With the increase of the turbineinlettemperature of high performance aero-engine day by day, the turbine coating blade coating technology has been widely used.
随着高性能航空发动机涡轮进口温度日益提高，涂层技术在涡轮叶片上得以广泛应用。
2
This paper introduces the parameter estimation research for the turbineinlettemperature and compressor exit pressure by using the engine variables measured under the different flight conditions.
本文研究利用不同飞行状态下测量的发动机变量估计涡轮进口温度和压气机出口压力。
3
The performance of a gas turbine is related to environmental temperatures and its output decreases with the increase of gas inlettemperature, which can be solved by cooling the inlet gas.