特征值理论在稳定性预测中的应用研究进展

孙晓峰; 董旭; 张光宇; 王卓; 孙大坤

doi:10.7527/S1000-6893.2022.27408

航空学报 >

2022 , Vol. 43 >Issue 10: 527408 - 527408

DOI: https://doi.org/10.7527/S1000-6893.2022.27408

流体力学与飞行力学

特征值理论在稳定性预测中的应用研究进展

孙晓峰 ,
董旭 ,
张光宇 ,
王卓 ,
孙大坤

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1. 北京航空航天大学能源与动力工程学院, 北京 100191;
2. 北京航空航天大学航空发动机研究院, 北京 100191

收稿日期: 2022-05-10

修回日期: 2022-05-23

网络出版日期: 2022-07-21

基金资助

军委科技发展部预研管理中心重点实验室基金资助项目（6142702200101）

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Progress review of application of eigenvalue theory to stability prediction

SUN Xiaofeng ,
DONG Xu ,
ZHANG Guangyu ,
WANG Zhuo ,
SUN Dakun

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1. School of Energy and Power Engineering, Beihang University, Beijing 100191, China;
2. Research Institute of Aero-Engine, Beihang University, Beijing 100191, China

Received date: 2022-05-10

Revised date: 2022-05-23

Online published: 2022-07-21

Supported by

Key Laboratory of Pre-Research Management Center (6142702200101)

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摘要

航空发动机三大主要部件风扇/压气机、燃烧室和涡轮的稳定工作范围直接决定了发动机整机的性能和稳定性，在追求高气动性能、高涡轮前温度和低排放的同时，主要部件的气动、气弹和燃烧稳定性问题变得尤为突出。基于经验的稳定性预估方法已不适用于现代航空发动机一体化的设计思想，发展快速、准确的稳定性评估方法和稳定性控制技术并将其纳入发动机设计流程具有重要的理论和工程价值。本文主要综述了基于小扰动方法和特征值理论发展的多种半解析模型的研究进展，该方法在设计阶段可以有效评估风扇/压气机气动稳定性、预测叶片颤振和主/加力燃烧室热声不稳定性，为进一步开展稳定性控制设计提供了基础，且为节约实验和数值成本，建立发动机一体化设计方法提供了可能。

关键词： 特征值理论; 航空发动机; 小扰动; 流动稳定性; 燃烧稳定性; 气弹稳定性

本文引用格式

孙晓峰 , 董旭 , 张光宇 , 王卓 , 孙大坤 . 特征值理论在稳定性预测中的应用研究进展[J]. 航空学报, 2022 , 43(10) : 527408 -527408 . DOI: 10.7527/S1000-6893.2022.27408

Abstract

The stable operating ranges of the fan/compressor, combustor and turbine of the aero-engine directly determine the performance and stability of the engine. While pursuing high aerodynamic performance, high turbine temperature and low emission, the aerodynamic, aeroelastic and combustion stability problems of the main components become particularly prominent. It is of great theoretical and engineering values to develop rapid and accurate stability assessment methods and stability control techniques and incorporate them into the engine design process. This paper gives a review of the research progress of a variety of semi-analytical models developed based on the small perturbation method and the eigenvalue theory. These methods can effectively evaluate the fan/compressor aerodynamic instability and predict the flutter and main/afterburner combustor thermal instability in the design phase. On this basis, the further stability control design can be conducted to save the cost of experiments and simulations.

Key words： eigenvalue theory; aero-engine; small perturbation method; flow stability; combustion stability; aeroelastic stability

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