Prediction method of stall margin in axial-flow transonic compressor
-
摘要: 研究了跨声速、单级设计压比为1.82的Stage 35轴流压气机与单级设计压比为2.05的Stage 37轴流压气机在不同转速下的特性.在HARIKA原型程序基础上,改进了其叶排效率、落后角、理论能头计算模型,采用了两种轴流压气机失速边界的预测方法,第1种为HARIKA原型程序的分离流量预测方法,第2种为Koch所提出的失速静压升系数预测方法,所得特性计算结果与实验点吻合较好,Stage 35设计点效率的误差由原型的3.9%降低到改进后的1.5%,Stage 37设计点效率的误差由3.1%降低到1.9%.两种预测方法对失速边界流量的预测误差最小分别可达1.3%与1.6%,表明两种失速边界预测方法都是可行的.Abstract: Performance of single stage axial-flow transonic compressor Stage 35 of design pressure ratio 1.82 and Stage 37 of design pressure ratio 2.05 at different rotation speeds was presented. Based on the HARIKA program, three models for respectively predicting cascade efficiency, deviation angle and head rise were improved. Two methods for predicting stall margin of axial-flow compressors were used. The first one was separation mass flow prediction method in HARIKA program. The second one was stalling static pressure rise coefficient prediction method proposed by Koch. Good agreement was achieved between the computation results and experiment data. The efficiency error of Stage 35 at design point decreases from 3.9% to 1.5%. The efficiency error of Stage 37 decreases from 3.1% to 1.9%. The minimum error of mass flow of stall margin predicted by two methods is 1.3% and 1.6% respectively. The result indicates that two methods used to predict stall margin are feasible.
-
[1] Koch C C.Stalling pressure rise capability of axial flow compressor stages[J].Journal of Engineering for Power,1981,103(4):645-656. [2] Smith L H,Jr.Axial compressor aerodesign evolution at general electric[J].Journal of Turbomachinery,2002,124(3):321-330. [3] Farokhi S.Aircraft propulsion[M].Lawrence,US:University of Kansas Press,2007. [4] Cumpsty N A.Compressor aerodynamics[M].London:University of Cambridge Press,1989. [5] Falck N.Axial flow compressor mean line design[D].Lund,Sweden:Lund University,2008. [6] 胡俊.均匀与非均匀进气条件下多级轴流压气机性能计算:均匀进气及径向畸变的影响[J].航空动力学报,2000,15(3):225-228. HU Jun.Calculation of off-design performance of multistage compressors with uniform and radial distorted inlet flow[J].Journal of Aerospace Power,2000,15(3):225-228.(in Chinese) [7] 吴艳辉,朱俊强,刘志伟.多级轴流压气机机匣处理级的探讨[J].航空动力学报,2002,17(5):542-548. WU Yanhui,ZHU Junqiang,LIU Zhiwei.Research on the axial position of treated casing in multistage axial-flow compressors[J].Journal of Aerospace Power,2002,17(5):542-548.(in Chinese) [8] 王英锋,胡骏.雷诺数对轴流压气机稳定性的影响[J].航空动力学报,2004,19(1):69-73. WANG Yingfeng,HU Jun.The effects of Reynolds number on the stability of axial compressors[J].Journal of Aerospace Power,2004,19(1):69-73.(in Chinese) [9] 王英锋,胡骏.雷诺数对轴流风扇/压气机性能和稳定性的影响[J].南京航空航天大学学报,2004,36(2):145-149. WANG Yingfeng,HU Jun.Effects of Reynolds number on performance and stability of axial fans/compressors[J].Journal of Nanjing University of Aeronautics and Astronautics,2004,36(2):145-149.(in Chinese) [10] 楚武利,王毅,杨泳.多级轴流压气机率先失速级的预测方法研究[J].流体机械,2005,33(10):11-14. CHU Wuli,WANG Yi,YANG Yong.Prediction method investigation of rotating stall stage in multi-stage axial flow compressor[J].Fluid Machinery,2005,33(10):11-14.(in Chinese) [11] 赵勇,胡骏,屠宝锋,等.多级轴流风扇/压气机非设计点性能计算方法[J].推进技术,2008,29(2):219-224. ZHAO Yong,HU Jun,TU Baofeng,et al.Calculation of multistage axial fan/compressor off-design performance[J].Journal of Propulsion Technology,2008,29(2):219-224.(in Chinese) [12] Veres J P.Axial and centrifugal compressor mean line flow analysis method[R].AIAA-2009-1641,2009. [13] Koch C C,Smith L H.Loss sources and magnitudes in axial-flow compressors[J].Journal of Engineering for Power,1976,98(3):411-424. [14] Boyer K M,O'Brien W F.An improved streamline curvature approach for off-design analysis of transonic axial compression systems[J].Journal of Turbomachinery,2003,125(3):475-481. [15] 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[R].NASA TP-1338,1978. [16] Moore R D,Reid L.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 2.05 .NASA TP-1659,1980. [17] Davis R L,Yao J.Prediction of compressor stage performance from choke through stall[R].AIAA-2005-1005,2005. [18] Davis R L,Yao K.Computational approach for predicting stall inception in multistage axial compressors[J].Journal of Propulsion and Power,2007,23(2):257-265.
点击查看大图
计量
- 文章访问数: 1839
- HTML浏览量: 4
- PDF量: 944
- 被引次数: 0