变宽度斜槽机匣处理对组合压气机的扩稳效果研究  

Study on stall margin improvement effect of the variable width oblique grooves on a combined compressor

作　　者：杨元英 安志强 李杜 杨晶晶 YANG Yuan-ying;AN Zhi-qiang;LI Du;YANG Jing-jing(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Hunan Key Laboratory of Turbomachinery on Small and Medium Aero-engine,Zhuzhou 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002

出　　处：《燃气涡轮试验与研究》2021年第3期11-15,21,共6页Gas Turbine Experiment and Research

基　　金：湖南省科技创新人才计划科技领军人才项目(2020RC4035)。

摘　　要：采用三维数值模拟方法,对高负荷轴流-离心组合压气机开展了机匣处理扩稳设计技术应用研究。为了同时达到较好的扩稳效果和较小的设计点效率降幅,在组合压气机第一级转子对应机匣位置采用了前伸出转子叶尖前缘、槽宽从前端到后端变化的斜槽机匣处理设计。对设计结果的分析显示,变宽度斜槽机匣处理在转子尖部区域呈现明显的抽吸-再注入扩稳流动特征;在设计点效率下降小于0.2个百分点的同时,使得组合压气机90%设计转速近喘点压比增加1.90%、轴流级近喘点压比增加3.15%。A high load axial-radial combined compressor was investigated by numerical simulation to study the application of casing treatment.In order to achieve maximum stall margin improvement and mini⁃mize efficiency drop,the oblique grooves with variable width from leading edge to trailing edge were em⁃ployed on the shroud casing upstream of first-stage rotor.The study of design result shows that the pump and refill flow characteristics of stability extension with the variable width shallow oblique grooves present clearly in the tip flow region of rotor,the total pressure ratio of axial stage near surge point increases by 3.15%and results in 1.90%enhancement on combined compressor at 90%design speed.Meanwhile,the decreasing of design point efficiency is less than 0.2 points according to the casing treatment.

关 键 词：航空发动机 组合压气机 机匣处理 变宽度斜槽 高负荷 扩稳效果 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]