航空发动机小扰动叶型受感部设计及试验研究
Design and Experimental Study of Small Disturbance LE Probe for Aero-engine
高倩 1余柯锋 1杨灿1
作者信息
- 1. 中国航发湖南动力机械研究所测试技术研究部,湖南株洲 412002
- 折叠
摘要
对航空发动机级间性能参数测试的小扰动叶型受感部进行数值模拟研究和校准试验研究.数值模拟研究结果表明,带B型整流罩的叶型受感部对流场的影响更小;校准试验研究表明,B型叶型受感部的总压特性较好,不敏感角范围为﹣30°～10°,总压测量误差绝对值不大于0.1%.根据数值模拟和校准试验研究结果,寻求某型航空发动机小扰动叶型受感部的最优设计方案,并在该型发动机整机全流程参数测量试验中进行试验应用,试验结果为该型发动机的性能验证、改进、改型提供了重要的技术支撑.
Abstract
The numerical simulation and calibration test study are carried out for the small disturbance LE probe,which is used to measure the inter-stage performance of aero-engine.The numerical simulation results show that the LE probe which has type B cowling has less impact for the flow field.The calibration test results show that the LE probe which has type B cowling has better total pressure characteristic,the range of insensitive angles are-30 ° to 10 °,the total pressure measurement error absolute value is not greater than 0.1%.And the optimal design scheme of small disturbance LE probe is obtained for one aero-engine,and the LE probe has been used in the whole flow path parameter measurement test.The test results provide important support for the performance verification and modification of the aero-engine.
关键词
航空发动机/级间参数测试/叶型受感部/校准试验Key words
aero-engine/interstage parameter measurement/LE probe/calibration test引用本文复制引用
出版年
2024
NETL
NSTL
万方数据