倾斜式周向槽机匣处理对压气机稳定性的影响  

Influence of Inclined Circumferential Groove Casing Treatment on Compressor Stability

作　　者：龚文琴 周佳星 辛佳 王伟韬 何振鹏 GONG Wen-qin;ZHOU Jia-xing;XIN Jia;WANG Wei-tao;HE Zhen-peng(Department of Computer Science and Technology,Tianjin Renai College,Tianjin 301636,China;Research Institute of Areo-Engine,Beihang University,Beijing 100191,China;College of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]天津仁爱学院计算机科学与技术系,天津301636 [2]北京航空航天大学航空发动机研究院,北京100191 [3]中国民航大学航空工程学院,天津300300

出　　处：《航空发动机》2024年第1期64-71,共8页Aeroengine

基　　金：天津市科技局科技计划项目(No.20YDTPJC01720);省部级重点专项(2021EEDSCXSFQZD009)资助。

摘　　要：为分析倾斜周向槽机匣处理对跨声速轴流压气机NASA Rotor 37稳定性的影响,采用数值仿真方法研究了光壁机匣和倾斜周向槽机匣的扩稳效果。结果表明:经过周向槽机匣处理后,叶尖泄漏流被诱导进入周向槽,抑制了低速区的发展且泄漏流经过周向槽流出后能够吹除低能区,改善低速区造成的流道堵塞情况,扩大压气机的稳定工作范围;在设计转速下,5种不同形式的周向槽机匣处理都能够提高压气机的稳定裕度,其中,CT3的扩稳效果最好,稳定裕度提高2.86%,而峰值效率降低最少,仅降低0.7%;通过正交试验优化设计方法发现,样本9对于提升转子的稳定裕度效果最为明显,能够将稳定裕度提升2.95%,但会使峰值效率降低1.56%;当周向槽轴向倾斜方式不同时,会使得周向槽的周向截面及槽内流动发生改变,从而对压气机的稳定裕度和峰值效率造成影响。To analyse the influence of the inclined circumferential groove casing on the stability of a transonic axial compressor,NASA Rotor 37,the stability enhancement effect of the smooth wall casing and the inclined circumferential groove casing was studied by numerical simulation.The results show that after the circumferential groove casing treatment,the tip leakage flow is induced into the circumferential groove,which inhibits the development of the low-speed zone.After passing through the circumferential groove,the leakage flow can blow away the low-energy zone,which can decrease the flow path blockage caused by the low-speed zone,and improve the stability of the compressor.Under the design speed,5 different types of circumferential groove casing treatment can all improve the stability margin of the compressor.Among them,the CT3 has the best stability enhancement effect,with a stability margin increase of 2.86%and the least reduction in peak efficiency of 0.7%.Through the orthogonal design of experiments optimization,it is found that Sample 9 has the most obvious effect on improving the stability margin of the rotor,with a 2.95%stability margin increase,but the peak efficiency reduction is 1.56%.When the circumferential grooves are different in axial inclination,the flow in the circumferential section of the circumferential groove and the flow in the grooves are changed,thereby affecting the stability margin and peak efficiency of the compressor.

关 键 词：倾斜周向槽 机匣处理 跨声速轴流压气机 数值模拟 稳定裕度 峰值效率 航空发动机 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]