涡轮导向器喉道燃气流量计算及参数敏感性分析

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。

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

Taking a high bypass ratio turbofan as the research object,the combustor exit temperature is calculated by using the method of HP turbine nozzle throat flow function,and to get the core airflow rate indirectly.The computation results are good agreement with the engine designer’s results.Based on that,parameter 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.