航空工程进展2024，Vol.15Issue(4)：113-120,8.DOI:10.16615/j.cnki.1674-8190.2024.04.13
高流量裕度离心压气机叶片表面微坑结构研究
Study on micro-pit structure on blade surface of high flow margin centrifugal compressor
陈京名 1姜潜基 1冯卓凡2
作者信息
- 1. 西安明德理工学院 智能制造与控制技术学院,西安 710124
- 2. 南昌航空大学 飞行器工程学院,南昌 330063
- 折叠
摘要
Abstract
The stability of compressor operation has an inducing and amplifying effect on the stability and perfor-mance of the entire engine.Therefore,it is required that the flow margin of the compressor should be wider to adapt to the working stability of the engine under variable operating conditions.A new blade structure with micro pits distributed on the suction surface of the mainstream blade is proposed based on"Golf ball effect".The flow of a certain type of centrifugal compressor impeller is numerically simulated by using the CFX fluid dynamics software to study the effect of adding micro pits on the performance of flow separation structure and flow margin at different parts of the suction surface of the blade.Study the effect of adding micro pit structures with radii of 0.25～0.30 mm at different parts of the blade suction surface on structural performance and flow margin.The results show that ad-ding micro pits at the leading and trailing edges of the mainstream blade suction surface can improve the flow mar-gin.When the radius of the micro pits is 0.3 mm,the flow margin effect is the best,which are increased by 3.01%and 3.15%respectively.The use of new structural blades can increase the compressor flow margin,and provide a reference for the design of centrifugal compressor impellers.关键词
离心压气机/高尔夫球效应/微结构/流量裕度Key words
centrifugal compressor/Golf ball effect/micro structure/flow margin分类
航空航天引用本文复制引用
陈京名,姜潜基,冯卓凡..高流量裕度离心压气机叶片表面微坑结构研究[J].航空工程进展,2024,15(4):113-120,8.
