叶根失速先兆触发跨声速压气机失速的机制研究

推进技术 ›› 2017, Vol. 38 ›› Issue (10): 2340-2347.

叶根失速先兆触发跨声速压气机失速的机制研究

武文倩^1,2,胡加国^1,3,潘天宇^1,2,李秋实^1,2

北京航空航天大学能源与动力工程学院，航空发动机气动热力国家级重点实验室，北京 100191; 北京航空航天大学先进航空发动机协同创新中心，北京 100191,北京航空航天大学能源与动力工程学院，航空发动机气动热力国家级重点实验室，北京 100191; 空军工程大学航空航天工程学院，陕西西安 710038,北京航空航天大学能源与动力工程学院，航空发动机气动热力国家级重点实验室，北京 100191; 北京航空航天大学先进航空发动机协同创新中心，北京 100191,北京航空航天大学能源与动力工程学院，航空发动机气动热力国家级重点实验室，北京 100191; 北京航空航天大学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:武文倩，女，硕士生，研究领域为叶轮机械流动不稳定性。E-mail: wuwenqian@buaa.edu.cn 通讯作者:潘天宇，男，博士，研究领域为叶轮机械流动不稳定性。
基金资助:
国家自然科学基金重点项目(51636001)。

Mechanism Study of Stall Triggered by Hub Region Inception in a Transonic Compressor

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China; Collaborative Innovation Center of Advanced Aero-Engine，Beihang University，Beijing 100191，China,National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China; School of Aeronautics and Astronautics Engineering，Air Force Engineering University，Xi’an 710038，China,National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China; Collaborative Innovation Center of Advanced Aero-Engine，Beihang University，Beijing 100191，China and National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China; Collaborative Innovation Center of Advanced Aero-Engine，Beihang University，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 实验中发现了一种起始于叶根的新型压气机失速先兆，为了探索这种先兆的初始扰动特征及失速的动态发展机制，对该压气机开展全周非定常数值研究。数值结果表明，在压气机进入失速的过程中，静子叶根区域首先形成堵塞区，验证了失速初始扰动起源于叶根区域。该扰动由六个轴对称分布、以45%转子转速旋转的堵塞团组成。随着失速程度的加深，静子叶根堵塞团在低叶高范围内合并为整圈的分离区，造成整个叶根区域流动的堵塞。叶根的堵塞导致气流从堵塞区上方绕行，加快了叶尖区域的流动速度，激波的增强导致叶顶泄漏涡破碎程度加剧，形成转子叶尖堵塞区并发展为旋转失速团，最终导致压气机失速。

关键词: 跨声速压气机；高负荷；叶根失速先兆；旋转失速；失速机制

Abstract: A new type of stall inception starting from the hub region was found in the experiments. Full-annulus transient simulations were carried out to explore the characteristics of the initial disturbance and the dynamic development mechanism of the stall process. The simulation results show that the blockage area firstly forms in the stator hub region during the stall process， indicating that the disturbance initiates in the compressor hub region. The disturbance is consisted of six axisymmetric blockages which are rotating at 45% of the rotor speed. In the stall evolution， the blockages merge into a full-annulus separation zone， leading to more serious flow blockage at low blade height. Because of the hub region blockage， more fluid have to go through the tip region， resulting in the increase of tip region flow rate， so the tip region fluid is accelerated. Moreover， shock wave/tip leakage vortex interaction cause the formation of tip blockage. The tip region’s blockage finally develops into rotating stall cells which lead to the compressor eventual stall.

Key words: Transonic compressor；High load；Hub region inception；Rotating stall；Stall mechanism

武文倩,胡加国,潘天宇,李秋实. 叶根失速先兆触发跨声速压气机失速的机制研究[J]. 推进技术, 2017, 38(10): 2340-2347.

WU Wen-qian^1,2,HU Jia-guo^1,3,PAN Tian-yu^1,2,LI Qiu-shi^1,2. Mechanism Study of Stall Triggered by Hub Region Inception in a Transonic Compressor[J]. Journal of Propulsion Technology, 2017, 38(10): 2340-2347.

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