航空发动机机匣壁面温度分布数值模拟与分析

Numerical Simulation and Analysis of Casing Wall Temperature Distribution for an Aeroengine

为了准确预测航空发动机机匣壁面的温度分布,通过建立发动机性能计算模型,借助发动机沿程热力循环参数计算的通用方法,利用管内流体对管壁的对流换热过程,开发了发动机机匣热壁1维数值计算软件,模拟了飞机包线内某个发动机状态下发动机机匣表面的温度场,并进行了试验验证。将计算结果与试验结果对比可知,温度分布曲线除外涵区外趋势基本一致。该方法将可将发动机机匣壁面温度作为单独模块进行模拟计算,可以为发动机设计和调试提供较为准确的参考数值。

In order to accurately predict casing wall temperature distribution of a turbofan engine, one dimensional numerical calculation software of the engine casing wall was developed, and the outer surface temperature field of the engine was simulated and validated on some operation conditions in aircraft flight envelope by building calculation model of engine performance, calculating turbofan engine thermodynamic cycle parameters, and researching convective heat transfer process of tube. The temperature distribution curves were consistent except outer duct by comparison between the calculation and expiration results. The casing wall temperature is simulated and calculated as a signal model by the above mentioned method, which can provide a more accurate reference value for engine design and test.