亚声速轴流压气机叶顶喷气设计规律的试验研究

doi:10.13675/j.cnki. tjjs. 180630

推进技术 ›› 2019, Vol. 40 ›› Issue (9): 1982-1990.DOI: 10.13675/j.cnki. tjjs. 180630

亚声速轴流压气机叶顶喷气设计规律的试验研究

王维^1,2,黄雨洁¹,卢金玲^1,2,罗兴锜^1,2,楚武利^3,4

1.西安理工大学水利水电学院;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;3.西北工业大学动力与能源学院;4.先进航空发动机协同创新中心，北京;100191

发布日期:2021-08-15
作者简介:王维，博士，讲师，研究领域为叶轮机械气动热力学。E-mail：weiwang@xaut.edu.cn
基金资助:
国家自然科学基金 51879216 51006084;陕西省自然科学基金 2018JQ5152;国家自然科学基金重点项目国家自然科学基金（51879216；51006084）；陕西省自然科学基金（2018JQ5152）；国家自然科学基金重点项目

Experimental Study of Tip Injection Method in aSubsonic Axial Flow Compressor

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

Published:2021-08-15

摘要/Abstract

摘要： 为了探索叶顶喷气在亚声速轴流压气机中的设计规律，试验研究了喷气量、喷嘴喉部高度、周向覆盖比例、喷气位置、喷嘴数目、喷嘴分布形式对压气机失速裕度的影响规律，分析了叶顶喷气的扩稳机理以及对压气机失速特性的影响，总结了叶顶喷气在亚声速和跨声速压气机中作用规律的异同。研究结果表明，叶顶喷气没有改变压气机的失速特性，其扩稳机理主要在于对叶顶堵塞的有效抑制，通道堵塞对叶顶喷气的非定常响应是离散叶顶喷气有效扩稳的重要原因。当喷嘴处于堵塞状态时扩稳效果达到最大，利用0.66%的喷气量可将压气机的失速裕度提升15%。对于压气机失速裕度的影响，喷气量、喷嘴喉部高度、喷气周向覆盖比例间存在交互作用，喷气位置、喷嘴周向分布形式和进气畸变对喷气扩稳效果的影响均不大。当压气机的失速均是由叶顶泄漏涡诱发的突尖失速时，叶顶喷气在亚声速压气机中的设计方法可用于指导跨声速压气机叶顶喷气的设计。

关键词: 轴流压气机;叶顶喷气;失速裕度;交互作用;叶顶泄漏涡

Abstract: The study is to investigate the tip injection method in a subsonic axial flow compressor. The effects on compressor stability of injection mass flow, injector throat height, circumferential coverage percentage, injection position, injector numbers and injector distribution were experimentally studied. The flow mechanism of stability improvement and the effect on compressor stall dynamic were analyzed. The similarities and differences of tip injection method in the subsonic and in the transonic compressor were summarized. The results show that the stall dynamic of the compressor is not changed by tip injection, and the effective depression on tip blockage mainly accounts for the enhancement of compressor stability. The unsteady response of tip blockage to the tip injection is primary responsible for the effectiveness of discrete tip injection with a partial circumferential coverage. Stability margin is improved by 15% employing 0.66% of the annulus mass flow when the injectors are choked. The effects on compressor stability of the injection mass flow, injector throat height and circumferential coverage percentage interact with each other. The effects on compressor stability improvement of injection position, injector circumferential distribution and inlet distortion are limited. When the compressor stall is triggered by tip leakage vortex resulting in a spike stall, the design methodology of tip injection derived from a subsonic compressor can be adopted in a transonic compressor.

Key words: Axial flow compressor;Tip injection;Stall margin;Interaction effect;Tip leakage vortex

王维,黄雨洁,卢金玲,罗兴锜,楚武利. 亚声速轴流压气机叶顶喷气设计规律的试验研究[J]. 推进技术, 2019, 40(9): 1982-1990.

WANG Wei^1,2,HUANG Yu-jie¹,LU Jin-ling^1,2,LUO Xing-qi^1,2,CHU Wu-li^3,4. Experimental Study of Tip Injection Method in aSubsonic Axial Flow Compressor[J]. Journal of Propulsion Technology, 2019, 40(9): 1982-1990.

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亚声速轴流压气机叶顶喷气设计规律的试验研究

Experimental Study of Tip Injection Method in aSubsonic Axial Flow Compressor

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