range,” Master's thesis, Massachusetts Institute of Technology, Cambridge, MA.https:\u002F\u002Fpdfs.semanticscholar.org\u002F4e20\u002Fa8d7e5daa3b0918f85579d4623c4d2c29f06.pdf",{},{"id":24,"text":443,"url":24,"identifiers":1086},{"doi":445},{"id":24,"text":1088,"url":24,"identifiers":1089},"1982, Casing Wall Boundary-Layer Development Through an Isolated Compressor Rotor, ASME J. Eng. Power, 104, 805, 10.1115\u002F1.3227347",{"doi":1090},"10.1115\u002F1.3227347",{"id":24,"text":1092,"url":24,"identifiers":1093},"1981, Stalling Pressure Rise Capability of Axial Flow Compressor Stages, ASME J. Eng. Power, 103, 645, 10.1115\u002F1.3230787",{"doi":1094},"10.1115\u002F1.3230787",{"id":24,"text":1096,"url":24,"identifiers":1097},"2002, The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part II: Low and High-Speed Designs and Test Verification, ASME J. Turbomach., 124, 533, 10.1115\u002F1.1507334",{"doi":1098},"10.1115\u002F1.1507334",{"id":24,"text":429,"url":24,"identifiers":1100},{"doi":431},{"id":24,"text":477,"url":24,"identifiers":1102},{"doi":479},{"id":1104,"createTime":1105,"updateTime":1105,"relativeEntities":1106,"slug":1107,"properties":1108,"entityType":107,"verifyStatus":108,"verifyTime":1116,"verifyNote":110,"languages":1117,"translateLanguages":24,"viewCount":25,"primaryUrl":1118,"fullTextUrl":24,"authors":1119,"publicationType":172,"publisherRelationship":1203,"citationCount":1248,"citationInfo":1249,"publishDate":1252,"publishYear":1250,"citationAnalyzeStatus":23,"lastCitationAnalyze":24,"indexDatabases":1253,"openAccess":24,"references":1254,"isForceReanalyzing":227},"f1d9cc60-6c94-4a87-a325-d96133bf3ef5","2025-02-06T17:51:03.794+00:00",[],"Comparative-Studies-on-Short-and-Long-Length-Scale-Stall-Cell-Propagating-in-an-Axial-Compressor-Rotor",{"openalex":1109,"abstract":1111,"title":1113,"doi":1115},{"VOID":1110},"W4234299926",{"EN":1112},"\u003Cjats:p>In a low-speed compressor test rig at Kyushu University, multiple short length-scale stall cells appeared under a mild stall condition and turned into a long length-scale cell under a deep stall condition. Then, for the two types of stall cell, the pressure distribution on the casing wall and the velocity distributions upstream and downstream of the rotor have been measured by high-response pressure transducers and a slanted hot-wire, respectively. The time-dependent ensemble-averages of these distributions have been obtained phase-locked to both the rotor and the stall cell rotation using a “double phase-locked averaging technique” developed by the authors. The structures of the two stall cells are compared: The short length-scale stall cell is characterized by a concentrated vortex spanning from the casing wall ahead of the rotor to the blade suction surface. In the long length-scale stall cell, the separation vortices go upstream irregularly when blade separation develops in the front half of the cell, and re-enter the rotor on the hub side in the rear half of it. The unsteady aerodynamic force and torsional moment acting on the blade tip section have been evaluated from the time-dependent ensemble-averages of the casing wall pressure distribution. The force fluctuation due to the short length-scale cells is somewhat smaller than that for the long length-scale cell. The blade suffers two peaks of the force during a period of the short length-scale cells passing through it. The moment fluctuation for the short length-scale cells is considerably larger than that for the long length-scale cell.\u003C\u002Fjats:p>",{"EN":1114},"Comparative Studies on Short and Long Length-Scale Stall Cell Propagating in an Axial Compressor Rotor",{"VOID":449},"2025-02-06T17:51:03.793+00:00",[112],"https:\u002F\u002Fasmedigitalcollection.asme.org\u002Fturbomachinery\u002Farticle\u002F123\u002F1\u002F24\u002F446161\u002FComparative-Studies-on-Short-and-Long-LengthScale",[1120,1139,1154,1169,1186],{"id":1121,"sortIndex":25,"researcher":24,"roles":1122,"affiliations":1123,"properties":1132,"displayName":1136,"givenName":24,"familyName":24},"d61220dc-7522-4771-bc8d-4b43c00f6255",[],[1124],{"id":1125,"sortIndex":25,"affiliation":1126,"properties":24},"b48c517a-005b-4d2e-936d-ea2eb6a2f22c",{"id":1125,"createTime":24,"updateTime":24,"relativeEntities":1127,"slug":24,"properties":1128,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1131,"statistic":24},[],{"title":1129},{"EN":1130},"Department of Energy and Mechanical Engineering, Kyushu University, Fukuoka, Japan",[],{"orcid":1133,"title":1135,"openalex":1137},{"VOID":1134},"https:\u002F\u002Forcid.org\u002F0000-0002-8190-863X",{"EN":1136},"M. 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A. E., 1985, “Development of Small Rotating Stall in a Single Stage Axial Compressor,” ASME Paper No. 85-GT-227.",{"doi":1258},"10.1115\u002F85-GT-227",{"id":24,"text":1260,"url":24,"identifiers":1261},"Silkowski, P. D., 1995, “Measurement of Rotor Stalling in a Matched and a Mismatched Multistage Compressor,” GTL Report, No. 221, Gas Turbine Laboratory, Massachusetts Institute of Technology.",{},{"id":24,"text":1263,"url":24,"identifiers":1264},"Day, I. J., Breuer, T., Escuret, J., Cherrett, M., and Wilson, A., 1999, “Stall Inception and the Prospects for Active Control in Four High Speed Compressors,” ASME J. Turbomach., 121, pp. 18–27.",{"doi":666},{"id":24,"text":1266,"url":24,"identifiers":1267},"Inoue, M., Kuroumaru, M., Tanino, T., and Furukawa, M., 2000, “Propagation of Multiple Short Length-Scale Stall Cells in an Axial Compressor Rotor,” ASME J. Turbomach., 122, pp. 45–53.",{"doi":427},{"id":24,"text":1269,"url":24,"identifiers":1270},"Day, I. J., and Cumpsty, N. A., 1978, “The Measurement and Interpretation of Flow Within Rotating Stall Cells in Axial Compressors,” J. Mech. Eng. Sci., 20, pp. 101–114.",{"doi":593},{"id":24,"text":1272,"url":24,"identifiers":1273},"Das, D. K., and Jiang, H. K., 1984, “An Experimental Study of Rotating Stall in a Multistage Axial-Flow Compressor,” ASME J. Eng. Gas Turbines Power, 106, pp. 542–551.",{"doi":1274},"10.1115\u002F1.3239605",{"id":24,"text":1276,"url":24,"identifiers":1277},"Poensgen, C. A., and Gallus, H. E., 1996, “Rotating Stall in a Single-Stage Axial Flow Compressor,” ASME J. Turbomach., 118, pp. 189–196.",{"doi":1278},"10.1115\u002F1.2836625",{"id":24,"text":1280,"url":24,"identifiers":1281},"Palomba, C., Puddu, P., and Nurzia, F., 1998, “3D Flow Field Measurement Around a Rotating Stall Cell,” ASME Paper No. 98-GT-594.",{"doi":1282},"10.1115\u002F98-GT-594",{"id":24,"text":1284,"url":24,"identifiers":1285},"Hoying, D. A., Tan, C. S., Huu, Duc Vo, and Greitzer, E. M., 1999, “Role of Blade Passage Flow Structures in Axial Compressor Rotating Stall Inception,” ASME J. Turbomach., 121, pp. 735–742.",{"doi":833},{"id":24,"text":1287,"url":24,"identifiers":1288},"Outa, E., and Kato, D., 1998, “N-S and Experimental Aspects of a Developed Part-Span Stall in an Axial Stage of a Rotor and Stator Cascades,” Proc. US-Japan Seminar, Abnormal Flow Phenomena in Turbomachinery, Osaka.",{},{"id":24,"text":1290,"url":24,"identifiers":1291},"Saxer-Felici, H. M., Saxer, A., Inderbitzin, A., and Gyarmathy, G., 1999, “Prediction and Measurement of Rotating Stall Cells in an Axial Compressor,” ASME J. Turbomach., 121, pp. 365–375.",{"doi":1292},"10.1115\u002F1.2841323",{"id":24,"text":1294,"url":24,"identifiers":1295},"Farge, M.\n          , 1992, “Wavelet Transforms and Their Applications to Turbulence,” Annu. Rev. Fluid Mech., 24, pp. 395–457.",{"doi":1296},"10.1146\u002Fannurev.fluid.24.1.395",{"id":1298,"createTime":1299,"updateTime":1299,"relativeEntities":1300,"slug":1301,"properties":1302,"entityType":107,"verifyStatus":108,"verifyTime":1299,"verifyNote":110,"languages":1313,"translateLanguages":24,"viewCount":25,"primaryUrl":1314,"fullTextUrl":24,"authors":1315,"publicationType":172,"publisherRelationship":1383,"citationCount":1429,"citationInfo":1430,"publishDate":1436,"publishYear":1431,"citationAnalyzeStatus":23,"lastCitationAnalyze":24,"indexDatabases":1437,"openAccess":24,"references":1438,"isForceReanalyzing":227},"a7dafbd0-4ac3-4bc4-89e4-bef7460ae9c3","2025-02-06T17:51:03.192+00:00",[],"The-Role-of-Tip-Leakage-Vortex-Breakdown-in-Compressor-Rotor-Aerodynamics",{"openalex":1303,"mag":1305,"abstract":1307,"title":1309,"doi":1311},{"VOID":1304},"W1986506080",{"VOID":1306},"1986506080",{"EN":1308},"\u003Cjats:p>The breakdown of tip leakage vortex has been investigated on a low-speed axial compressor rotor with moderate blade loading. Effects of the breakdown on the rotor aerodynamics are elucidated by Navier–Stokes flow simulations and visualization techniques for identifying the breakdown. The simulations show that the leakage vortex breakdown occurs inside the rotor at a lower flow rate than the peak pressure rise operating condition. The breakdown is characterized by the existence of the stagnation point followed by a bubblelike recirculation region. The onset of breakdown causes significant changes in the nature of the tip leakage vortex: large expansion of the vortex and disappearance of the streamwise vorticity concentrated in the vortex. The expansion has an extremely large blockage effect extending upstream of the leading edge. The disappearance of the concentrated vorticity results in no rolling-up of the vortex downstream of the rotor and the disappearance of the pressure trough on the casing. The leakage flow field downstream of the rotor is dominated by the outward radial flow, resulting from the contraction of the bubblelike structure of the breakdown region. It is found that the leakage vortex breakdown plays a major role in characteristic of rotor performance at near-stall conditions. As the flow rate is decreased from the peak pressure rise operating condition, the breakdown region grows rapidly in the streamwise, spanwise, and pitchwise directions. The growth of the breakdown causes the blockage and the loss to increase drastically. Then, the interaction of the breakdown region with the blade suction surface gives rise to the three-dimensional separation of the suction surface boundary layer, thus leading to a sudden drop in the total pressure rise across the rotor.\u003C\u002Fjats:p>",{"EN":1310},"The Role of Tip Leakage Vortex Breakdown in Compressor Rotor Aerodynamics",{"VOID":1312},"10.1115\u002F1.2841339",[112],"https:\u002F\u002Fasmedigitalcollection.asme.org\u002Fturbomachinery\u002Farticle\u002F121\u002F3\u002F469\u002F434074\u002FThe-Role-of-Tip-Leakage-Vortex-Breakdown-in",[1316,1333,1349,1366],{"id":1317,"sortIndex":25,"researcher":24,"roles":1318,"affiliations":1319,"properties":1328,"displayName":1330,"givenName":24,"familyName":24},"7257f6fd-994d-4f02-a81c-95822c4c9dbf",[],[1320],{"id":1321,"sortIndex":25,"affiliation":1322,"properties":24},"61c4efce-32ee-46ed-9722-35b7724d2d7f",{"id":1321,"createTime":24,"updateTime":24,"relativeEntities":1323,"slug":24,"properties":1324,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1327,"statistic":24},[],{"title":1325},{"EN":1326},"Department of Mechanical Science and Engineering, Kyushu University, Fukuoka, 812-8581, Japan",[],{"title":1329,"openalex":1331},{"EN":1330},"Manabu Furukawa",{"VOID":1332},"A5108402969",{"id":1334,"sortIndex":138,"researcher":24,"roles":1335,"affiliations":1336,"properties":1343,"displayName":1136,"givenName":24,"familyName":24},"765e5c9c-b390-4411-8c63-0aaca84b1615",[],[1337],{"id":1321,"sortIndex":25,"affiliation":1338,"properties":24},{"id":1321,"createTime":24,"updateTime":24,"relativeEntities":1339,"slug":24,"properties":1340,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1342,"statistic":24},[],{"title":1341},{"EN":1326},[],{"orcid":1344,"title":1346,"openalex":1347},{"VOID":1345},"https:\u002F\u002Forcid.org\u002F0000-0002-9324-2628",{"EN":1136},{"VOID":1348},"A5015830150",{"id":1350,"sortIndex":156,"researcher":24,"roles":1351,"affiliations":1352,"properties":1359,"displayName":1363,"givenName":24,"familyName":24},"667787c5-f95d-45e5-bd01-c74781e26aa7",[],[1353],{"id":1321,"sortIndex":25,"affiliation":1354,"properties":24},{"id":1321,"createTime":24,"updateTime":24,"relativeEntities":1355,"slug":24,"properties":1356,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1358,"statistic":24},[],{"title":1357},{"EN":1326},[],{"orcid":1360,"title":1362,"openalex":1364},{"VOID":1361},"https:\u002F\u002Forcid.org\u002F0000-0002-1851-8604",{"EN":1363},"Keitarou Saiki",{"VOID":1365},"A5013025234",{"id":1367,"sortIndex":301,"researcher":24,"roles":1368,"affiliations":1369,"properties":1376,"displayName":1380,"givenName":24,"familyName":24},"cc9122c9-f3aa-4d92-8f80-b3fff0ad80ee",[],[1370],{"id":1321,"sortIndex":25,"affiliation":1371,"properties":24},{"id":1321,"createTime":24,"updateTime":24,"relativeEntities":1372,"slug":24,"properties":1373,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1375,"statistic":24},[],{"title":1374},{"EN":1326},[],{"orcid":1377,"title":1379,"openalex":1381},{"VOID":1378},"https:\u002F\u002Forcid.org\u002F0000-0003-1427-3483",{"EN":1380},"K. 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K.\n            , ThomasJ. L., and van LeerB., 1986, “Comparison of Finite Volume Flux Vector Splittings for the Euler Equations,” AIAA Journal, Vol. 24, No. 9, pp. 1453–1460.",{"doi":1442},"10.2514\u002F3.9465",{"id":24,"text":1444,"url":24,"identifiers":1445},"Ayder\n              E.\n            , and Van den BraembusscheR., 1994, “Numerical Analysis of the Three-Dimensional Swirling Flow in Centrifugal Compressor Volutes,” ASME JOURNAL OF TURBOMACHINERY, Vol. 116, pp. 462–468.",{"doi":1446},"10.1115\u002F1.2929435",{"id":24,"text":1448,"url":24,"identifiers":1449},"Baldwin, B. S., and Lomax, H., 1978, “Thin Layer Approximation and Algebraic Model for Separated Turbulent Flow,” AIAA Paper No. 78-257.",{"doi":1450},"10.2514\u002F6.1978-257",{"id":24,"text":1452,"url":24,"identifiers":1453},"Chakravarthy, S. R., 1986, “The Versatility and Reliability of Euler Solvers Based on High-Accuracy TVD Formulations,” AIAA Paper No. 86-0243.",{"doi":1454},"10.2514\u002F6.1986-243",{"id":24,"text":1456,"url":24,"identifiers":1457},"Delery\n              J. M.\n            \n          , 1994, “Aspects of Vortex Breakdown,” Progress in Aerospace Sciences, Vol. 30, No. 1, pp. 1–59.",{"doi":1458},"10.1016\u002F0376-0421(94)90002-7",{"id":24,"text":1460,"url":24,"identifiers":1461},"Escudier\n              M.\n            \n          , 1988, “Vortex Breakdown: Observations and Explanations,” Progress in Aerospace Sciences, Vol. 25, No. 2, pp. 189–229.",{"doi":1462},"10.1016\u002F0376-0421(88)90007-3",{"id":24,"text":1464,"url":24,"identifiers":1465},"Furukawa\n              M.\n            , YamasakiM., and InoueM., 1991, “A Zonal Approach for Navier–Stokes Computations of Compressible Cascade Flow Fields Using a TVD Finite Volume Method,” ASME JOURNAL OF TURBOMACHINERY, Vol. 113, pp. 573–582.",{"doi":1466},"10.1115\u002F1.2929118",{"id":24,"text":1468,"url":24,"identifiers":1469},"Furukawa\n              M.\n            , NakanoT., and InoueM., 1992, “Unsteady Navier–Stokes Simulation of Transonic Cascade Flow Using an Unfactored Implicit Upwind Relaxation Scheme With Inner Iterations,” ASME JOURNAL OF TURBOMACHINERY, Vol. 114, pp. 599–606.",{"doi":1470},"10.1115\u002F1.2929184",{"id":24,"text":1472,"url":24,"identifiers":1473},"Furukawa\n              M.\n            , SaikiK., and InoueM., 1995, “Numerical Simulation of Three-Dimensional Viscous Flow in Diagonal Flow Impeller,” in: Numerical Simulations in Turbomachinery, ASME FED-Vol. 227, pp. 29–36.",{},{"id":24,"text":1475,"url":24,"identifiers":1476},"Furukawa\n              M.\n            , SaikiK., NagayoshiK., KuroumaruM., and InoueM., 1998, “Effects of Stream Surface Inclination on Tip Leakage Flow Fields in Compressor Rotors,” ASME JOURNAL OF TURBOMACHINERY, Vol. 120, pp. 683–692.",{"doi":1477},"10.1115\u002F1.2841777",{"id":24,"text":1479,"url":24,"identifiers":1480},"Hall\n              M. G.\n            \n          , 1972, “Vortex Breakdown,” Annual Review of Fluid Mechanics, Vol. 4, pp. 195–218.",{"doi":1481},"10.1146\u002Fannurev.fl.04.010172.001211",{"id":24,"text":1483,"url":24,"identifiers":1484},"Inoue, M., and Furukawa, M., 1994, “Artificial Dissipative and Upwind Schemes for Turbomachinery Blade Flow Calculations,” VKI Lecture Series No. 1994-06.",{},{"id":24,"text":1486,"url":24,"identifiers":1487},"Inoue\n              M.\n            , and KuroumaruM., 1984, “Three-Dimensional Structure and Decay of Vortices Behind an Axial Flow Rotating Blade Row,” ASME Journal of Engineering for Gas Turbines and Power, Vol. 106, pp. 561–569.",{"doi":1488},"10.1115\u002F1.3239607",{"id":24,"text":1490,"url":24,"identifiers":1491},"Inoue\n              M.\n            , KuroumaruM., and FukuharaM., 1986, “Behavior of Tip Leakage Flow Behind an Axial Compressor Rotor,” ASME Journal of Engineering for Gas Turbines and Power, Vol. 108, pp. 7–14.",{"doi":1492},"10.1115\u002F1.3239889",{"id":24,"text":1494,"url":24,"identifiers":1495},"Inoue\n              M.\n            , and KuroumaruM., 1989, “Structure of Tip Clearance Flow in an Isolated Axial Compressor Rotor,” ASME JOURNAL OF TURBOMACHINERY, Vol. 111, No. 3, pp. 250–256.",{"doi":1496},"10.1115\u002F1.3262263",{"id":24,"text":1498,"url":24,"identifiers":1499},"Inoue, M., Kuroumaru, M., and Ando, Y., 1990, “Behavior of Tip Clearance Flow in Axial Flow Impellers at Low Flow Rate,” Proc. 3rd Japan–China Joint Conference on Fluid Machinery, Vol. II, pp. 179–186.",{},{"id":24,"text":1501,"url":24,"identifiers":1502},"Inoue\n              M.\n            , KuroumaruM., IwamotoT., and AndoY., 1991, “Detection of a Rotating Stall Precursor in Isolated Axial Flow Compressor Rotors,” ASME JOURNAL OF TURBOMACHINERY, Vol. 113, No. 2, pp. 281–289.",{"doi":1503},"10.1115\u002F1.2929102",{"id":24,"text":1505,"url":24,"identifiers":1506},"Inoue, M., Furukawa, M., Saiki, K., and Yamada, K., 1998, “Physical Explanations of Tip Leakage Flow Field in an Axial Compressor Rotor,” Paper No. 98-GT-91.",{"doi":1507},"10.1115\u002F98-GT-091",{"id":24,"text":1509,"url":24,"identifiers":1510},"Lakshminarayana\n              B.\n            , ZaccariaM., and MaratheB., 1995, “The Structure of Tip Clearance Flow in Axial Flow Compressors,” ASME JOURNAL OF TURBOMACHINERY, Vol. 117, pp. 336–347.",{"doi":1511},"10.1115\u002F1.2835667",{"id":24,"text":1513,"url":24,"identifiers":1514},"Leibovich\n              S.\n            \n          , 1978, “The Structure of Vortex Breakdown,” Annual Review of Fluid Mechanics, Vol. 10, pp. 211–246.",{"doi":1515},"10.1146\u002Fannurev.fl.10.010178.001253",{"id":24,"text":1517,"url":24,"identifiers":1518},"Leibovich\n              S.\n            \n          , 1984, “Vortex Stability and Breakdown: Survey and Extension,” AIAA Journal, Vol. 22, No. 9, pp. 1192–1206.",{"doi":1519},"10.2514\u002F3.8761",{"id":24,"text":1521,"url":24,"identifiers":1522},"Levy\n              Y.\n            , DeganiD., and SeginerA., 1990, “Graphical Visualization of Vortical Flows by Means of Helicity,” AIAA Journal, Vol. 28, pp. 1347–1352.",{"doi":1523},"10.2514\u002F3.25224",{"id":24,"text":1525,"url":24,"identifiers":1526},"Maskell, E. C., 1955, “Flow Separation in Three Dimensions,” RAE Aero. Rept. 2655.",{},{"id":24,"text":1528,"url":24,"identifiers":1529},"Perry\n              A. E.\n            , and ChongM. S., 1987, “A Description of Eddying Motions and Flow Patterns Using Critical-Point Concepts,” Annual Review of Fluid Mechanics, Vol. 19, pp. 125–155.",{"doi":1530},"10.1146\u002Fannurev.fluid.19.1.125",{"id":24,"text":1532,"url":24,"identifiers":1533},"Sawada\n              K.\n            \n          , 1995, “A Convenient Visualization Method for Identifying Vortex Centers,” Trans. Japan Soc. of Aero. Space Sci., Vol. 38, No. 120, pp. 102–116.",{},{"id":24,"text":1535,"url":24,"identifiers":1536},"Swanson, R. C., and Turkel, E., 1993, “Aspects of a High-Resolution Scheme for the Navier–Stokes Equations,” AIAA Paper No. 93-3372-CP.",{"doi":1537},"10.2514\u002F6.1993-3372",{"id":24,"text":1539,"url":24,"identifiers":1540},"Schlechtriem, S., and Lotzerich, M., 1997, “Breakdown of Tip Leakage Vortices in Compressors at Flow Conditions Close to Stall,” ASME Paper No. 97-GT-41.",{"doi":1541},"10.1115\u002F97-GT-041",{"id":24,"text":1543,"url":24,"identifiers":1544},"Van Leer, B., Thomas, J. L., Roe, P. L., and Newsome, R. W., 1987, “A Comparison of Numerical Flux Formulas for the Euler and Navier–Stokes Equations,” AIAA Paper No. 87-1104.",{},{"id":24,"text":1546,"url":24,"identifiers":1547},"Zhiyong, L., 1991, “A Study on Mode of 3-Dimensional Separation and Open Separation,” in: Separated Flows and Jets, Springer-Verlag, pp. 219–223.",{"doi":1548},"10.1007\u002F978-3-642-84447-8_32",{"id":1550,"createTime":1551,"updateTime":1551,"relativeEntities":1552,"slug":1553,"properties":1554,"entityType":107,"verifyStatus":108,"verifyTime":1551,"verifyNote":110,"languages":1563,"translateLanguages":24,"viewCount":25,"primaryUrl":1564,"fullTextUrl":24,"authors":1565,"publicationType":172,"publisherRelationship":1662,"citationCount":1705,"citationInfo":1706,"publishDate":1708,"publishYear":1012,"citationAnalyzeStatus":23,"lastCitationAnalyze":24,"indexDatabases":1709,"openAccess":24,"references":1710,"isForceReanalyzing":227},"e537517a-cb92-4f55-8753-258869cb36f7","2025-02-06T17:51:02.940+00:00",[],"Stall-Inception-in-Low-Pressure-Ratio-Fans",{"openalex":1555,"abstract":1557,"title":1559,"doi":1561},{"VOID":1556},"W4229856125",{"EN":1558},"\u003Cjats:p>A combined experimental and computational test program, with two low-pressure ratio aero-engine fans, has been used to identify the flow mechanisms at stall inception and the subsequent stall cell growth. The two fans have the same rotor tip clearance, annulus design, and downstream stators, but different levels of tip loading. The measurement data show that both the fans stall via spike-type inception, but that the growth of the stall cell and the final cell size is different in each fan. The computations, reproducing both the qualitative and quantitative behavior of the steady-state and transient measurements, are used to identify the flow mechanisms at the origin of stall inception. In one fan, spillage of tip leakage flow upstream of the leading edge plane is responsible. In the other, sudden growth of casing corner separation blockage leads to stall. These two mechanisms are in accord with the findings from core compressors. However, the transonic aerodynamics and the low hub-to-tip radius ratio of the fans lead to the following two findings: first, the casing corner separation is driven by shock-boundary layer interaction and second, the spanwise loading distribution of the fan determines whether the spike develops into full-span or part-span stall and both types of behavior are represented in the present work. Finally, the axial momentum flux of the tip clearance flow is shown to be a useful indicator of the leakage jet spillage mechanism. A simple model is provided that links the tip loading, stagger, and solidity with the tip clearance axial momentum flux, thereby allowing the aerodynamicist to connect, qualitatively, design parameters with the stall behavior of the fan.\u003C\u002Fjats:p>",{"EN":1560},"Stall Inception in Low-Pressure Ratio Fans",{"VOID":1562},"10.1115\u002F1.4042731",[112],"https:\u002F\u002Fasmedigitalcollection.asme.org\u002Fturbomachinery\u002Farticle\u002Fdoi\u002F10.1115\u002F1.4042731\u002F476913\u002FStall-Inception-in-LowPressure-Ratio-Fans",[1566,1583,1596,1613,1628,1645],{"id":1567,"sortIndex":25,"researcher":24,"roles":1568,"affiliations":1569,"properties":1576,"displayName":1580,"givenName":24,"familyName":24},"d5179616-4205-4019-ac2b-b6ac24692e3c",[],[1570],{"id":270,"sortIndex":25,"affiliation":1571,"properties":24},{"id":270,"createTime":24,"updateTime":24,"relativeEntities":1572,"slug":24,"properties":1573,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1575,"statistic":24},[],{"title":1574},{"VI":275},[],{"orcid":1577,"title":1579,"openalex":1581},{"VOID":1578},"https:\u002F\u002Forcid.org\u002F0000-0002-0563-3902",{"EN":1580},"Seunghwan Kim",{"VOID":1582},"A5100451556",{"id":1584,"sortIndex":138,"researcher":24,"roles":1585,"affiliations":1586,"properties":1593,"displayName":262,"givenName":24,"familyName":24},"8a6f1ab4-11f8-4f6a-96c5-357bd5484761",[],[1587],{"id":896,"sortIndex":25,"affiliation":1588,"properties":24},{"id":896,"createTime":24,"updateTime":24,"relativeEntities":1589,"slug":24,"properties":1590,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1592,"statistic":24},[],{"title":1591},{"EN":901},[],{"title":1594,"openalex":1595},{"EN":262},{"VOID":264},{"id":1597,"sortIndex":156,"researcher":24,"roles":1598,"affiliations":1599,"properties":1606,"displayName":1610,"givenName":24,"familyName":24},"0ad105d7-f977-469f-bf43-af1b2f95510a",[],[1600],{"id":270,"sortIndex":25,"affiliation":1601,"properties":24},{"id":270,"createTime":24,"updateTime":24,"relativeEntities":1602,"slug":24,"properties":1603,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1605,"statistic":24},[],{"title":1604},{"VI":275},[],{"orcid":1607,"title":1609,"openalex":1611},{"VOID":1608},"https:\u002F\u002Forcid.org\u002F0000-0001-5873-4160",{"EN":1610},"Cesare A. 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J. Gunn",{"VOID":1661},"A5020045028",{"url":24,"publisher":1663,"properties":1701},{"id":6,"createTime":7,"updateTime":8,"relativeEntities":1664,"slug":10,"properties":1665,"entityType":22,"verifyStatus":23,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":25,"subjectFields":1670,"manageAffiliations":1675,"indexDatabases":1686,"url":83,"thumbnailPath":24,"statistic":24,"gsStatistic":24,"type":24,"analyzePriority":24},[],{"country":1666,"eissn":1667,"issn":1668,"title":1669},{"VOID":13},{"VOID":15},{"VOID":17},{"EN":19},[1671],{"id":28,"createTime":24,"updateTime":24,"relativeEntities":1672,"label":1673,"description":1674,"parentId":24,"standard":24,"scholarHubFieldId":24},[],{"EN":31},{},[1676,1681],{"id":35,"createTime":24,"updateTime":24,"relativeEntities":1677,"slug":24,"properties":1678,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1680,"statistic":24},[],{"title":1679},{"EN":39},[],{"id":42,"createTime":24,"updateTime":24,"relativeEntities":1682,"slug":24,"properties":1683,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1685,"statistic":24},[],{"title":1684},{"EN":46},[],[1687,1694],{"id":50,"indexDatabase":1688,"url":63,"indexYears":24,"academicFieldIds":1693,"indexDatabaseRanking":24},{"id":52,"createTime":24,"updateTime":24,"relativeEntities":1689,"label":1690,"description":1691,"key":59,"publicationTags":1692,"standard":24},[],{"EN":55,"VI":55},{"EN":57,"VI":58},[61,62],[65],{"id":67,"indexDatabase":1695,"url":78,"indexYears":79,"academicFieldIds":1700,"indexDatabaseRanking":82},{"id":69,"createTime":24,"updateTime":24,"relativeEntities":1696,"label":1697,"description":1698,"key":75,"publicationTags":1699,"standard":24},[],{"EN":72,"VI":72},{"EN":72,"VI":74},[77],[81],{"issue":1702,"volume":1704},{"VOID":1703},"7",{"VOID":1009},32,{"total":1705,"publishYear":1012,"statisticByYear":1707},{"2019":319,"2020":581,"2022":219,"2023":581,"2024":804},"2019-07-01",[61,82],[1711,1714,1717,1721,1724,1728,1732,1736,1740,1744,1747,1750,1754,1758,1761,1765,1767],{"id":24,"text":1712,"url":24,"identifiers":1713},"Camp, 1998, A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor, ASME J. Turbomach., 120, 393, 10.1115\u002F1.2841730",{"doi":394},{"id":24,"text":1715,"url":24,"identifiers":1716},"Garnier, 1991, Rotating Waves as a Stall Inception Indication in Axial Compressors, ASME J. Turbomach., 113, 290, 10.1115\u002F1.2929105",{"doi":398},{"id":24,"text":1718,"url":24,"identifiers":1719},"Tan, 2010, Spike-Type Compressor Stall Inception, Detection and Control, Ann. Rev. Fluid Mech., 42, 275, 10.1146\u002Fannurev-fluid-121108-145603",{"doi":1720},"10.1146\u002Fannurev-fluid-121108-145603",{"id":24,"text":1722,"url":24,"identifiers":1723},"Pullan, 2015, Origins and Structure of Spike-Type Rotating Stall, ASME J. Turbomach., 137, 051007, 10.1115\u002F1.4028494",{"doi":243},{"id":24,"text":1725,"url":24,"identifiers":1726},"Hewkin-Smith, 2017, The Role of Tip Leakage Flow in Spike-Type Rotating Stall Inception, 10.1115\u002FGT2017-63655",{"doi":1727},"10.1115\u002FGT2017-63655",{"id":24,"text":1729,"url":24,"identifiers":1730},"Strazisar, 1985, Investigation of Flow Phenomena in a Transonic Fan Rotor Using Laser Anemometry, ASME J. Eng. Gas Turbines Power, 107, 427, 10.1115\u002F1.3239743",{"doi":1731},"10.1115\u002F1.3239743",{"id":24,"text":1733,"url":24,"identifiers":1734},"Copenhaver, 1997, Unsteady Flow and Shock Motion in a Transonic Compressor Rotor, AIAA J. Propulsion Power, 13, 17, 10.2514\u002F2.5145",{"doi":1735},"10.2514\u002F2.5145",{"id":24,"text":1737,"url":24,"identifiers":1738},"Adamczyk, 1993, The Role of Tip Clearance in High-speed Fan Stall, ASME J. Turbomach., 115, 28, 10.1115\u002F1.2929212",{"doi":1739},"10.1115\u002F1.2929212",{"id":24,"text":1741,"url":24,"identifiers":1742},"Hah, 2006, Short Length Scale Rotating Stall Inception in a Transonic Axial Compressor: Criteria and mechanisms, 10.1115\u002FGT2006-90045",{"doi":1743},"10.1115\u002FGT2006-90045",{"id":24,"text":1745,"url":24,"identifiers":1746},"Choi, 2012, Validation of Numerical Simulation for Rotating Stall in a Transonic Fan, ASME J. Turbomach., 135, 021004, 10.1115\u002F1.4006641",{"doi":690},{"id":24,"text":1748,"url":24,"identifiers":1749},"Korsia, 2009, Vital European Research and Development Programme For Greener Aero-engines",{},{"id":24,"text":1751,"url":24,"identifiers":1752},"Gunn, 2014, Aerodynamics of Boundary Layer Ingesting Fans, 10.1115\u002FGT2014-26142",{"doi":1753},"10.1115\u002FGT2014-26142",{"id":24,"text":1755,"url":24,"identifiers":1756},"Lee, 2017, Validation of a Numerical Model for Predicting Stalled Flows in a Low-Speed Fan, 10.1115\u002FGT2017-63245",{"doi":1757},"10.1115\u002FGT2017-63245",{"id":24,"text":1759,"url":24,"identifiers":1760},"Brandvik, 2011, An Accelerated 3D Navier–Stokes Solver for Flows in Turbomachines, ASME J. Turbomach., 133, 021025, 10.1115\u002F1.4001192",{"doi":431},{"id":24,"text":1762,"url":24,"identifiers":1763},"Liu, 2011, Modification of Spalart-Allmaras Model with Consideration of Tubulence Energy Backscatter Using Velocity Helicity, Phys. Lett. A, 375, 2377, 10.1016\u002Fj.physleta.2011.05.023",{"doi":1764},"10.1016\u002Fj.physleta.2011.05.023",{"id":24,"text":641,"url":24,"identifiers":1766},{"doi":479},{"id":24,"text":1768,"url":24,"identifiers":1769},"Emmons, 1955, Compressor Surge and Stall Propagation, Trans. ASME, 79, 455",{},{"id":1771,"createTime":1772,"updateTime":1772,"relativeEntities":1773,"slug":1774,"properties":1775,"entityType":107,"verifyStatus":108,"verifyTime":1772,"verifyNote":110,"languages":1785,"translateLanguages":24,"viewCount":25,"primaryUrl":1786,"fullTextUrl":24,"authors":1787,"publicationType":172,"publisherRelationship":1852,"citationCount":1897,"citationInfo":1898,"publishDate":1901,"publishYear":1431,"citationAnalyzeStatus":23,"lastCitationAnalyze":24,"indexDatabases":1902,"openAccess":24,"references":1903,"isForceReanalyzing":227},"0928b7f9-a77e-46b2-a4f0-42c00e6fc30f","2025-02-06T17:51:01.785+00:00",[],"Role-of-Blade-Passage-Flow-Structurs-in-Axial-Compressor-Rotating-Stall-Inception",{"openalex":1776,"mag":1778,"abstract":1780,"title":1782,"doi":1784},{"VOID":1777},"W1967862827",{"VOID":1779},"1967862827",{"EN":1781},"\u003Cjats:p>The influence of three-dimensional flow structures within a compressor blade passage has been examined computationally to determine their role in rotating stall inception. The computations displayed a short length-scale (or spike) type of stall inception similar to that seen in experiments; to the authors’ knowledge this is the first time such a feature has been simulated. A central feature observed during the rotating stall inception was the tip clearance vortex moving forward of the blade row leading edge. Vortex kinematic arguments are used to provide a physical explanation of this motion as well as to motivate the conditions for its occurrence. The resulting criterion for this type of stall inception (the movement of the tip clearance vortex forward of the leading edge) depends upon local flow phenomena related to the tip clearance with the implication that for this and possibly other stall mechanisms the flow structure within the blade passages must be addressed to explain the stability of an axial compression system that exhibits such short length-scale disturbances.\u003C\u002Fjats:p>",{"EN":1783},"Role of Blade Passage Flow Structurs in Axial Compressor Rotating Stall Inception",{"VOID":833},[112],"https:\u002F\u002Fasmedigitalcollection.asme.org\u002Fturbomachinery\u002Farticle\u002F121\u002F4\u002F735\u002F434280\u002FRole-of-Blade-Passage-Flow-Structurs-in-Axial",[1788,1805,1822,1837],{"id":1789,"sortIndex":25,"researcher":24,"roles":1790,"affiliations":1791,"properties":1800,"displayName":1802,"givenName":24,"familyName":24},"81c7df2f-5e58-4abc-be47-a89cf60cbfb3",[],[1792],{"id":1793,"sortIndex":25,"affiliation":1794,"properties":24},"b37109af-1473-4acb-b412-ce5d39d1b7df",{"id":1793,"createTime":24,"updateTime":24,"relativeEntities":1795,"slug":24,"properties":1796,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1799,"statistic":24},[],{"title":1797},{"EN":1798},"Air Force Research Laboratory, Wright Patterson Air Force Base, Dayton, OH 45433",[],{"title":1801,"openalex":1803},{"EN":1802},"Donald Hoying",{"VOID":1804},"A5081054263",{"id":1806,"sortIndex":138,"researcher":24,"roles":1807,"affiliations":1808,"properties":1817,"displayName":1819,"givenName":24,"familyName":24},"a1937bd2-689b-49d0-a2ba-73695b427759",[],[1809],{"id":1810,"sortIndex":25,"affiliation":1811,"properties":24},"2e4456fa-34af-446f-87ab-1e11e9229eea",{"id":1810,"createTime":24,"updateTime":24,"relativeEntities":1812,"slug":24,"properties":1813,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1816,"statistic":24},[],{"title":1814},{"EN":1815},"Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA 02139",[],{"title":1818,"openalex":1820},{"EN":1819},"C. S. Tan",{"VOID":1821},"A5112064844",{"id":1823,"sortIndex":156,"researcher":24,"roles":1824,"affiliations":1825,"properties":1832,"displayName":1834,"givenName":24,"familyName":24},"220b8d2f-3937-4117-affc-6abb5cb91164",[],[1826],{"id":1810,"sortIndex":25,"affiliation":1827,"properties":24},{"id":1810,"createTime":24,"updateTime":24,"relativeEntities":1828,"slug":24,"properties":1829,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1831,"statistic":24},[],{"title":1830},{"EN":1815},[],{"title":1833,"openalex":1835},{"EN":1834},"Huu Duc Vo",{"VOID":1836},"A5011303063",{"id":1838,"sortIndex":301,"researcher":24,"roles":1839,"affiliations":1840,"properties":1849,"displayName":314,"givenName":24,"familyName":24},"1904820e-f814-4319-b030-1c4e2c747492",[],[1841],{"id":1842,"sortIndex":25,"affiliation":1843,"properties":24},"4d65c471-6e02-4899-a59b-899356920a4a",{"id":1842,"createTime":24,"updateTime":24,"relativeEntities":1844,"slug":24,"properties":1845,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1848,"statistic":24},[],{"title":1846},{"VI":1847},"United Technologies Research Center, East Hartford, CT 06108",[],{"title":1850,"openalex":1851},{"EN":314},{"VOID":316},{"url":24,"publisher":1853,"properties":1891},{"id":6,"createTime":7,"updateTime":8,"relativeEntities":1854,"slug":10,"properties":1855,"entityType":22,"verifyStatus":23,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":25,"subjectFields":1860,"manageAffiliations":1865,"indexDatabases":1876,"url":83,"thumbnailPath":24,"statistic":24,"gsStatistic":24,"type":24,"analyzePriority":24},[],{"country":1856,"eissn":1857,"issn":1858,"title":1859},{"VOID":13},{"VOID":15},{"VOID":17},{"EN":19},[1861],{"id":28,"createTime":24,"updateTime":24,"relativeEntities":1862,"label":1863,"description":1864,"parentId":24,"standard":24,"scholarHubFieldId":24},[],{"EN":31},{},[1866,1871],{"id":35,"createTime":24,"updateTime":24,"relativeEntities":1867,"slug":24,"properties":1868,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1870,"statistic":24},[],{"title":1869},{"EN":39},[],{"id":42,"createTime":24,"updateTime":24,"relativeEntities":1872,"slug":24,"properties":1873,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":1875,"statistic":24},[],{"title":1874},{"EN":46},[],[1877,1884],{"id":50,"indexDatabase":1878,"url":63,"indexYears":24,"academicFieldIds":1883,"indexDatabaseRanking":24},{"id":52,"createTime":24,"updateTime":24,"relativeEntities":1879,"label":1880,"description":1881,"key":59,"publicationTags":1882,"standard":24},[],{"EN":55,"VI":55},{"EN":57,"VI":58},[61,62],[65],{"id":67,"indexDatabase":1885,"url":78,"indexYears":79,"academicFieldIds":1890,"indexDatabaseRanking":82},{"id":69,"createTime":24,"updateTime":24,"relativeEntities":1886,"label":1887,"description":1888,"key":75,"publicationTags":1889,"standard":24},[],{"EN":72,"VI":72},{"EN":72,"VI":74},[77],[81],{"issue":1892,"pages":1894,"volume":1896},{"VOID":1893},"4",{"VOID":1895},"735-742",{"VOID":1428},207,{"total":1897,"publishYear":1431,"statisticByYear":1899},{"2012":1433,"2013":803,"2014":219,"2015":806,"2016":805,"2017":1900,"2018":803,"2019":803,"2020":1900,"2021":805,"2022":1900,"2023":1433,"2024":804},13,"1999-10-01",[61,82],[1904,1907,1910,1913,1916,1920,1924,1927,1930,1933,1936,1940,1944,1947,1950,1953,1956,1959,1963,1966,1970,1973],{"id":24,"text":1905,"url":24,"identifiers":1906},"Adamczyk\n              J. J.\n            , CelestinaM. L., and GreitzerE. M., 1993, “The Role of Tip Clearance in High-Speed Fan Stall,” ASME JOURNAL OF TURBOMACHINERY, Vol. 115, pp. 28–38.",{"doi":1739},{"id":24,"text":1908,"url":24,"identifiers":1909},"Camp, T. R., 1995, “Aspects of the Off-Design Performance of Axial Flow Compressors,” PhD Thesis, University of Cambridge.",{},{"id":24,"text":1911,"url":24,"identifiers":1912},"Cumpsty, N. A., 1989, Compressor Aerodynamics, Longman Scientific & Technical, Essex, England.",{},{"id":24,"text":1914,"url":24,"identifiers":1915},"Day\n              I. J.\n            \n          , 1993, “Stall Inception in Axial Flow Compressors,” ASME JOURNAL OF TURBOMACHINERY, Vol. 115, pp. 1–9.",{"doi":813},{"id":24,"text":1917,"url":24,"identifiers":1918},"Gong, Y., Tan, C. S., Gordon, K., and Greitzer, E. M., 1998, “A Computational Model for Short Wave-Length Stall Inception and Development in Multi-Stage Compressor,” Submitted for TurboExpo98, Stockholm, Sweden.",{"doi":1919},"10.1115\u002F98-GT-476",{"id":24,"text":1921,"url":24,"identifiers":1922},"Haynes\n              J. M.\n            , HendricksG. J., and EpsteinA. H., 1994, “Active Stabilization of Rotating Stall in a Three-Stage Axial Compressor,” ASME JOURNAL OF TURBOMACHINERY, Vol. 116, pp. 226–239.",{"doi":1923},"10.1115\u002F1.2928357",{"id":24,"text":1925,"url":24,"identifiers":1926},"He, L., and Ismael, J. O., 1997, “Computations of Blade Row Stall Inception in Transonic Flows,” Proc. ISABE 1997, Paper No. 97-7100, pp. 697–707.",{},{"id":24,"text":1928,"url":24,"identifiers":1929},"Hoying, D. A., 1996, “Blade Passage Flow Structure Effects on Axial Compressor Rotating Stall Inception,” PhD Thesis, Massachusetts Institute of Technology.",{},{"id":24,"text":1931,"url":24,"identifiers":1932},"Khalid, S. A., 1995, “The Effects of Tip Clearance on Axial Compressor Pressure Rise,” PhD Thesis, Massachusetts Institute of Technology.",{},{"id":24,"text":1934,"url":24,"identifiers":1935},"Koch\n              C. C.\n            \n          , 1981, “Stalling Pressure Rise Capability of Axial Flow Compressor Stages,” ASME Journal of Engineering for Power, Vol. 103, pp. 645–656.",{"doi":1094},{"id":24,"text":1937,"url":24,"identifiers":1938},"Moore\n              F. K.\n            , and GreitzerE. M., 1986a, “A Theory of Post-Stall Transients in Axial Compression Systems: Part I—Development of Equations,” ASME Journal of Engineering for Gas Turbines and Power, Vol. 108, pp. 68–76.",{"doi":1939},"10.1115\u002F1.3239887",{"id":24,"text":1941,"url":24,"identifiers":1942},"Moore\n              F. K.\n            , and GreitzerE. M., 1986b, “A Theory of Post-Stall Transients in Axial Compression Systems: Part II—Application,” ASME Journal of Engineering for Gas Turbines and Power, Vol. 108, pp. 231–239.",{"doi":1943},"10.1115\u002F1.3239893",{"id":24,"text":1945,"url":24,"identifiers":1946},"Park, H. G., 1994, “Unsteady Disturbance Structures in Axial Flow Compressor Stall Inception,” Master’s Thesis, Massachusetts Institute of Technology.",{},{"id":24,"text":1948,"url":24,"identifiers":1949},"Seitz, P., and Cumpsty, N. A., 1999, Private Communication.",{},{"id":24,"text":1951,"url":24,"identifiers":1952},"Silkowski, P. D., 1995, “Measurements of Rotor Stalling in a Matched and a Mismatched Multistage Compressor,” GTL Report No. 221, Gas Turbine Laboratory, Massachusetts Institute of Technology.",{},{"id":24,"text":1954,"url":24,"identifiers":1955},"Smith, L. H., Jr., 1970, “Casing Boundary Layers in Multistage Axial-Flow Compressors,” Flow Research on Blading, L. S. Dzung, ed., Elsevier Pub. Co., Amsterdam.",{},{"id":24,"text":1957,"url":24,"identifiers":1958},"Storer\n              J. A.\n            , and CumpstyN. A., 1991, “Tip Leakage Flows in Axial Compressors,” ASME JOURNAL OF TURBOMACHINERY, Vol. 113, pp. 252–259.",{"doi":1041},{"id":24,"text":1960,"url":24,"identifiers":1961},"Tam\n              C. K. W.\n            , and WebbJ. C., 1993, “Dispersion-Relation-Preserving Finite Difference Schemes for Computational Acoustics,” Journal of Computational Physics, Vol. 107, pp. 262–281.",{"doi":1962},"10.1006\u002Fjcph.1993.1142",{"id":24,"text":1964,"url":24,"identifiers":1965},"Tryfonidis\n              M.\n            , EtcheversO., PaduanoJ. D., HendricksG. F., and EpsteinA. H., 1995, “Pre-Stall Behavior of Several High-Speed Compressors,” ASME JOURNAL OF TURBOMACHINERY, Vol. 117, pp. 62–80.",{},{"id":24,"text":1967,"url":24,"identifiers":1968},"Van Zante, D., et al., 1999, “Recommendations for Achieving Accurate Simulation of Tip Clearance Flows in Transonic Compressor Rotors,” ASME Paper No. 99-GT-390.",{"doi":1969},"10.1115\u002F99-GT-390",{"id":24,"text":1971,"url":24,"identifiers":1972},"Weingold, H., 1998, Private Communication.",{},{"id":24,"text":1974,"url":24,"identifiers":1975},"Wisler, D. C., 1981, “Core Compressor Exit Stage Study, Volume IV—Data and Performance Report for the Best Stage Configuration,” NASA CR-165357, NASA Lewis Research Center.",{},{"id":1977,"createTime":1978,"updateTime":1978,"relativeEntities":1979,"slug":1980,"properties":1981,"entityType":107,"verifyStatus":108,"verifyTime":1978,"verifyNote":110,"languages":1992,"translateLanguages":24,"viewCount":25,"primaryUrl":1993,"fullTextUrl":24,"authors":1994,"publicationType":172,"publisherRelationship":2053,"citationCount":2095,"citationInfo":2096,"publishDate":2098,"publishYear":801,"citationAnalyzeStatus":23,"lastCitationAnalyze":24,"indexDatabases":2099,"openAccess":24,"references":2100,"isForceReanalyzing":227},"daa44e49-0b41-474d-b479-82fbf0dbc460","2025-02-06T17:51:01.365+00:00",[],"Stall-Warning-by-Blade-Pressure-Signature-Analysis",{"openalex":1982,"mag":1984,"abstract":1986,"title":1988,"doi":1990},{"VOID":1983},"W2034540627",{"VOID":1985},"2034540627",{"EN":1987},"\u003Cjats:p>At low mass flow rates, axial compressors suffer from flow instabilities leading to stall and surge. The inception process of these instabilities has been widely researched in the past---primarily with the aim of predicting or averting stall onset. In recent times, attention has shifted to conditions well before stall and has focused on the level of irregularity in the blade passing signature in the rotor tip region. In general, the irregularity increases in intensity as the flow rate through the compressor is reduced. Attempts have been made to develop stall warning\u002Favoidance procedures based on the level of flow irregularity, but little effort has been made to characterize the irregularity itself, or to understand its underlying cause. Work on this project has revealed for the first time that the increase in irregularity in the blade passing signature is highly dependent on both tip-clearance size and eccentricity. In a compressor with small, uniform, tip-clearance, the increase in blade passing irregularity that accompanies a reduction in flow rate will be modest. If the tip-clearance is enlarged, however, there will be a sharp rise in irregularity at all circumferential locations. In a compressor with eccentric tip-clearance, the increase in irregularity will only occur in the part of the annulus where the tip-clearance is largest, regardless of the average clearance level. In this paper, some attention is also given to the question of whether the irregularity observed in the prestall flow field is due to random turbulence or to some form of coherent flow structure. Detailed flow measurements reveal that the latter is the case. From these findings, it is clear that a stall warning system based on blade passing signature irregularity would be difficult to implement in an aero-engine where tip-clearance size and eccentricity change during each flight cycle and over the life of the compressor.\u003C\u002Fjats:p>",{"EN":1989},"Stall Warning by Blade Pressure Signature Analysis",{"VOID":1991},"10.1115\u002F1.4006426",[112],"https:\u002F\u002Fasmedigitalcollection.asme.org\u002Fturbomachinery\u002Farticle\u002Fdoi\u002F10.1115\u002F1.4006426\u002F378435\u002FStall-Warning-by-Blade-Pressure-Signature-Analysis",[1995,2019,2038],{"id":1996,"sortIndex":25,"researcher":24,"roles":1997,"affiliations":1998,"properties":2015,"displayName":281,"givenName":24,"familyName":24},"b0b417a8-f0ec-45fb-95f3-ed28d5df6e59",[],[1999,2007],{"id":2000,"sortIndex":25,"affiliation":2001,"properties":24},"5cf3f7d6-57f9-4b8e-a070-6c4aa05c5d6d",{"id":2000,"createTime":24,"updateTime":24,"relativeEntities":2002,"slug":24,"properties":2003,"entityType":24,"verifyStatus":24,"verifyTime":24,"verifyNote":24,"languages":24,"translateLanguages":24,"viewCount":24,"url":24,"parentIds":2006,"statistic":24},[],{"title":2004},{"VI":2005},"University of Cambridge, Cambridge, 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Whittle Laboratory, University of Cambridge, Cambridge CB3 0DY, 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A Theory of Post-Stall Transients in Axial Compression Systems. I. Development of Equations, ASME J. Eng. Gas Turbines Power, 108, 68, 10.1115\u002F1.3239887",{"doi":1939},{"id":24,"text":2105,"url":24,"identifiers":2106},"1986, A Theory of Post-Stall Transients in Axial Compression Systems. II. Application, ASME J. Eng. Gas Turbines Power, 108, 231, 10.1115\u002F1.3239893",{"doi":1943},{"id":24,"text":2108,"url":24,"identifiers":2109},"1998, A Study of Spike and Modal Stall Inception in a Low-Speed Axial Compressor, ASME J. Turbomach., 120, 393",{},{"id":24,"text":2111,"url":24,"identifiers":2112},"Strazisar, A. J., Bright, M. M., Thorp, S., Culley, D. E., and Suder, K. L., 2004, “Compressor Stall Control Through Endwall Recirculation,” Proceedings of ASME Turbo Expo 2004, Vienna, Austria, June14–17, ASME Paper No. GT2004-54295. 10.1115\u002FGT2004-54295",{"doi":2113},"10.1115\u002FGT2004-54295",{"id":24,"text":2115,"url":24,"identifiers":2116},"März, J., Hah, C., and Neise, W., 2001, “An Experimental and Numerical Investigation into the Mechanisms of Rotating Instability,” Proceedings of ASME Turbo Expo 2001, New Orleans, LA, June4–7, Paper No. 2001-GT-0536.",{},{"id":24,"text":2118,"url":24,"identifiers":2119},"Dhingra, M., Neumeier, Y., Prasad, J. V. R., and Shin, H.-W., 2003, “Stall and Surge Precursors in Axial Compressors,” 39th AIAA\u002FASME\u002FSAE\u002FASEE Joint Propulsion Conference and Exhibit, Hunstville, AL, July20–23, Paper No. AIAA 2003-4425.",{"doi":2120},"10.2514\u002F6.2003-4425",{"id":24,"text":2122,"url":24,"identifiers":2123},"Liu, Y., Dhingra, M., and Prasad, J. V. R., 2009, “Active Compressor Stability Management via a Stall Margin Control Mode,” Proceedings of ASME Turbo Expo 2009, Orlando, FL, June 8–12, ASME Paper No. GT2009-60140.10.1115\u002FGT2009-60140",{},{"id":24,"text":2125,"url":24,"identifiers":2126},"Christensen, D., Cantin, P., Gutz, D., Szucs, P. N., Wadia, A. R., Armor, J., Dhingra, M., Neumeier, Y., and Prasad, J. V. R., 2008, “Development and Demonstration of a Stability Management System for Gas Turbine Engines,” ASME J. Turbomach., 130, pp. 1–8. 10.1115\u002F1.2777176",{"doi":2127},"10.1115\u002F1.2777176",{"id":24,"text":2129,"url":24,"identifiers":2130},"Gannon, A. J., Hobson, G. V., and Davis, W. 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