中小型航空发动机叶型稳态压力受感器设计及试验研究  

Design and experimental study on the steady state pressure airfoil probe of Medium and small Aeroengine

作　　者：余柯锋 

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《电子测试》2017年第7期16-17,11,共3页Electronic Test

摘　　要：基于压力受感器的设计经验,为探索中小型航空发动机叶型稳态压力受感器的设计方向,本文利用开口吹气式亚音速校准风洞,对不同结构形式的叶型稳态压力受感器进行了吹风校准试验。通过测取不同工况下受感器的压力值,计算总压测量系数,分析了带整流套和不带整流套对于受感器不敏感角的影响,为进一步优化中小型航空发动机叶型稳态压力受感器设计提供了指导。This article aims at exploring the designing direction of Medium and small Aeroengine steady state airfoil probe with the help of existing design experience of pressure probe. A series of calibration test with probes which have different structures were conducted in a subsonic wind tunnel. By calculating the total pressure coefficient with measurements under different conditions, analysing difference between airfoil probe＇s insensitive angle with or without cowling, it will provide guidance for further optimization of Medium and small Aeroengine steady state airfoil probe.

关 键 词：叶型稳态压力受感器 风洞试验 不敏感角 

分 类 号：V263.3[航空宇航科学与技术—航空宇航制造工程]