Influence of Endwall Air Injection with Discrete Holes on Corner Separation of a Compressor Cascade
Tóm tắt
The aim of this study is to reveal the influence mechanism of endwall air injection with distributed holes on the corner separation of a highly loaded compressor cascade, so as to promote the application of injection in aero-engines. Single-hole and double-hole endwall injection schemes featuring different axial locations, pitchwise locations, injection mass rates and injection directions, were designed and investigated. Results showed that the corner separation was eliminated by endwall injection; the optimal single-hole injection scheme achieved an endwall loss coefficient reduction of 29.7%, with injection coefficient as low as 0.48%. The optimal axial location of single-hole endwall injection was at 82% axial chord, being the center of corner separation. However, as injection hole was located at upstream of it, endwall injection resulted in severer corner separation. The mid-span flow field was deteriorated after endwall injection, which was due to 3D flow effects, i.e., AVDR (axial velocity density ratio) effect and low-momentum fluid spanwise migration effect. The optimal injection was achieved at low injection angle and from close to the suction surface on pitchwise. Double-hole injection exhibited inferior performance compared with single-hole, which was due to the interaction of the two injection streams and mixing of injection streams with the bulk stream.
Tài liệu tham khảo
Meng Q., Du X., Chen S., Wang S.T., Numerical study of dual sweeping jet actuators for corner separation control in compressor cascade. Journal of Thermal Science, 2021, 30: 201–209.
Luo J.Q., Zhou C., Liu F., Multipoint design optimization of a transonic compressor blade by using an adjoint method. Journal of Turbomachinery, 2014, 136(5): 051005.
Lui Y.W., Yan H., Liu Y.J., Lu L.P., Li Q.S., Numerical study of corner separation in a linear compressor cascade using various turbulence models. Chinese Journal of Aeronautics, 2016, 29(3): 639–652.
Horlock J.H., Louis J.F., Percival P.E., Lakshmin B., Wall stall in compressor cascade. Journal of Basic Engineering, 1966, 88(3): 637–648.
Luecke J.R., Gallus H.E., Sanz W., Benestschik H., Platzer M.F., Numerical investigation of transition and hub-corner stall phenomena inside an annular compressor cascade. AIAA paper No. 96-2655, 1996.
Hah C., Loellbach J., Development of hub corner stall and its influence on the performance of axial compressor blade rows. Journal of Turbomachinery, 1999, 121(1): 67–77.
Gbadebo S.A., Cumpsty N.A., Hynes T.P., Three dimensional separations in axial compressors. Journal of Turbomachinery, 2005, 127(3): 331–339.
Scillitoe A.D., Tucker P.G., Adami P., Numerical investigation of three-dimensional separation in an axial flow compressor: the influence of freestream turbulence intensity and endwall boundary layer state. Journal of Turbomachinery, 2017, 139(2): 021011.
Ji L.C., Chen J., Lin F., Review and understanding on sweep in axial compressor design. ASME Paper No. GT2005-68473, 2005.
Wellborn S.R., Delaney R.A., Redesign of a 12-stage axial-flow compressor using multistage CFD. ASME Paper No. 2001-GT-0351, 2001.
Liu B.J., Fu D., Yu X.J., Development of a preliminary design method for subsonic splittered blades in highly loaded axial-flow compressors. Applied Science, 2017, 7(3): 283.
Zhang H.X., Chen S.W., Gong Y., Wang S.T., Wang Z.Q., Combined application of negative bowed blades and unsteady pulsed holed suction in a high-load compressor in terms of aerodynamic performance and energy efficiency. Applied Thermal Engineering, 2018, 144: 291–304.
Guo S., Chen S.W., Song Y.P., Song Y.F., Chen F., Effects of boundary layer suction on aerodynamic performance in a high-load compressor cascade. Chinese Journal of Aeronautics, 2010, 23(2): 179–186.
Hirano T., Ogawa T., Yasui R., Tsujita H., Effect of double air injection on performance characteristics centrifugal compressor. Journal of thermal science, 2017, 26(1): 11–17.
Djedai H., Mdouki R., Mansouri Z., Aouissi M., Numerical investigation of three-dimensional separation control in an axial compressor cascade. International Journal of Heat and Technology, 2017, 35(3): 657–662.
Suder K.L., Hathaway M.D., Thorp S.A., Strazisar A.J., Bright M.B., Compressor stability enhancement using discrete tip injection. ASME Journal of Turbomachinery, 2001, 123(1): 14–23.
Culley D.E., Bright M.M., Prahst P.S., Strazisar A.J., Active flow separation control of a stator vane using surface injection in a multistage compressor experiment. ASME paper No. GT2003-38863, 2003.
Sarimurat M.N., Dang T.Q., An analytical model for boundary layer control via steady blowing and its application to NACA-65-410 cascade. Journal of Turbomachinery, 2013, 136(6): 061011.
Brück C., Tiedemann C., Peitsch D., Experimental investigation on highly loaded compressor airfoils with active flow control under non-steady flow conditions in a 3D-annular low-speed cascade. ASME Paper No. GT2016-56891, 2016.
Feng D.M., Chen F., Song Y.P., Chen H.L., Wang Z.Q., Enhancing aerodynamic performances of highly loaded compressor cascades via air injection. Chinese Journal of Aeronautics, 2009, 22(2): 121–128.
Nerger D., Saathoff H., Radespiel R., Gümmer V., Clemen C., Experimental investigation of endwall and suction side blowing in a highly loaded compressor stator cascade. Journal of Turbomachinery, 2012, 134(2): 021010.
Vorreiter A., Fischer S., Saathoff H., Radespiel R., Seume J.R., Numerical investigations of the efficiency of circulation control in a compressor stator. Journal of Turbomachinery, 2012, 134(2): 021012.
Hu J.G., Wang R.G., Li R.K., Wu P.G., Effects of slot jet and its improved approach in a high-load compressor cascade. Experiments in Fluids, 2017, 58(11): 155.
Dinh C.T., Ma S.B., Kim K.Y., Aerodynamic optimization of a single-stage axial compressor with stator shroud air injection. AIAA journal, 2017, 55(8): 2739–2754.
Dinh C.T., Kim K.Y., Effects of non-axisymmetric casing grooves combined with airflow injection on stability enhancement of an axial compressor. International Journal of Turbo & Jet Engine, 2019, 36(3): 283–296.
Cao Z.Y., Zhou C., Sun Z.L., Comparison of aerodynamic characteristics between a novel highly loaded injected blade with curvature induced pressure-recovery concept and one with conventional design. Chinese Journal of Aeronautics, 2017, 30(3): 939–950.
Kirtley K.R., Graziosi P., Wood P., Beacher B., Shin H.-W., Design and test of an ultra-low solidity flow controlled compressor stator. ASME paper No. GT2004-53012, 2004.
Evans S.W., Hodson H.P., The cost of flow control in a compressor. ASME Paper No. GT2011-45059, 2011.
Cao Z.Y., Liu B., Zhang T., Control of separations in a highly loaded diffusion cascade by tailored boundary layer suction. Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, 2014, 228: 1363–1374.
Liesner K., Meyer R., Lemke M., Gmelin C., Thiele F., On the efficiency of secondary flow suction in a compressor cascade. ASME Paper GT2010-22336, 2010.
Taylor J.V., Miller R.B., Competing three-dimensional mechanisms in compressor flows. Journal of Turbomachinery, 2017, 139(2): 021009.
Denton J.D., Loss mechanisms in turbomachines. Journal of Turbomachinery, 1993, 115(4): 621–656.