Abstract: On the basis of an aero-engine performance emulation model，a turbine cooling algorithm was employed to calculate the cooling flow and the resulting decrease in turbine efficiency. The influence of turbine cooling technology on aero-engine performance was analyzed with regards to different cooling means and different levels of cooling technology. The results show that among all cooling means considered，the convection film cooling offers the best general performance with favorable specific thrust，thermal efficiency and specific fuel consumption. And as for the convection film cooling，when the required cooling flow and incidental turbine efficiency loss are reduced by 20%，the specific fuel consumption drops by 0.9% and the specific thrust boosts by 3%.

Key words: Aero-engine；Turbine cooling algorithm；Cooling means；Levels of cooling technology

摘要： 为了分析不同涡轮冷却方式以及冷却技术水平对航空发动机性能的影响，建立了航空发动机性能仿真模型，引入了考虑冷气用量以及冷却附带效率损失的涡轮冷却算法。计算结果表明:在相同的热力循环参数下，对流气膜冷却对应的发动机单位推力、热效率以及耗油率均较为良好，综合表现最佳；就对流气膜冷却而言，若冷气用量以及冷却附带效率损失均减少20%，则发动机耗油率降低0.9%，单位推力提高3%。

关键词: 航空发动机；涡轮冷却算法；冷却方式；冷却技术水平