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Effect of fouling, thermal barrier coating degradation and film cooling holes blockage on gas turbine engine creep life

机译：燃气涡轮发动机蠕变寿命污垢，热阻挡涂层降解和薄膜冷却孔阻塞的效果

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Gas turbines are sometimes operated in very hostile conditions due to service exigencies. These environments are characterized by degradation modes such as fouling, thermal barrier coating degradation and blockage of cooling holes which affect the creep life of engines. Therefore this paper presents a performance-based creep life estimation model capable of predicting the impact of different forms of degradation on the creep life of gas turbines. The model comprises performance, thermal, stress, and life estimation models. High pressure turbine blade was selected as the life limiting component of the gas turbine; therefore the integrated model was employed to investigate the effect of engine degradation on the creep life of a high pressure turbine blade of an aero derivative model gas turbine engine using a Creep Factor approach. The results shows that engine degradation affect the performance of gas turbine component which in turn affect their creep life.
机译：由于服务需求，燃气轮机有时在非常敌对的条件下运行。这些环境的特征在于污垢模式，例如污垢，热障涂层劣化和影响发动机蠕变寿命的冷却孔堵塞。因此，本文介绍了一种基于性能的蠕变寿命估计模型，其能够预测不同形式的降解对燃气轮机蠕变寿命的影响。该模型包括性能，热，应力和寿命估计模型。选择高压涡轮机叶片作为燃气轮机的寿命限制部件;因此，采用综合模型来研究发动机劣化对航空衍生模型燃气涡轮发动机高压涡轮机叶片的蠕变寿命的影响，使用蠕变因子方法。结果表明，发动机劣化影响燃气轮机部件的性能，这反过来影响其蠕变寿命。

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