某在役航空发动机压气机叶片性能研究  

Study on the Performance of the Compressor Blade of an Certain Aero-engine in Service

作　　者：魏永超[1] 

机构地区：[1]中国民用航空飞行学院飞行技术与飞行安全科研基地,广汉618307

出　　处：《科学技术与工程》2017年第5期119-125,共7页Science Technology and Engineering

基　　金：国家自然科学基金(61079022);民航局科技基金(20150215);四川省科技基金(2015JY0188)资助

摘　　要：真实工况下叶片型面变化与性能演变规律,是需要研究解决的问题。基于在役某发动机,开展了压气机叶片型面测量、建模、模型比对以及性能分析。利用开发的三维扫描系统,完成了真实工况下的叶片型面测量与建模;在理论分析基础上,完成了叶片差异量化评估;并采用有限元技术,对叶片的静强度特性和振动模态进行了研究,分析了其性能特点;通过进一步数据对比,总结得出叶片性能演变规律。真实的验证分析数据研究可进一步推动构建叶片性能模型,并指导我国发动机设计与维修。The change of blade surface and the law of its performance under real working conditions are the problems that need to be solved. Based on a certain engine in service, the profile measurement, modeling, model comparison and performance analysis of the compressor blade were developed. Using our 3D scanning system, the blade surface measurement and modeling under the real working condition were completed. Based on the theoretical analysis, the quantitative evaluation of the differences between blades was done. The blade static characteristic and vibration modal were studied using the finite element method. Through the further data comparison, blade perform-ance evolution rule was concluded. The real validation analysis data can further promote the construction of the blade performance model, and guide the design and maintenance of the engine of our country.

关 键 词：压气机叶片 型面测量 静力学 振动模态 

分 类 号：V231.92[航空宇航科学与技术—航空宇航推进理论与工程]