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。
This paper introduces the parameter estimation research for the turbine inlet temperature and compressor exit pressure by using the engine variables measured under the different flight conditions.
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。
With the increase of the turbine inlet temperature of high performance aero-engine day by day, the turbine coating blade coating technology has been widely used.
对四冲程柴油机增压系统的空气流量，排气温度、压气机出口压力和涡轮进口压力的若干种计算方法进行了分析。
Several calculating methods for determining the air-flow rate, the exhaust temperature, the compressor outlet pressure and the turbine inlet pressure are compared.
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