Spike-Type Compressor Stall Inception, Detection, and Control

Annual Review of Fluid Mechanics - Tập 42 Số 1 - Trang 275-300 - 2010
C. S. Tan1, I. J. Day2, Scott Morris3, A. R. Wadia4
1Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, Massachusetts 02139;
2Whittle Laboratory, University of Cambridge, Cambridge CB3 0DY, United Kingdom;
3Hessert Laboratory for Aerospace Research, University of Notre Dame, Notre Dame, Indiana 46556;
4Chief Engineer's Office, General Electric Aviation, Cincinnati, Ohio 45215;

Tóm tắt

An aerodynamic instability known as stall occurs in axial compressors as the mass flow rate is reduced and the blade loading reaches its limit. At this limiting condition, an easily recognizable flow breakdown process, known as spike-type stall inception, is observed in most modern compressors. This article begins by examining measurements from both low- and high-speed compressors to explain the characteristic features of spike-type stall. This is followed by a review of past work on compressor stability and an assessment of recent advances in this field. Included here is a study of the three-dimensional flow features that typify spike formation and its eventual growth into a mature stall cell. We also consider the formation criteria for spike-type stall and the means for early detection and possible control. On the computational side, a possible mechanism for spike formation is identified from three-dimensional studies of the flow in the rotor tip region. This mechanism involves tip-clearance backflow at the blade's trailing edge in combination with forward spillage of tip-leakage flow at the leading edge. This flow pattern implies that a successful stall-control technology will have to rely on an effective means of suppressing tip-clearance backflow and forward spillage.

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Tài liệu tham khảo

Bae J. 2001. Active control of compressor tip clearance flow. PhD thesis, Mass. Inst. Technol., Cambridge. 93 pp.

Bae J, Breuer K, Tan CS. 2004. Periodic unsteadiness in compressor tip clearance vortex. Presented at Am. Soc. Mech. Eng. Turbo Expo 04, Vienna, Austria

10.1115/1.1776584

Bennington M, Cameron J, Morris S, Gendrich C. 2007. Over rotor casing surface streak measurements in a high speed axial compressors. Presented at Am. Soc. Mech. Eng. Turbo Expo 07, Montreal, Canada

Bennington M, Cameron J, Morris S, Legault C, Barrows S, et al. 2008. Investigation of tip-flow based stall criteria using rotor casing visualization. Presented at Am. Soc. Mech. Eng. Turbo Expo 08, Berlin, Germany

Brouckaert JF, Van de Wyer N, Farkas B, Ullmann F, Desset J, et al. 2009. Unsteady pressure measurements in a single stage low pressure axial compressor: tip vortex flow and stall inception. Presented at Am. Soc. Mech. Eng. Turbo Expo 09, Orlando, Florida

Cameron J, Morris S. 2007. Spatial correlation based stall inception analysis. Presented at Am. Soc. Mech. Eng. Turbo Expo 07, Montreal, Canada

Cameron J, Morris S, Barrows S, Chen JP. 2008. On the interpretation of casing measurements in axial compressors. Presented at Am. Soc. Mech. Eng. Turbo Expo 08, Berlin, Germany

10.1115/1.2841730

10.2514/1.41428

10.1115/1.2777176

10.1016/0142-727X(89)90040-4

Corke TC, Post ML. 2005. Overview of plasma flow control: concepts, optimization, and applications. Presented at 43rd AIAA Aerosp. Sci. Meet., Reno, Pap. No. AIAA 2005–563

Cumpsty NA, 2004, Compressor Aerodynamics

Day IJ, 1976, Axial compressor stall

10.1115/1.2929216

10.1115/1.2929209

10.1115/1.2841229

10.1115/1.2928353

Deppe A, Saathoff H, Stark U. 2005. Spike-type stall inception in axial compressors. Proc. 6th Eur. Conf. Turbomach., Lille, France, pp. 178–88

Dhingra M, Neumeier Y, Prasad JVR, Breeze-Stringfellow A, Shin HW, Szucs PN. 2006. A stochastic model for a compressor stability measure. Presented at Am. Soc. Mech. Eng. Turbo Expo 06, Barcelona, Spain

Emmons HW, 1955, Trans. ASME, 79, 455

10.1115/1.2840924

10.1115/1.2841773

Gong Y. 1999. A computational model for rotating stall and inlet distortions in multi-stage compressors. PhD thesis, Mass. Inst. Technol., Cambridge. 187 pp.

10.1115/1.2836726

10.1115/1.3446138

10.1115/1.3241725

Hah C, Bergner J, Schiffer HP. 2006. Short length-scale rotating stall inception in a transonic axial compressor: criteria and mechanism. Presented at Am. Soc. Mech. Eng. Turbo Expo 06, Barcelona, Spain

10.1115/1.2928357

10.1115/1.555425

Houghton TO, Day IJ. 2009. Enhancing the stability of subsonic compressors using casing grooves. Presented at Am. Soc. Mech. Eng. Turbo Expo 09, Orlando, Florida

10.1115/1.2836727

10.1115/1.2929102

10.1016/j.ast.2003.06.001

Koch CC. 1974. Discussion of Benser WA: transonic compressor technology advancements. Fluid mechanics, acoustics, and design of turbomachinery, Part II. NASA SP-304

Lighthill MJ, 1975, Fourier Analysis and Generalised Functions

10.2514/1.36525

10.1115/1.2836624

10.1115/1.2927406

10.1115/1.3239565

10.1115/1.3239887

10.1115/1.1508383

Nolan S. 2005. Effect of radial transport on compressor tip flow structures and enhancement of stable flow range. M.S. thesis, Mass. Inst. Technol., Cambridge. 75 pp.

10.1146/annurev.fluid.33.1.491

Park HG. 1994. Unsteady disturbance structures in axial flow compressor stall inception. M.S. thesis, Mass. Inst. Technol., Cambridge. 150 pp.

10.1146/annurev.fluid.35.101101.161128

Saathoff H, Stark U. 2000. Tip clearance flow induced endwall boundary layer separation in a single-stage axial-flow low-speed compressor. Presented at Am. Soc. Mech. Eng. Turbo Expo 06, Munich, Germany

Silkowski PD, 1995, Gas Turbine Lab. Rep. No. 221

Simpson AK, Longley JP. 2007. An experimental study of the inception of rotating stall in a single stage low-speed axial compressor. Presented at Am. Soc. Mech. Eng. Turbo Expo 07, Montreal, Canada

Spakovszky ZS, Roduner CH. 2007. Spike and modal stall inception in an advanced turbocharger centrifugal compressor. Presented at Am. Soc. Mech. Eng. Turbo Expo 07, Montreal, Canada

10.1115/1.2841345

10.1146/annurev.fluid.30.1.107

Strazisar AJ, Bright MM, Thorp S, Culley D, Suder KL. 2004. Compressor stall control through endwall recirculation. Presented at Am. Soc. Mech. Eng. Turbo Expo 04, Vienna, Austria

10.1115/1.1330272

Tahara N, Outa E, Kurosaki M, Nakakita T, Ohta Y, Tsurumi Y. 2004. Early stall warning technique for axial flow compressors. Presented at Am. Soc. Mech. Eng. Turbo Expo 04, Vienna, Austria

Tong Z, Li L, Nie C. 2009. A method of online stall control by DSP in axial compressors. Presented at Am. Soc. Mech. Eng. Turbo Expo 09, Florida, GT2009–59771

10.1115/1.2835644

Vo HD. 2001. Role of tip clearance flow on axial compressor stability. PhD thesis, Mass. Inst. Technol., Cambridge. 95 pp.

Vo HD, Cameron J, Morris S. 2008a. Control of short length-scale rotating stall inception on a high-speed axial compressor with plasma actuation. Presented at Am. Soc. Mech. Eng. Turbo Expo 08, Berlin, Germany

10.1115/1.2750674

Wadia A, Christensen D, Prasad JVR. 2006. Compressor stability management in aircraft engines. Proc. 25th Congr. Int. Council Aerosp. Sci, Hamburg, Germany, ICAS 2006–5.4.2 (Pap. No. 759)

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Annual Review of Fluid Mechanics

Tập 42 Số 1

275-300

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