Inducer tip endwall bleeding effects on centrifugal compressor stability enhancement
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摘要: 对一台在导风轮叶顶设置有自循环机匣处理的离心压气机,借鉴其试验结果制定了3种引气位置A,B和C,并结合不同的引气量进行了端壁引气扩稳的数值研究.计算结果表明:引气位置和引气范围对扩稳效果有重要影响,引气位置C覆盖了整个叶尖回流区,引气面积最大,扩稳效果最好.随引气量的变化,出现了两种不同的扩稳机理:小引气量可以吸除叶尖泄漏流,缓解通道阻塞,延缓端壁失速;过大的引气量则挤占有效流通面积,将通流区域压向轮毂侧,增加了叶轮的做功能力.兼顾压气机的效率考虑,小引气量具有优势,引气位置C用5%引气量可以获得19.6%的裕度提升.Abstract: Numerical simulation was carried out to explore the benefit of inducer tip endwall bleeding effects on centrifugal compressor stability enhancement. Based on the experimental results of the centrifugal compressor with a self-recirculating casing treatment on top of inducer, three tip bleeding configurations (A, B and C) with different bleed rates were simulated. The result shows that bleed position and bleed range have grate influence on stability enhancement effect. Configurations C is the best location because it has the largest bleeding area covers the whole tip backflow zone. Additionally, with the variation of suction flow rate, there are two different mechanisms of stability extension.When the flow rate is low, bleeding can suppress the tip leakage flow and remove low momentum fluid, so the channel blocking will be reduced to delay endwall stall. Otherwise, larger rate of suction flow will occupy the channel and the main flow will be pushed towards hub side to improve the rim power of the rotor. Considering the compression efficiency, lower bleeding rate has advantages. For configuration C, 5% is the optimum bleed rate with the margin increase by 19.6%.
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Key words:
- inducer /
- endwall bleeding /
- casing treatment /
- total pressure ratio /
- efficiency /
- stall margin
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[1] 刘大响,叶陪梁,胡俊,等.航空燃气涡轮发动机稳定性设计与评定技术[M].北京:航空工业出版社,2004. [2] Greitzer E M.Review-axial compressor stall phenomena[J].ASME Journal of Fluids Engineering,1980,102(2):134-150. [3] Kerrcbrock J L,Reijnan C P,Ziminsky W S,et al.Aspirated compressors[R].ASME Paper GT-97-525,1997. [4] Chapman D C.Model 250-C30/C281 compressor development[C]//AGAED Conference Proceedings:Centrifugal Compressors,Flow Phenomenon,and Performance.Neuilly Surseine,FR:Advisory Group for Aerospace Research and Development,1980:201-206. [5] General Motors Corporation.Dual function compressor bleed:United States,US4248566[P].1981-02-03. [6] 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. [7] 赵斌,李绍斌,周盛.引气对跨声轴流压气机性能的影响[J].北京航空航天大学学报,2011,37(1):15-20. ZHAO Bin,LI Shaobin,ZHOU Sheng.Bleeding impact on performance of transonic axial compressor[J].Journal of Beijing University of Aeronautics and Astronautics,2011,37(1):15-20.(in Chinese) [8] 王掩刚,牛楠,赵龙波,等.端壁抽吸位置对压气机叶栅角区分离控制的影响[J].推进技术,2010,31(4):433-437. WANG Yangang,NIU Nan,ZHAO Longbo,et al.Effect on corner separation control for high load compressor cascade with different end-wall BLS position[J].Journal of Propulsion Technology,2010,31(4):433-437.(in Chinese) [9] 周敏,李航航,唐侃平.低雷诺数下附面层组合抽吸方案对压气机特性影响的研究[J].应用力学学报,2012,29(1):27-31. ZHOU Min,LI Hanghang,TANG Kanping.Combined boundary layer suction effect on compressor characters at low Reynolds number[J].Chinese Journal of Applied Mechanics,2012,29(1):27-31.(in Chinese) [10] Palmer D L,Waterman W F.Design and development of an advanced two-stage centrifugal compressor[J].ASME Journal of Turbomachinery,1995,117(3):205-212. [11] Pratt & Whitney Canada Corp.Mixed flow and centrifugal compressor for gas turbine engine:United States,US6488469 B1[P].2002-12-03. [12] 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[R].ASME Paper GT2008-50214,2008. [13] DENG Xiangyang,Elizabeth A L,FENG Jinzhang.Time-accurate calculations of a passive shroud bleed configuration and implications for unsteady blade loading[R].ASME Paper GT2011-45777,2011. [14] WANG Tong,XU Wei,GU Chuangang,et al.A new type of self-adaptive casing treatment for a centrifugal compressor[R].ASME Paper GT2010-23457,2010. [15] 戴四敏.导风轮轮罩引气对离心式压气机性能影响的数值研究[J].航空动力学报,2005,20(1):125-129. DAI Simin.Numeric simulation of inducer shroud bleeding effect on centrifugal compressor performance[J].Journal of Aerospace Power,2005,20(1):125-129.(in Chinese) [16] 康剑雄.75kW燃气轮机离心叶轮改进设计及试验研究[D].上海:上海交通大学,2008. KANG Jianxiong.Improved design and experimental investigation for the centrifugal impeller of a 75kW gas turbine engine[D].Shanghai:Shanghai Jiaotong University,2008.(in Chinese) [17] 石建成,邹学奇,温泉,等.离心压气机流动控制机匣新型处理方式研究[J].航空发动机,2010,36(3):1-4. SHI Jiancheng,ZOU Xueqi,WEN Quan,et al.Study on new type casing treatment method for centrifugal compressor[J].Aeroengine,2010,36(3):1-4.(in Chinese) [18] 杨策,施新.径流式叶轮机械理论及设计[M].北京:国防工业出版社,2004. [19] Dunham J.Mechanical engineering science monograph[M].London:Institution of Mechanical Engineers,1965. [20] Schuler B J,Kerrebrock J L,Merchant A A,et al.Design,analysis,fabrication and test of an aspirated fan stage[R].ASME Paper GT2000-618,2000. [21] Kerrebrock J L.The prospects for aspirated compressors[R].AIAA 2000-2472,2000. [22] 任铭林,向宏辉.有关轴流压气机效率问题的探讨[J].燃气涡轮试验与研究,2009,22(4):9-14. REN Minglin,XIANG Honghui.Exploration of efficiency in axial compressor[J].Gas Turbine Experiment and Research,2009,22(4):9-14.(in Chinese)
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