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大涵道比涡扇发动机风扇叶片动应力测量试飞
引用本文:陶冶,田琳,解梦涛,宋振海,李兴海.大涵道比涡扇发动机风扇叶片动应力测量试飞[J].航空发动机,2017,43(3):67-73.
作者姓名:陶冶  田琳  解梦涛  宋振海  李兴海
作者单位:中国飞行试验研究院,西安710089;2. 中国航发沈阳发动机研究所,沈阳110015
摘    要:为了给风扇叶片设计验证和改进提供依据,针对大涵道比涡扇发动机风扇叶片的结构特点和振动强度设计要求,获取了飞行中发动机风扇叶片的振动特性,对风扇叶片振动强度进行了仿真分析,并将分析结果应用于测试方案设计,对飞机和发动机本体进行了改装,建立了飞行试验方法。基于充分的技术准备,完成了国内首次大涵道比涡扇发动机风扇叶片动应力测量试飞,填补了国内试飞领域的技术空白,掌握了发动机风扇叶片动应力测量试飞技术,为中国开展航空发动机转子叶片动应力测量的研制试飞和适航审定试飞奠定了基础。

关 键 词::动应力  测量试飞  风扇叶片  大涵道比  涡扇发动机

Flight Test on Fan-blade Vibration Stress of High Bypass Ratio Turbofan Engine
Authors:TAO Ye  TIAN Lin  XIE Meng-tao  SONG Zhen-hai  LI Xing-hai
Institution:1. Chinese Flight Test Establishment,Xi''an 710089;2. AECC Shenyang Engine Research Institute,Shenyang 110015
Abstract:According to the structural characters and vibration strength requirements for high bypass ratio turbofan engine, vibration characters of the fan blade of an engine in flight were obtained, which provides data for design verification and modification. Simulation analysis of vibration characters of fan blade was carried out and the result of analysis was applied to test project design, major refit was carried out in some aircraft and engine, and flight test method was established. Based on adequate technical preparation, domestic first flight test on fan-blade vibration stress of high bypass ratio turbofan engine was completed, which fills the blank of technology in flight-test field in China. Technology of flight test on fan-blade vibration stress of a high bypass ratio turbofan engine was mastered, which lay the basis for implementing development and airworthiness certification flight tests on rotor-blade vibration stress of an aeroengine in China
Keywords:vibration stress  flight test  fan blade  high bypass ratio  turbofan engine
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