| Citation: | WEI Wei, REN Siyuan, LI Xuechen, et al. Experimental method of varying static pressure ratio for a transonic compressor rotor cascade[J]. Journal of Aerospace Power, 2024, 39（11）：20240087 doi: 10.13224/j.cnki.jasp.20240087
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The study focused on addressing the experimental challenge of increasing the static pressure ratio for transonic compressor rotor cascades. To this end, various experimental methods were investigated, including altering the blade numbers of the cascade model and adjusting the back pressure in a variable density plane cascade wind tunnel. A calibration method was developed to estimate the Mach number of the flow field, by utilizing the predicted isentropic Mach number distributions of blade surfaces obtained from computational fluid dynamics (CFD). This method effectively guided the high static pressure ratio experiments conducted near the design point of the rotor cascade of the L030-4 compressor. The results demonstrated the success of the combined approach, involving the reduction of blade numbers and adjustment of back pressure in achieving the desired high static pressure ratio conditions with seven blades. Furthermore, the Mach number calibration method based on CFD facilitated the realization of high static pressure ratio experiments near the design point of the L030-4 compressor cascade. The obtained parameters, including total pressure loss, static pressure ratio, exit flow angle, and axial density velocity ratio of the cascade, were compared with the experimental data from foreign wind tunnel experiments. The relative deviations were all below 4%, validating the rationality of the calibration method.
| [1] |
刘永泉,刘太秋,季路成. 航空发动机风扇/压气机技术发展的若干问题与思考[J]. 航空学报,2015,36(8): 2563-2576. LIU Yongquan,LIU Taiqiu,JI Lucheng. Some problems and thoughts in the development of aero-engine fan/compressor[J]. Acta Aeronautica et Astronautica Sinica,2015,36(8): 2563-2576. (in Chinese
LIU Yongquan, LIU Taiqiu, JI Lucheng. Some problems and thoughts in the development of aero-engine fan/compressor[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(8): 2563-2576. (in Chinese)
|
| [2] |
张庆典,马宏伟,杨益,等. 平面叶栅气动试验研究进展与展望[J]. 力学学报,2022,54(7): 1755-1777. ZHANG Qingdian,MA Hongwei,YANG Yi,et al. Progress and prospect of aerodynamic experimental research on linear cascade[J]. Chinese Journal of Theoretical and Applied Mechanics,2022,54(7): 1755-1777. (in Chinese doi: 10.6052/0459-1879-21-684
ZHANG Qingdian, MA Hongwei, YANG Yi, et al. Progress and prospect of aerodynamic experimental research on linear cascade[J]. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(7): 1755-1777. (in Chinese) doi: 10.6052/0459-1879-21-684
|
| [3] |
LICHTFUSS H J,STARKEN H. Supersonic cascade flow[J]. Progress in Aerospace Sciences,1974,15: 37-149. doi: 10.1016/0376-0421(74)90004-9
|
| [4] |
LIU Baojie,SHI Hengtao,YU Xianjun. A new method for rapid shock loss evaluation and reduction for the optimization design of a supersonic compressor cascade[J]. Proceedings of the Institution of Mechanical Engineers,Part G: Journal of Aerospace Engineering,2018,232(13): 2458-2476. doi: 10.1177/0954410017715277
|
| [5] |
LICHTFUSS H J,STARKEN H. Supersonic exit flow of two-dimensional cascades[R]. ASME Paper 72-GT-49,1972.
|
| [6] |
TWEEDT D L,SCHREIBER H A,STARKEN H. Experimental investigation of the performance of a supersonic compressor cascade[J]. Journal of Turbomachinery,1988,110(4): 456-466. doi: 10.1115/1.3262219
|
| [7] |
SCHREIBER H A,STARKEN H. Experimental cascade analysis of a transonic compressor rotor blade section[J]. Journal of Engineering for Gas Turbines and Power,1984,106(2): 288-294. doi: 10.1115/1.3239561
|
| [8] |
FUCHS R,STARKEN H. Experimental investigations of supersonic cascades designed for high static pressure ratios[R]. ASME Paper 77-GT-37,1977.
|
| [9] |
SEROVY G K,OKIISHI T H. Performance of a compressor cascade configuration with supersonic entrance flow:a review and comparison of experiments in three installations[J]. Journal of Turbomachinery,1988,110(4): 441-449. doi: 10.1115/1.3262217
|
| [10] |
SCHREIBER H A,STARKEN H. An investigation of a strong shock-wave turbulent boundary layer interaction in a supersonic compressor cascade[R]. ASME Paper 91-GT-92,1991.
|
| [11] |
STEINERT W,FUCHS R,STARKEN H. Inlet flow angle determination of transonic compressor cascades[J]. Journal of Turbomachinery,1992,114(7): 487-493.
|
| [12] |
TIAN Simeng,PETRIE-REPAR P,GLODIC N,et al. CFD-aided design of a transonic aeroelastic compressor rig[J]. Journal of Turbomachinery,2019,141(10): 101003. doi: 10.1115/1.4043884
|
| [13] |
LOUDA P,PŘÍHODA J. Study on the numerical model of transonic wind tunnel test section[J]. Journal of Thermal Science,2021,30(1): 231-241. doi: 10.1007/s11630-020-1277-3
|
| [14] |
GAN Jiuliang,WATANABE T,HIMENO T. Effect of shock wave behavior on unsteady aerodynamic characteristics of oscillating transonic compressor cascade[R]. ASME Paper GT2021-59416,2021.
|
| [15] |
王宏娟,蔡可军,余申. 超声速压气机叶栅中激波、边界层相互作用的基本现象及被动式控制的研究[J]. 流体力学实验与测量,1997,11(2): 60-64. WANG Hongjuan,CAI Kejun,YU Shen. Some preliminary experimental results on passive control of shock wave boundary layer interaction in supersonic cascades[J]. Experiments and Measurements in Fluid Mechanics,1997,11(2): 60-64. (in Chinese
WANG Hongjuan, CAI Kejun, YU Shen. Some preliminary experimental results on passive control of shock wave boundary layer interaction in supersonic cascades[J]. Experiments and Measurements in Fluid Mechanics, 1997, 11(2): 60-64. (in Chinese)
|
| [16] |
兰发祥,周拜豪,梁德旺,等. 跨、超声速吸附式压气机平面叶栅试验[J]. 航空动力学报,2010,25(5): 1123-1128. LAN Faxiang,ZHOU Baihao,LIANG Dewang,et al. Experimental investigation of transonic and supersonic aspirated compressor cascades[J]. Journal of Aerospace Power,2010,25(5): 1123-1128. (in Chinese
LAN Faxiang, ZHOU Baihao, LIANG Dewang, et al. Experimental investigation of transonic and supersonic aspirated compressor cascades[J]. Journal of Aerospace Power, 2010, 25(5): 1123-1128. (in Chinese)
|
| [17] |
王松涛,胡应交. 基于超声速冲动式转子的下游静叶气动设计方法研究[J]. 推进技术,2013,34(8): 1035-1041. WANG Songtao,HU Yingjiao. Study of aerodynamic design method for downstream stator based on supersonic impulse rotors[J]. Journal of Propulsion Technology,2013,34(8): 1035-1041. (in Chinese
WANG Songtao, HU Yingjiao. Study of aerodynamic design method for downstream stator based on supersonic impulse rotors[J]. Journal of Propulsion Technology, 2013, 34(8): 1035-1041. (in Chinese)
|
| [18] |
王松涛,胡应交,王仲奇. 低反动度高负荷超声速轴流压气机气动设计方法[J]. 航空动力学报,2013,28(6): 1322-1332. WANG Songtao,HU Yingjiao,WANG Zhongqi. Aerodynamic design method of high loaded supersonic axial-compressor with low reaction[J]. Journal of Aerospace Power,2013,28(6): 1322-1332. (in Chinese
WANG Songtao, HU Yingjiao, WANG Zhongqi. Aerodynamic design method of high loaded supersonic axial-compressor with low reaction[J]. Journal of Aerospace Power, 2013, 28(6): 1322-1332. (in Chinese)
|
| [19] |
邱名. 高级压比轴流压气机转子通道内激波组织研究[D]. 南京: 南京航空航天大学,2014. QIU Ming. Investigation of shock organization in axial compressor passages of high pressure ratio[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2014. (in Chinese
QIU Ming. Investigation of shock organization in axial compressor passages of high pressure ratio[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2014. (in Chinese)
|
| [20] |
张疏影,周玲,季路成. 通道参数对超声速叶栅性能的影响[J]. 航空动力学报,2022,37(4): 836-847. ZHANG Shuying,ZHOU Ling,JI Lucheng. Effects of passage parameters on performance of supersonic cascade[J]. Journal of Aerospace Power,2022,37(4): 836-847. (in Chinese
ZHANG Shuying, ZHOU Ling, JI Lucheng. Effects of passage parameters on performance of supersonic cascade[J]. Journal of Aerospace Power, 2022, 37(4): 836-847. (in Chinese)
|
| [21] |
查戈成,严汝群. 超音速多圆弧(MCA)叶型叶珊的研究[J]. 航空动力学报,1987,2(2): 113-116,184-185. ZHA Gecheng,YAN Ruqun. Investigation of supersonic multiple circular arc (MCA) airfoil cascade of axial-flow compressor[J]. Journal of Aerospace Power,1987,2(2): 113-116,184-185. (in Chinese
ZHA Gecheng, YAN Ruqun. Investigation of supersonic multiple circular arc (MCA) airfoil cascade of axial-flow compressor[J]. Journal of Aerospace Power, 1987, 2(2): 113-116, 184-185. (in Chinese)
|
| [22] |
项林,马继华,陶德平. 超音速扩压叶栅激波结构与流动特征分析[J]. 燃气涡轮试验与研究,1999,12(1): 1-6. XIANG Lin,MA Jihua,TAO Deping. Analysis of shock wave structure and flow characteristics of supersonic compressor cascade[J]. Gas Turbine Experiment and Research,1999,12(1): 1-6. (in Chinese
XIANG Lin, MA Jihua, TAO Deping. Analysis of shock wave structure and flow characteristics of supersonic compressor cascade[J]. Gas Turbine Experiment and Research, 1999, 12(1): 1-6. (in Chinese)
|
| [23] |
邱名,陈逖,王子维,等. 超声速压气机叶栅研究进展[C]//第三届中国航空科学技术大会论文集. 北京: 中国航空学会,2017: 357-375.
|
| [24] |
江雄,邱名,范召林. 喉道对压气机超声叶栅流态及性能的影响[J]. 航空学报,2017,38(3): 120308. JIANG Xiong,QIU Ming,FAN Zhaolin. Effect of supersonic compressor cascade throat on flow pattern and cascade performance[J]. Acta Aeronautica et Astronautica Sinica,2017,38(3): 120308. (in Chinese
JIANG Xiong, QIU Ming, FAN Zhaolin. Effect of supersonic compressor cascade throat on flow pattern and cascade performance[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(3): 120308. (in Chinese)
|
| [25] |
郝颜,邱名,江雄,等. 进口预旋对预压缩叶栅性能影响研究[J]. 推进技术,2017,38(12): 2725-2733. HAO Yan,QIU Ming,JIANG Xiong,et al. Investgation of inlet pre-swirl influence on performance in precompression cascade[J]. Journal of Propulsion Technology,2017,38(12): 2725-2733. (in Chinese
HAO Yan, QIU Ming, JIANG Xiong, et al. Investgation of inlet pre-swirl influence on performance in precompression cascade[J]. Journal of Propulsion Technology, 2017, 38(12): 2725-2733. (in Chinese)
|
| [26] |
李清华,曹志远,胡骏. 端壁吸/吹气对超声速压气机叶栅流场影响机理的对比研究[J]. 推进技术,2019,40(9): 1991-2002. LI Qinghua,CAO Zhiyuan,HU Jun. Comparison between effects of endwall suction and air injection on flow field of a supersonic compressor cascade[J]. Journal of Propulsion Technology,2019,40(9): 1991-2002. (in Chinese
LI Qinghua, CAO Zhiyuan, HU Jun. Comparison between effects of endwall suction and air injection on flow field of a supersonic compressor cascade[J]. Journal of Propulsion Technology, 2019, 40(9): 1991-2002. (in Chinese)
|
| [27] |
刘永振,徐强仁,马英群,等. 超声速压气机叶栅前缘通道激波损失的鼓包控制研究[J]. 航空动力学报,2019,34(10): 2294-2304. LIU Yongzhen,XU Qiangren,MA Yingqun,et al. Investigation on the first passage shock loss with bump control inside a supersonic compressor cascade[J]. Journal of Aerospace Power,2019,34(10): 2294-2304. (in Chinese
LIU Yongzhen, XU Qiangren, MA Yingqun, et al. Investigation on the first passage shock loss with bump control inside a supersonic compressor cascade[J]. Journal of Aerospace Power, 2019, 34(10): 2294-2304. (in Chinese)
|
| [28] |
盛佳明,张海灯,吴云,等. 电弧放电等离子体激励控制超声速压气机叶栅激波/边界层干扰仿真研究[J]. 推进技术,2020,41(10): 2228-2236. SHENG Jiaming,ZHANG Haideng,WU Yun,et al. Simulation study of arc discharge plasma actuator for supersonic compressor cascade shock wave/boundary layer interaction control[J]. Journal of Propulsion Technology,2020,41(10): 2228-2236. (in Chinese
SHENG Jiaming, ZHANG Haideng, WU Yun, et al. Simulation study of arc discharge plasma actuator for supersonic compressor cascade shock wave/boundary layer interaction control[J]. Journal of Propulsion Technology, 2020, 41(10): 2228-2236. (in Chinese)
|
| [29] |
陈为雄,王掩刚,马峰,等. 超声速来流基元叶型前缘加工误差气动敏感性分析[J]. 推进技术,2019,40(10): 2235-2242. CHEN Weixiong,WANG Yangang,MA Feng,et al. Aerodynamic sensitivity analysis of manufacturing errors for leading edge of supersonic elementary blade profile[J]. Journal of Propulsion Technology,2019,40(10): 2235-2242. (in Chinese
CHEN Weixiong, WANG Yangang, MA Feng, et al. Aerodynamic sensitivity analysis of manufacturing errors for leading edge of supersonic elementary blade profile[J]. Journal of Propulsion Technology, 2019, 40(10): 2235-2242. (in Chinese)
|
| [30] |
陈卓远,耿少娟,刘帅鹏,等. 轮廓度误差对超声速压气机叶栅气动性能的影响[J]. 中国舰船研究,2024,19(2): 197-206. CHEN Zhuoyuan,GENG Shaojuan,LIU Shuaipeng,et al. Effects of profile variability on aerodynamic performance of supersonic compressor cascade[J]. Chinese Journal of Ship Research,2024,19(2): 197-206. (in Chinese
CHEN Zhuoyuan, GENG Shaojuan, LIU Shuaipeng, et al. Effects of profile variability on aerodynamic performance of supersonic compressor cascade[J]. Chinese Journal of Ship Research, 2024, 19(2): 197-206. (in Chinese)
|
| [31] |
FROST G R,HEARSEY R M,WENNERSTROM A J. A computer program for the specification of axial compressor airfoils[R]. Springfield,US: Aerospace Research Laboratories ARL 72-0171,1972.
|
| [32] |
魏巍,马护生,周晓刚,等. 变密度平面叶栅风洞的设计与实现[J]. 实验流体力学,2022,36(5): 24-33. WEI Wei,MA Husheng,ZHOU Xiaogang,et al. Design and actualization of the variable density plane cascade wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2022,36(5): 24-33. (in Chinese doi: 10.11729/syltlx20210175
WEI Wei, MA Husheng, ZHOU Xiaogang, et al. Design and actualization of the variable density plane cascade wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022, 36(5): 24-33. (in Chinese) doi: 10.11729/syltlx20210175
|
| [33] |
中国航空工业第一集团公司. 超跨音速平面叶栅试验方法: HB 20145-2014 [S]. 北京: 国家国防科技工业局,2014: 1-14.
|
| [34] |
NING Fangfei. MAP: a CFD package for turbomachinery flow simulation and aerodynamic design optimization[R]. ASME Paper GT2014-26515,2014.
|
| [35] |
EDWARDS J R. A low-diffusion flux-splitting scheme for Navier-Stokes calculations[J]. Computers & Fluids,1997,26(6): 635-659.
|
| [36] |
杜磊,宁方飞. 基于S-A湍流模型和间歇因子输运方程的转捩流数值模拟[J]. 航空动力学报,2015,30(10): 2450-2461. DU Lei,NING Fangfei. Numerical simulation of transition flows based on S-a turbulence model and intermittency transport equation[J]. Journal of Aerospace Power,2015,30(10): 2450-2461. (in Chinese
DU Lei, NING Fangfei. Numerical simulation of transition flows based on S-a turbulence model and intermittency transport equation[J]. Journal of Aerospace Power, 2015, 30(10): 2450-2461. (in Chinese)
|
| [37] |
ZHANG Shuying,ZHOU Ling,JI Lucheng. Investigation of hysteresis loop in the starting process of supersonic cascade[J]. AIAA Journal,2022,60(4): 2685-2693. doi: 10.2514/1.J061232
|
| [38] |
KIOCK R,LEHTHAUS F,BAINES N C,et al. The transonic flow through a plane turbine cascade as measured in four European wind tunnels[J]. Journal of Engineering for Gas Turbines and Power,1986,108(2): 277-284. doi: 10.1115/1.3239900
|
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