Influence of Core Engine Component Coupling on Aerodynamic Heat Tramsfer Characteristics of High Pressure Turbine
To investigate the influence of compressors and combustion chambers on the performance of high pressure turbines,a joint simulation of the core engine components,such as compressor,combuster and turbine,was conducted.The aerodynamic performance and temperature distribution of high pressure turbines with film cooling were analyzed,and compared with the calculation results of a single component for turbine.The result shows that the core engine calculation reveals non-uniform parameter characteris-tics,which are mainly reflected in temperature.Temperature distribution changes more significantly with the development of the mainstream.The temperature distribution of IGVs is mainly determined by the in-let temperature boundary conditions.When the physical properties of the mainstream and the cold air are changed by the physical property difference under core engine calculation method,the flow field condition remains almost unchanged,while the effect on Mach number is below 2％,the temperature field changes above 6％at leading edge of blade and near pressure side area in channel,and the distribution trend re-mains unchanged.
gas turbinecoupling calculationhigh pressure turbinefilm cooling
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