Manufacturing variabilities of high-pressure compressor blades can hardly be avoided in aero-engines, which may seriously affect the aerodynamic performance of the compressors. To analyze the sensitivity of manufacturing variabilities on compressor performance, the rear stage of a high-pressure compressor is used to make the numerical simulation. Firstly, several typical manufacturing variabilities such as positional tolerance, profile tolerance and twisted tolerance are chosen and Gaussian distribution probability density function is used to determine the distribution of tolerance. Then the effective law of manufacturing variabilities to compressor's performance such as isentropic efficiency and total pressure ratio are investigated through numerical simulation, and the sensitivity parameters are extracted. The results indicate that when the position of blade changes, aerodynamic performance of high-pressure compressor are always reduced, for example, the axial position makes the surge margin decrease almost 25%, while profile and twisted tolerance can lead to negative linear variation; throughout these three variabilities, the sensitivity of performance to the blade twist and axial position are larger, while circular position and profile tolerance have minor effects.
[1] 李晓丽,楚武利. 安装角变化对多级轴流压缩机性能影响的分析[J]. 风机技术,2008(5):27-29. LI Xiaoli,CHU Wuli. Analysis on the influence of variable installation angle on performance of multi-stage axial-flow compressor[J]. Compressor,Blower and Fan Technology,2008(5):27-29.
[2] LANGE A,VOIGT M,VOGELER K,et al. Impact of manufacturing variability on multistage high-pressure compressor performance[J]. Journal of Engineering for Gas Turbines and Power,2012,134(11):417-426.
[3] LANGE A,VOIGT M,VOGELER K,et al. Probabilistic CFD simulation of a high-pressure compressor stage taking manufacturing variability into account[C]//American Society of Mechanical Engineers. Proceedings of ASME Turbo Expo 2010,Power for Land,Sea,and Air,June 14-18,2010,Glasgow,Brussels UK. ASME,2010:617-628.
[4] MARX J,STÄDING J,REITZ G,et al. Investigation and analysis of deterioration in high pressure compressors due to operation[J]. CEAS Aeronautical Journal,2014,5(4):515-525.
[5] LEBELE-ALAWA B T,HART H I,OGAJI S O T,et al. Rotor-blades' profile influence on a gas-turbine's compressor effectiveness[J]. Applied Energy,2008(85):494-505.
[6] ROBERTS W B,ARMIN A,KASSASEYA G,et al. The effect of variable chord length on transonic axial rotor performance[J]. Journal of Turbomachinery,2002,124(3):351-357.
[7] SCHNELL R,KAMPMANN T L,NICKE E. On the impact of geometric variability on fan aerodynamic performance,unsteady blade row interaction,and its mechanical characteristics[J]. Journal of Turbomachinery,2014,136(9):091005.
[8] GIEBMANNS A,SCHNELL R,STEINERT W,et al. Analyzing and optimizing geometrically degraded transonic fan blades by means of 2D and 3D simulations and cascade measurements[C]//American Society of Mechanical Engineers. Proceedings of ASME Turbo Expo 2012. Copenhagen:ASME,2012:279-288.
[9] 王松,王国辉,韩青,等. 叶片积垢对压气机性能衰退的影响[J]. 哈尔滨工程大学学报,2014,35(12):1524-1528. WANG Song,WANG Guohui,HAN Qing,et al. Compressor performance deterioration caused by blade fouling[J]. Journal of Harbin Engineering University,2014,35(12):1524-1528.
[10] 李钊,王永华,黄帅,等. 积垢对压气机流场影响的数值分析[J]. 海军航空工程学院学报,2011,26(6):637-644. LI Zhao,WANG Yonghua,HUANG Shuai,et al. Numerical analysis of the effect of fouling on compressor flow field[J]. Journal of Naval Aeronautical and Astronautical University,2011,26(6):637-644.
[11] ELMSTROM M E,MILLSAPS K T,HOBSON G V,et al. Impact of nonuniform leading edge coatings on the aerodynamic performance of compressor airfoils[J]. Journal of Turbomachinery,2011,133(4):041004.
[12] 张伟昊,邹正平,刘火星,等. 叶型偏差对整机环境中涡轮性能的影响[J]. 工程热物理学报,2010,31(11):1830-1834. ZHANG Weihao,ZOU Zhengping,LIU Huoxing,et al. Effects of profile deviation on turbine performance in whole engine environment[J]. Journal of Engineering Thermophysics,2010,31(11):1830-1834.
[13] BENINI E,BIOLLO R. Aerodynamics of swept and leaned transonic compressor-rotors[J]. Applied Energy,2007,84(10):1012-1027.
[14] 陈浮,赵桂杰,宋彦萍,等. 叶片弯、掠对压气机端壁流动的影响[J]. 工程热物理学报,2004,25(2):211-215. CHEN Fu,ZHAO Guijie,SONG Yanping,et al. Influences of swept and curved blade on the flow near compressor cascade endwall[J]. Journal of Engineering Thermophysics,2004,25(2):211-215.
[15] 冯秀莲,金东海,桂幸民. 叶片弯掠对压气机静子叶片气动性能影响的三维数值模拟[J]. 航空动力学报,2009,24(10):2338-2343. FENG Xiulian,JIN Donghai,GUI Xingmin. Numerical Simulation of the aerodynamics performance of swept and curved blade on the compressor stator[J]. Journal of Aerospace Power,2009,24(10):2338-2343.
[16] FATHI A,ALIZADEH M. Effects of blade manufacturing deviations on turbine performance[C]//American Society of Mechanical Engineers. Proceedings of the ASME 2012 Gas Turbine India Conference,December 1,2012,Mumbai,Maharashtra,India. Gurgaon:ASME,2012:203-211.
[17] WUNSCH D,HIRSCH C,NIGRO R,et al. Quantification of combined operational and geometrical uncertainties in turbo-machinery design[C]//American Society of Mechanical Engineers. Proceedings of ASME Turbo Expo 2015,Turbine Technical Conference and Exposition,June 15-19,2015,Montreal,Canada. New York:ASME,2015:18-28.
[18] DENTON J D. Some limitation of turbomachinery CFD[C]//American Society of Mechanical Engineers. Proceedings of ASME Turbo Expo 2010,Power for Land Sea and Air,June 14-18,2010,Glasgow,UK. Brussels:ASME,2010:735-745.
