多级高压比压气机气动失稳试验研究

李宏新; 贾博博; 陈禹西; 张志博; 梁彩云; 全福祥

doi:10.13224/j.cnki.jasp.20230302

多级高压比压气机气动失稳试验研究

doi: 10.13224/j.cnki.jasp.20230302

1.
中国航发沈阳发动机研究所，沈阳 110015
2.
大连理工大学电子信息与电气工程学部，辽宁大连 116024

基金项目: 国家自然科学基金重大项目（61890925）

详细信息

作者简介:
李宏新（1969-），男，研究员，博士，主要从事航空发动机技术管理工作。E-mail：wc15942328426@126.com

通讯作者:
张志博（1984-），男，研究员，博士，主要从事叶轮机试验研究。E-mail：zhibo346@163.com

中图分类号: V216
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出版历程
- 收稿日期: 2023-05-09
- 网络出版日期: 2025-03-28

Experimental investigation of aerodynamic instabilities in a multistage high pressure ratio compressor

1.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
2.
Faculty of Electronic Information and Electrical Engineering，Dalian University of Technology，Dalian Liaoning 116024，China

摘要

摘要:
针对航空发动机多级高压比压气机气动失稳先兆特征微弱、机理复杂、测量难度高、不易检测和预判等问题，开展了系统性的全尺寸多级高压比轴流压气机气动失稳先兆特征试验研究，通过采用全环均布与扇区均布相结合的多截面、多相位、高采样率的脉动压力测试方法，获取了不同转速和可调叶片角度压气机气动失稳特征，旨在为压气机气动稳定性研究和航空发动机主动安全控制提供重要的研究基础。结果表明：在相对换算转速为0.8与1.0时，压气机的失稳形式均表现为喘振，入喘前先兆特征频率周向模态波的幅值和阶数逐渐增；不同转速时失稳首发级与失稳先兆特征存在差异；叶片开/关角度对失稳过程的影响主要体现在喘前模态波幅值变化上。
- 高压压气机 /
- 喘振 /
- 脉动压力 /
- 失稳先兆 /
- 模态波
Abstract:
The aerodynamic instability inception of aero-engine multistage high pressure ratio compressor has weak feature, complicated mechanism and difficulty in detection and prediction. A systematic experimental investigation of rotating stall and surge inception in a full-size multistage high pressure ratio axial flow compressor was developed. The rotating stall and surge characteristics at different rotate speed and angel of variable vanes were obtained by using a multi-section, multi-phase, high sample rate test method combined with the whole ring and sector uniformed measuring point distributions. These efforts aimed at providing an important research basis for compressor aerodynamic stability research and aero engine active safety control. The results showed that at the relative corresponding speed of 0.8 and 1.0, the instability was manifested as surge; before entering the surge state, the amplitude and order of the circumferential modal wave of inception characteristic frequency increased gradually; the stage leading to instability was different at different speeds. The influence of variable vanes angle was reflected in the modal wave amplitude change before surge.
- high pressure ratio compressor /
- surge /
- dynamic pressure /
- instability inception /
- modal wave

HTML

图 1 压气机特性图

Figure 1. Characteristic chart of compressor

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图 2 堵点、工作点和近喘点95%叶高处相对马赫数分布

Figure 2. 95% blade height Mach number distribution at choked point, surge point and operating point

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图 3 静叶角度对压气机特性影响

Figure 3. Effect of variable vane angle on compressor characteristic

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图 4 压气机部件失稳状态模拟试验平台

Figure 4. Experimental facility of compressor component instability simulation

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图 5 动态压力测点位置及编号示意

Figure 5. Dynamic pressure measurement points location and numbering

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图 6 动态信号采集方法

Figure 6. Dynamic signal acquisition method

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图 7 两个换算转速下出口脉动压力变化

Figure 7. Variation of pulsating pressure in outlet at two converted speeds

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图 8 喘振发生过程时域特征

Figure 8. Time-domain feature during surge

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图 9 失稳首发级分析

Figure 9. First instability stage analysis

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图 10 模态波频谱特征

Figure 10. Frequency-domain feature of modal wave

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图 11 开角度工况下各级模态波周向模态阶数

Figure 11. Order of the circumferential modal wave at stages with open variable vane

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表 1 出口动态压力测点布置方案

Table 1. Dynamic pressure measurement points position

截面位置	测点布局
R1前（A）	扇形，间隔21°12′，5个测点
R2前（B）	全环，间隔30°，12个测点
R3前（C）	扇形1间隔20°，4个测点扇形2间隔24°，5个测点
R4前（D）	扇形1间隔19°，5个测点扇形2间隔21°12′，5个测点
出口（E）	30非均布，3个测点

下载: 导出CSV

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