跨声速多级压气机中的非定常流场频域分析

doi:10.7527/S1000-6893.2016.0012

流体力学与飞行力学

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跨声速多级压气机中的非定常流场频域分析

赵军¹, 刘宝杰²

1. 中国民航飞行学院航空工程学院, 广汉 618307;
2. 北京航空航天大学能源与动力工程学院, 北京 100083

收稿日期:2015-10-22 修回日期:2016-01-08 出版日期:2016-06-15 发布日期:2016-01-12
通讯作者: 刘宝杰男,博士,教授,博士生导师。主要研究方向:叶轮机械内气动热力学研究。Tel:010-82316419 E-mail:liubj@buaa.edu.cn E-mail:liubj@buaa.edu.cn
作者简介:赵军男,博士,高级工程师。主要研究方向:叶轮机械内复杂流动研究。Tel:0838-5182503 E-mail:491452660@qq.com
基金资助:
国家自然科学基金(51306201);四川省教育厅自然科学科研项目(16ZB0035);中国民用航空飞行学院科学研究基金(J2014-38,J2015-28)

Frequency-domain analysis of unsteady flow in multi-stage transonic compressor

ZHAO Jun¹, LIU Baojie²

1. Aviation Engineering Institute, Civil Aviation Flight University of China, Guanghan 618307, China;
2. School of Energy and Power Engineering, Beihang University, Beijing 100083, China

Received:2015-10-22 Revised:2016-01-08 Online:2016-06-15 Published:2016-01-12
Supported by:
National Natural Science Foundation of China (51306201);Natural Science Project of Sichuan Provincial Department of Education (16ZB0035);Science Research Foundation of Civil Aviation Flight University of China (J2014-38, J2015-28)

摘要/Abstract

摘要：

基于三维定常Denton程序发展了三维非定常计算程序,对三维跨声速多级压气机近失速点进行了定常与非定常数值模拟,并在此基础上对典型径向截面的非定常流场进行了频域分析。结果表明:通过对非定常频域图谱的研究,从一个全新的视角来分析非定常流场,可以看到一些在时域流场中很难直观看到的现象;轴向速度受尾迹的影响非常大,且在沿流向发展过程中,随着谐波阶次增加,幅值沿轴向的振荡幅度降低,幅值衰减的速度也加快;各叶排进口1阶谐波幅值在S3面内的分布受到下游叶排的势干扰,周向最大值点沿径向的走势与叶型的径向弯曲一致;气流密度、静压和总压受尾迹的影响较小,而气流静温、总温受尾迹的影响较大。

关键词: 航空发动机, 跨声速, 压气机, 非定常计算, 频域分析

Abstract:

Three-dimensional unsteady solver has been developed based on three-dimensional Denton steady solver. Steady and unsteady numerical simulation have been conducted on multi-stage transonic compressor near stall point,and then frequency-domain analysis of unsteady flow field have been conducted on some typical radial sections. Frequency-domain research makes us analyze the unsteady flow field from a new perspective, and we can see some of the phenomena that are difficult to see in the time domain. The effect of the wake on axial velocity is very large, and in the developing process along the flow, with the increase of harmonic order, axial oscillation amplitude reduces, and the attenuation speed of the amplitude is also accelerating. The distribution of the 1st harmonic amplitude in the S3 plane is disturbed by the potential interference of the downstream blade row, and the maximum value point in the circumferential direction along the radial direction shaped as the blade profile. The effect of the wake on flow density, static pressure and total pressure is small, while the air static temperature and total temperature are greatly affected by the wake.

Key words: aero-engine, transonic, compressor, unsteady calculation, frequency analysis

中图分类号:

V231.3

赵军, 刘宝杰. 跨声速多级压气机中的非定常流场频域分析[J]. 航空学报, 2016, 37(6): 1798-1808.

ZHAO Jun, LIU Baojie. Frequency-domain analysis of unsteady flow in multi-stage transonic compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(6): 1798-1808.

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E-mail：hkxb@buaa.edu.cn

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跨声速多级压气机中的非定常流场频域分析

Frequency-domain analysis of unsteady flow in multi-stage transonic compressor

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