变转速下跨声速压气机的耦合扩稳方法

赵乐; 王维; 张乐福; 王伟超; 卢金玲; 楚武利

doi:10.7527/S1000-6893.2021.24942

航空学报 >

2022 , Vol. 43 >Issue 1: 124942 - 124942

DOI: https://doi.org/10.7527/S1000-6893.2021.24942

流体力学与飞行力学

变转速下跨声速压气机的耦合扩稳方法

赵乐 ,
王维 ,
张乐福 ,
王伟超 ,
卢金玲 ,
楚武利

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1. 西安理工大学水利水电学院, 西安 710048;
2. 西安理工大学省部共建西北旱区生态水利国家重点实验室, 西安 710048;
3. 西北工业大学动力与能源学院, 西安 710072;
4. 先进航空发动机协同创新中心, 北京 100191

收稿日期: 2020-11-02

修回日期: 2021-01-04

网络出版日期: 2022-02-14

基金资助

中国博士后科学基金（2020M683525）；国家重点研发计划（2018YFB1501900）；国家自然科学基金（51879216，51679195）；陕西省教育厅科研计划（19JK0587）

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Coupling method for stability improvement for transonic compressor at variable speed

ZHAO Le ,
WANG Wei ,
ZHANG Lefu ,
WANG Weichao ,
LU Jinling ,
CHU Wuli

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1. Faculty of Water Resources and Hydroelectric Engineering, Xi’an University of Technology, Xi’an 710048, China;
2. State Key Laboratory of Eco-hydraulic in Northwest Arid Region, Xi’an University of Technology, Xi’an 710048, China;
3. School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China;
4. Collaborative Innovation Center of Advanced Aero-Engine, Beijing 100191, China

Received date: 2020-11-02

Revised date: 2021-01-04

Online published: 2022-02-14

Supported by

China Postdoctoral Science Foundation (2020M683525); National Key R & D Program of China(2018YFB1501900); National Natural Science Foundation of China (51879216,51679195); Scientific Research Projects of Shaanxi Provincial Department of Education(19JK0587)

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摘要

为了探索在不同转速下均可有效提高压气机失速裕度的扩稳方法，以跨声速压气机为研究对象，利用缝式机匣处理和叶顶喷气进行耦合设计，并参数化研究了缝数目、缝长、缝宽及喷嘴周向宽度对压气机性能的影响规律，结合非定常数值模拟揭示了耦合型机匣处理的扩稳机理。研究结果表明，在100%、80%、60%转速下，压气机失速裕度分别提高9.31%、8.26%、8.68%，设计点效率分别降低0.77%、0.23%、0.41%。缝数目、缝长、缝宽是影响压气机失速裕度及效率的显著因素，而喷嘴周向宽度对压气机失速裕度及效率的影响较小。耦合型机匣处理内形成了抽吸、喷气的耦合流动循环，耦合强度的增加有利于压气机失速裕度的提高，但会降低压气机效率。耦合型机匣处理提高了叶顶负荷，但降低了叶顶泄漏强度，极大消除了叶顶泄漏涡引起的叶顶堵塞，这是压气机失速裕度提高的主要原因。耦合型机匣处理具有在不同转速下均能有效扩稳的潜力。

关键词： 跨声速压气机; 变转速; 耦合型机匣处理; 失速裕度; 叶顶泄漏涡

本文引用格式

赵乐 , 王维 , 张乐福 , 王伟超 , 卢金玲 , 楚武利 . 变转速下跨声速压气机的耦合扩稳方法[J]. 航空学报, 2022 , 43(1) : 124942 -124942 . DOI: 10.7527/S1000-6893.2021.24942

Abstract

To explore an effective method to improve the stall margin of a transonic compressor at different operating speeds, this study couples the slot casing treatment and tip injection to enhance the compressor stability. The effects of the number, length, width of the slots and the nozzle circumferential width on the compressor performance are studied parametrically, and the mechanism of stability enhancement is revealed using unsteady numerical simulations. The results show that the stall margin increases by 9.31%, 8.26% and 8.68% at 100%, 80% and 60% speed, respectively, while the compressor efficiency at the design point is decreased correspondingly by 0.77%, 0.23% and 0.41%. The number, length and width of the slots have significant effects on the stall margin and the efficiency of the compressor, while the circumferential width of the nozzle has little effect on the compressor performance. A flow cycle composed of suction and injection is formed in the coupled casing treatment. The increase of the coupling strength is beneficial to the improvement of the stall margin, and detrimental to the compressor efficiency. The coupling casing treatment leads to the increase of the blade tip loading, meanwhile reducing the tip leakage intensity and eliminating the tip blockage caused by the tip leakage vortex, which is the main reason for the improvement of the compressor stall margin. The coupling casing treatment has the potential to enhance effectively the compressor stability at different speeds.

Key words： transonic compressor; variable speeds; coupling casing treatment; stall margin; tip leakage vortex

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