涡轮导向器喉道燃气流量计算及参数敏感性分析  

Gas Flow Rate Calculation at High Pressure Turbine Nozzle Throat and the Analysis on Parameter Sensitivity

作　　者：高扬[1] 刘旭东[1] 屈霁云[1] 寿圣德[1] 

机构地区：[1]中国飞行试验研究院发动机所,陕西西安710089

出　　处：《燃气涡轮试验与研究》2012年第2期37-42,共6页Gas Turbine Experiment and Research

摘　　要：以某型大涵道比涡扇发动机为对象,采用高压涡轮导向器喉道流量函数的方法,计算得到燃烧室的出口温度,并间接获得燃烧室出口燃气流量。计算结果表明,本文方法所得结果与设计方计算结果吻合较好。在此基础上,针对该计算方法进行了参数敏感性分析,其结果将有助于飞行试验工程师更加合理地选择测试方法及传感器类型,为后续的试验工作奠定技术基础。Taking a high bypass ratio turbofan as the research object, the combustor exit temperature is cal- culated by using the method of HP turbine nozzle throat flow function, and to get the core airflow rate indi- rectly. The computation results are good agreement with the engine designer＇s results. Based on that, param- eter sensitivity analysis is performed, from which the result can be useful for flight test engineers to select suitable measurement and transducers, and also provided the technical base for future test.

关 键 词：燃气流量计算 参数敏感性分析 发动机性能 飞行试验 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]