为研究上游压气机和燃烧室对高压涡轮性能的影响，本文采用RANS方法对燃气轮机核心机进行整机联合仿真，对带气膜冷却的高压涡轮气动性能及温度分布进行了分析，并与单一部件计算结果进行了对比。计算结果表明：涡轮部件计算参数分布均匀，核心机计算展示了非均匀的参数特征，且特征主要体现在温度上，随主流往后的发展变化也更加明显；在流动状况下相似的情况下，IGV的温度分布主要由入口温度边界条件决定。改变涡轮和冷气的物性，流动状况几乎不改变，对于马赫数影响在2%以内，温度差别集中于前缘及通道内近压力侧区域，差别可以达到6%以上，分布趋势不变。

To investigate the influence of upstream compressors and combustion chambers on the performance of high-pressure turbines, this paper uses the RANS method to conduct a joint simulation of the core engine. The aerodynamic performance and temperature distribution of high-pressure turbines with film cooling are analyzed, and compared with the calculation results of a single component. The result shows that the calculation parameters of the turbine components are evenly distributed, and the core machine calculation shows non-uniform parameter characteristics, which are mainly reflected in temperature and change more significantly with the development of the mainstream. Under similar flow conditions, the temperature distribution of IGVs is mainly determined by the inlet temperature boundary conditions. By changing the physical properties of the turbine and the cold air, the flow condition remains almost unchanged, while the effect on Mach number below 2%, and the temperature value changes above 6% at leading edge and pressure side part, and the distribution trend remains unchanged.

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