跨声速轴流压气机非轴对称端壁造型优化设计

推进技术 ›› 2012, Vol. 33 ›› Issue (5): 689-694.

跨声速轴流压气机非轴对称端壁造型优化设计

刘波,曹志远,黄建,赵鹏程

西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072

发布日期:2021-08-15
作者简介:刘波(1960—),男,博士,教授,博士生导师,研究领域为先进叶轮机械设计与实验技术。E-mail:liubo704@nwpu.edu.cn
基金资助:
国家自然科学基金(50976093)。

Design Optimization for a Transonic Compressor with Implementation of Non-axisymmetric Endwall Contouring

School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072,China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072,China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072,China;School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072,China

Published:2021-08-15

摘要/Abstract

摘要： 为探索非轴对称端壁提高跨声速轴流压气机性能的潜力,基于三维数值模拟优化平台,针对跨声速轴流压气机转子进行了非轴对称轮毂优化造型,深入分析了非轴对称轮毂造型对跨声速压气机流场结构及性能的影响机理。结果表明:优化造型后的非轴对称轮毂同时提高了该跨声速压气机的效率和压比,最高效率点效率提高0.31%,压比提高0.31%,并改善了压气机的变工况性能。 

关键词: 非轴对称端壁;轮毂;优化设计;跨声速压气机 

Abstract: In order to explore whether non-axisymmetric end wall can effectively improve the performance of transonic compressor, a transonic compressor rotor was optimized with the implementation of non-axisymmetric hub endwall contouring by three dimension numerical simulation optimization platform. And this paper described how the compressor flow field was influenced by the non-axisymmetric endwall. The investigation reveals that the non-axisymmetric hub endwall can improve both the efficiency and pressure ratio of the transonic compressor. At the highest efficiency condition, the efficiency increases by 0.31% and the pressure ratio increases by 0.31%. The off-design performance of the compressor is improved.

Key words: Non-axisymmetric endwall；Hub；Optimization design；Transonic compressor

刘波,曹志远,黄建,赵鹏程. 跨声速轴流压气机非轴对称端壁造型优化设计[J]. 推进技术, 2012, 33(5): 689-694.

参考文献

[2] Brennan G, Harvey N W,Rose M G, et al.Improving the Efficiency of the Trent 500-HP Turbine Using Nonaxisymmetric End Walls[J].Journal of Turbomachinery, 3,5(3):497-504.
[3] Harvey N W, Brennan G,Newman D A, et al.Improving Turbine Efficiency Using Non-Axisymmetirc End Walls:Validation in the Multi-Row Environment and with Low Aspect Ratio Blading[R].ASME 2002-GT-30337.
[4] Knezevici D C, Sijolander S A, Praisner T J, et al.Measurements of Secondary Losses in a High-Lift Front-Loaded Turbine Cascade with the Implementation of Non-Axisymmetric Endwall Contouring[R].ASME 2009-GT-59677.
[5] Glen Snedden, Dwain Dunn, Grant Ingram, et al.The Application of Non-Axisymmetric Endwall Contouring in a Single Stage, Rotating Turbine[R].ASME 2009-GT-59169.
[6] 刘波,管继伟,陈云永,等.用端壁造型减小涡轮叶栅二次流损失的数值研究[J].推进技术,2008,29(3):355-359.(LIU Bo, GUAN Ji-wei, CHEN Yun-yong, et al.Numerical Investigation for Effect of Non-Axisymmetric Endwall Profiling on Secondary Flow in Turbine Cascade[J].Journal of Propulsion Technology, 8,9(3):355-359.)
[7] 李国君,马晓永,李军.非轴对称端壁成型及其对叶栅损失影响的数值研究[J].西安交通大学学报,2005,39(11):1169-1172.
[8] 郑金,李国君,贾海东,等.变工况下非轴对称端壁环形叶栅流场特性实验[J].航空动力学报,2008,23(12):2308-2313.
[9] 汪传美,李国君,郑金,等.非轴对称端壁成型技术的实验研究[J].西安交通大学学报,2008,42(9):1086-1190.
[10] 高增珣,高学林,袁新.透平叶栅非轴对称端壁的气动最优化设计[J].工程热物理学报,2007,28(4):589-591.
[11] 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[R].NASA-TP-7,8.
[12] 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-8,8.