Bleeding impact on performance of transonic axial compressor

[1] 杨燕生,吴向宇,陆海鹰,等.航空发动机设计手册,第16分册:空气系统及传热分析[M].北京:航空工业出版社,2001:1-11 Yang Yansheng,Wu Xiangyu,Lu Haiying,et al.Design manual of aircraft engine,16th volumes: air systems and analysis of heat transfer[M].Beijing: Aviation Industry Press,2001:1-11(in Chinese) [2] Andrew J Y,Ronald J R.Effects of bleed air extraction on thrust level of the F404-GE-400 turbofan engine .NASA TM-104247,1992 [3] Alison B E.The effects of compressor seventh-stage bleed air extraction on performance of the F100-PW-220 afterburning turbofan engine .NASA CR-179447,1991 [4] 赵斌,李绍斌,侯安平,等.发动机空气系统气源引气的研究和探讨 // 航空学会第十五届叶轮机专业委员会学术交流会文集.张家界:中国航空学会动力专业分会,2009:190-198 Zhao Bin,Li Shaobin,Hou Anping,et al.The research on air bleed of air system in aero-engine // Academic Exchanging Meeting of 15th Turbomachinery Committee of Aviation Institute,Zhangjiajie:CSAA,2009:190-198(in Chinese) [5] Wellborn S R,Michael L K.Bleed flow interactions with an axial-flow compressor powerstream .AIAA Paper 2002-4057,2002 [6] Leishman B A,Cumpsty N A,Denton J D.Effects of bleed rate and endwall location on the aerodynamic behavior of a circular hole bleed off-take[J].ASME Journal of Turbomachinery,2007,129(4):645-658 [7] Leishman B A,Cumpsty N A,Denton J D.Effects of inlet ramp surfaces on the aerodynamic behavior of bleed hole and bleed slot off-take configurations[J].ASME Journal of Turbomachinery,2007,129(4): 659-668 [8] Leishman B A,Cumpsty N A.Mechanism of the interaction of a ramped bleed slot with the primary flow[J].ASME Journal of Turbomachinery,2007,129(4): 669-678 [9] Gummer V,Goller M,Swoboda M.Numerical investigation of end wall boundary layer removal on highly loaded axial compressor blade rows[J].Journal of Turbomachinery,2008,130(1):011015.1-011015.9 [10] Dobrzynski B,Saathoff H,Kosyna G,et al.Active flow control in a single-stage axial compressor using tip injection and endwall boundary layer removal .ASME GT2008-50214,2008 [11] 张皓光,楚武利,吴艳辉,等.轴向间隙引气对双级轴流式压气机性能及流场影响的数值研究[J].流体机械,2006,34(7):24-27 Zhang Haoguang,Chu Wuli,Wu Yanhui,et al.Numerical investigation on the effect of axial clearance bleeding on a tow-stage axial-flow compressor flow-field and performance[J].Journal of Fluid Machinery,2006,34(7):24-27(in Chinese) [12] Vo H D,Tan C S,Greitzer E M.Criteria for spike initiated rotating stall .ASME GT2005-68374,2005 [13] Hah C,Bergner J,Schiffer H.Short length-scale rotating stall inception in a transonic axial compressor-criteria and mechanism .ASME GT2006-90045,2006 [14] Adamczyk J J,Celestina M L,Greitzer E M.The role of tip clearance in high-speed fan stall[J].ASME Journal of Turbomachinery,1993,115(1): 28-38 [15] Joslyn H D,Dring R P.Axial compressor stator aerodynamics[J].ASME Journal of Heat Transfer,1985,107(2): 485-493 [16] Kang S,Hirsch C.Three dimensional flow in a linear compressor cascade at design condition .ASME 91-GT-114,1991 [17] Prandlt L.Essentials of fluid dynamics[M].New York:Hafner Publishing Company,1952 [18] Reid L,Moore R D.Design and overall performance of four highly loaded,high-speed inlet stages for an advanced high-pressure-ratio core compressor .NASA TP-1337,1978 [19] Reid L,Moore R D.Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26,respectively,and with design pressure ratio of 1.82 .NASA TP-1338,1978