基于特征值理论的轴流跨声速压气机失稳预测

doi:10.7527/S1000-6893.2013.0499

流体力学与飞行力学

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基于特征值理论的轴流跨声速压气机失稳预测

刘小华^1,2, 周燕佩¹, 孙大坤², 马云飞², 孙晓峰²

1. 中国民航科学技术研究院发动机适航审定中心筹建办公室, 北京 100028;
2. 北京航空航天大学能源与动力工程学院, 北京 100191

收稿日期:2013-11-08 修回日期:2013-12-19 出版日期:2014-11-25 发布日期:2013-12-23
通讯作者: 孙晓峰,Tel.: 010-82317408 E-mail: sunxf@buaa.edu.cn E-mail:sunxf@buaa.edu.cn
作者简介:刘小华男, 博士, 工程师.主要研究方向: 叶轮机械流动稳定性、航空发动机性能、民航发动机适航审定技术. E-mail: Liuxh@mail.castc.org.cn; 周燕佩男, 教授, 高级工程师.主要研究方向: 航空发动机整机性能与结构、民航发动机适航审定技术. E-mail: Zhouyp@mail.castc.org.cn; 孙大坤男, 博士, 讲师.主要研究方向: 叶轮机流动稳定性、压气机扩稳理论与实验. E-mail: sundk@buaa.edu.cn; 马云飞男, 博士研究生.主要研究方向: 叶轮机流动稳定性理论与实验. E-mail: mmayunfei@163.com; 孙晓峰男, 博士, 教授, 博士生导师.主要研究方向: 叶轮机械非定常空气动力学、叶轮机流动稳定性、航空发动机气动声学、气动弹性. Tel: 010-82317408 E-mail: sunxf@buaa.edu.cn
基金资助:
国家自然科学基金(51106154,51010007,51236001);国家"973"计划(2012CB720201)

Axial Transonic Compressor Flow Instability Prediction Based on Eigenvalue Theory

LIU Xiaohua^1,2, ZHOU Yanpei¹, SUN Dakun², MA Yunfei², SUN Xiaofeng²

1. Aeroengine Airworthiness Certification Center Preparatory Office, China Academy of Civil Aviation Science and Technology, Beijing 100028, China;
2. School of Energy and Power Engineering, Beihang University, Beijing 100191, China

Received:2013-11-08 Revised:2013-12-19 Online:2014-11-25 Published:2013-12-23
Supported by:
National Natural Science Foundation of China (51106154,51010007,51236001); National Basic Research Program of China(2012CB720201)

摘要/Abstract

摘要：

流动失稳问题是叶轮机械所面临的严峻挑战之一,而旋转失速是轴流压气机及压缩系统中普遍存在的一种典型流动不稳定状态.基于特征值理论发展了一个轴流压气机流动失稳开始点预测模型,应用谱方法和奇异值分解(SVD)算法求解所建立的特征值方程,通过特征频率的虚部判断压缩系统的流动稳定性.并通过一个高速单转子在高低两个转速时的算例,定量分析了流动压缩性对跨声速压气机流动失稳开始点预测的重要影响.该模型可在合理的精度范围内,以工程应用可接受的计算资源消耗来预测跨声速单级压气机旋转失速的开始点流量,同时不应用大量经验数据,为压气机设计阶段的稳定性评估提供指导.

关键词: 压气机, 流动失稳, 旋转失速, 特征值, 谱方法

Abstract:

Flow instability is a great challenge in turbomachinery, and rotating stall is one major type of flow instability in compression system of aero-engine. In the present paper a rotating stall inception model based on a general eigenvalue theory of flow stability is developed with an emphasis on flow instability onset in axial transonic compressors. After solving the established eigenvalue equation using the spectral method and the singular value decomposition (SVD) method, the onset point of flow instability is determined by the imaginary part of the resultant eigenvalue. The significant effect of flow compressibility on the stall onset point calculation for a transonic rotor is studied by comparing the prediction results for a high speed single rotor at both high and low rotational speeds. The capacity of the present model to predict the stall inception point is assessed against the experimental data of a transonic single stage compressor. It is verified that this model is capable of predicting the mass flow at the stall onset point of a multi-stage transonic compressor flow with reasonable accuracy without numerous empirical data, and it is sustainable in terms of computation cost for industrial application.

Key words: compressor, flow instability, rotating stall, eigenvalue, spectral method

中图分类号:

V211.6

刘小华, 周燕佩, 孙大坤, 马云飞, 孙晓峰. 基于特征值理论的轴流跨声速压气机失稳预测[J]. 航空学报, 2014, 35(11): 2979-2991.

LIU Xiaohua, ZHOU Yanpei, SUN Dakun, MA Yunfei, SUN Xiaofeng. Axial Transonic Compressor Flow Instability Prediction Based on Eigenvalue Theory[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(11): 2979-2991.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于特征值理论的轴流跨声速压气机失稳预测

Axial Transonic Compressor Flow Instability Prediction Based on Eigenvalue Theory

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