［1］ VUNNAM K, HOOVER R. Modeling of inlet distortion using a combined turbofan and nacelle inlet model during crosswind and low speed forward operation［C］// ASME Proceedings. Vancouver, British Columbia, Canada: International Gas Turbine Institute, 2011, 1: 371-380.
[2]
［2］ SUN Peng, GAO Hai-yang, ZHONG Jing-jun, et al. Study on the influence of total pressure distortion on end wall flow field in a supersonic compressor［C］// ASME Proceedings . San Antonio, Texas, USA: International Gas Turbine Institute, 2013, 6C: V06CT42A017.
[3]
［3］ ROSE M G. Nonaxisymmetric endwall profiling in the HP NGVs of an axial flow gas turbine［R］.ASME 1994:94-GT-249.
[4]
［4］ HOEGER M, CARDAMONE P. FOTTNER L. Influence of endwall contouring on the transonic flow in a compressor vane［R］. ASME Paper, 2002 : GT-2002-30440.
[5]
［5］ HARVEY N W. Some effects of nonaxisymmetric endwall profiling on axial flow compressor aero dynamics Part I:linear cascade investigation［R］.ASME Paper, 2008 :GT200850990.
LI Guo-jun. MA Xiao-yong. LI Jun. Non-axisymmetric turbine end wall profiling and numerical investigation of its effect on the turbine cascade loss［J］. Journal of Xi’an Jiaotong University, 2005,39(11): 9-12 (in Chinese).
SUN Ping. GAO Xiang. LI Chuan-peng. Influence of nonaxisymmetric endwall contour on compressor performance and fluid dynamics［J］. Science and Technology Innovation Herald, 2012 (25): 85-87. (in Chinese)
ZHAO Yang-zheng. LIU Qian-zhi. LIAO Ming-fu. Effects of uneven blade spacing on unsteady blade forcing in an axial compressor［J］. Journal of Propulsion Technology, 2007, 28（2）：167-169. (in Chinese)
BAI Zhi-gang. LIU Qian-zhi. Numerical study of the effects of uneven blade spacing on the flow in an axial compressor［J］. Advances in Aeronautical Science and Engineering. 2010, 1（1）：90-94. (in Chinese)
SUN Peng. All annulus numerical simulation of total pressure distortion effect in a transonic fan［D］.Harbin：Harbin Institute of Technology,2007. （in Chinese）
[16]
［11］ SUN Peng, ZHONG Jing-jun, YANG Mu-xiao, et al. Effects of bowed stator on a fan characteristic with distorted inlet［C］// ASME Proceedings. Glasgow, UK: International Gas Turbine Institute,2010, 7: 2585-2591.
ZHANG Jing-xuan. The unsteady mechanism and the role of tip clearance flow in distortion induced instability in an axial compressor［D］. Beijing: Graduate School of the Chinese Academy of Sciences，2007. (in Chinese)
