航空发动机过渡态典型热端部件热响应分析

为满足航空发动机方案设计阶段结构分析及强度寿命评估的要求,必须提供相关零件稳态和过渡态热状态数据。应用1维解析方法和数值方法分别对薄壁类和轴对称缘盘类热端部件进行了过渡态热状态计算分析,得到带涂层叶片、盘及机匣平均温度随发动机状态的变化,并依此分别进行了各零件热响应分析;由热响应分析结果得到了高压涡轮转子和机匣过渡态热伸长量,并进行了过渡态的热间隙分析,为结构分析提供输入;计算结果与采用ANSYS软件计算的结果偏差普遍在3%以内,说明计算方法合理,可适用于方案设计阶段过渡态热端部件热状态计算。

Transient Thermal Response Analysis for Aeroengine Typical Host Part

In order to meet structure analysis and intensity-life evaluation in aeroengine concept design,steady and transient thermal behavior about host part of aeroengine must be provided.The transient thermal behavior for thin wall part and disc-discpiston part was obtained respectively by one-dimensional analytic method,and one-dimensional numerical method.Transient average temperature about turbine blade,disc and shroud were achieved,and thermal response analysis for each part was carried out.Based on the above data,thermal elongation indicator of high pressure turbine rotor and stator was obtained,and turbine blade tip clearance variation tendency according to aeroengine working time-history was achieved,and it is very need for blade tip clearance design.The deviation between the calculation and the ANSYS calculation was generally 3%.The method is applicable for transient thermal response analysis about host part in concept design phase.