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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。
In order to provide the basis for the verification and improvement of fan blade design, the vibration characteristics of fan blade in flight were obtained and the vibration intensity of fan blade was simulated and analyzed in accordance with the structural characteristics and vibration intensity design requirements of fan blade with large bypass ratio turbofan. , And the analysis results are applied to the test scheme design, the aircraft and the engine body was modified, the establishment of a flight test method. Based on sufficient technical preparations, the first large-bypass turbofan engine fan blade dynamic stress measurement test was completed in China, filling the technical gaps in the field of test flight in the country and mastering the test technology of dynamic stress measurement of engine fan blades. As a pilot project for China’s development of aeroengine rotor Development of blade dynamic stress measurement test and airworthiness certification test laid the foundation.