跨声速压气机叶尖开槽射流扩稳策略探究

推进技术 ›› 2014, Vol. 35 ›› Issue (11): 1475-1481.

跨声速压气机叶尖开槽射流扩稳策略探究

胡加国,王如根,李　坤,董　鑫

空军工程大学航空航天工程学院，陕西西安 710038;空军工程大学航空航天工程学院，陕西西安 710038;空军工程大学航空航天工程学院，陕西西安 710038;空军工程大学航空航天工程学院，陕西西安 710038

发布日期:2021-08-15
作者简介:胡加国(1990—)，男，硕士生，研究领域为气动热力理论与工程。

Investigation on Slot Jetting Flow Method and Mechanism of Transonic Compressor

School of Aeronautics and Astronautics Engineering，Air Force Engineering University，Xi’an 710038，China;School of Aeronautics and Astronautics Engineering，Air Force Engineering University，Xi’an 710038，China;School of Aeronautics and Astronautics Engineering，Air Force Engineering University，Xi’an 710038，China;School of Aeronautics and Astronautics Engineering，Air Force Engineering University，Xi’an 710038，China

Published:2021-08-15

摘要/Abstract

摘要： 为了提高跨声速轴流压气机的稳定工作范围，提出一种叶尖开槽射流的扩稳策略，设计7种开槽方案，并通过数值模拟分析其效果及扩稳机理。计算结果表明，针对叶尖通道堵塞设计的开槽射流方案取得了较好的效果，压气机稳定工作裕度实现了2.33%～4.53%的提高，但峰值效率降低0.26%～1.24%；在合理的范围内，槽道的宽度越宽、深度越深、出口位置在近失速工况的分离点前和出口射流角度25°左右时扩稳效果最好，但性能损失与扩稳效果负相关；开槽射流实现扩稳的原因是:槽道入口对压力面前缘低速流团的抽吸作用、出口射流对吸力面尾缘分离的吹除作用以及减小叶尖间隙内的泄漏。

关键词: 跨声速压气机；流动失稳；叶尖开槽；射流；扩稳机理

Abstract: In order to broaden the stable working range of transonic axial compressor，a new strategy of jetting flow was developed with slot on the tip of blade，as well as seven cases. Numerical simulation shows that the designation for decreasing blade tip passage works well. It is potential to extend the operating range of compressor from 2.33% to 4.53%，while decreasing the top efficiency by 0.26% to 1.24%. Under a reasonable range，a greater slot width and depth，outlet position located in front of separation point when near instability and outlet jetting flow angle is approximately 25°，can increase the effect of improving stability，however it will worsen compressor performance. The mechanism of broaden compressor stability for tip slot jetting is that inlet of the slot bleeding low velocity flow mass located in front of pressure side，outlet jetting flow blowing away the trailing edge separation，and the slot decreasing clearance leakage between blade tip and shroud.

Key words: Transonic compressor；Flow instability；Tip slot；Jet flow；Mechanism of improving stability

胡加国,王如根,李　坤,董　鑫. 跨声速压气机叶尖开槽射流扩稳策略探究[J]. 推进技术, 2014, 35(11): 1475-1481.

HU Jia-guo,WANG Ru-gen,LI Kun,DONG Xin. Investigation on Slot Jetting Flow Method and Mechanism of Transonic Compressor[J]. Journal of Propulsion Technology, 2014, 35(11): 1475-1481.

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