主燃烧室采用增压燃烧的涡扇发动机热力过程和性能分析

Thermodynamic Process and Performance Analysis of Turbofan Engine with PGC in Main Combnstion Chamber

为了研究主燃烧室采用增压燃烧(PGC)的涡扇发动机性能,建立了其热力循环过程计算模型,采用考虑增压特性的传统涡扇发动机性能计算方法,分析了增压比、涡轮前温度、涵道比、飞行速度、飞行高度等循环参数对增压燃烧涡扇发动机的性能影响,并与传统涡扇发动机的性能进行了对比评估。结果表明:增压燃烧发动机循环效率高于等压燃烧发动机的,且加热比越大,增压燃烧发动机性能优势越明显。初步获得了不同循环参数对增压燃烧涡扇发动机的性能影响规律。与同参数的传统涡扇发动机相比,在总增压比为25~45、涡轮前温度为1500~1800 K内,增压燃烧涡扇发动机的单位推力增大4.7%~8.6%,耗油率降低4.6%~8.5%;在飞行高度为15 km、马赫数为0~3内,增压燃烧涡扇发动机的推力增大4.1%~27.6%,耗油率降低2.3%~11.4%,并且飞行马赫数越高,增压燃烧涡扇发动机的性能优势越大。

A thermodynamic cycle calculation model was developed to study the performance of a turbofan engine with Pressure Gain Combustion(PGC)in the main combustor.By using the traditional turbofan engine performance calculation method considering pressure gain characteristics,the influences of the parameters such as overall pressure ratio,turbine inlet temperature,bypass ratio,speed and al⁃titude on the overall performance of the turbofan engine with PGC were studied,and compared with that of the traditional turbofan engine.The results show that the cycle efficiency of the engine with PGC is higher than that of the engine with isobaric combustion.And the higher the heating ratio,the more obvious the performance advantage of the turbofan engine with PGC.The effect of different cycle parameters on the turbofan engine with PGC was preliminarily obtained.Compared with the traditional turbofan engine with the same parameters,within the overall pressure ratio of 25 to 45 and the turbine inlet temperature of 1500 to1800 K,the specific thrust of turbofan engine with PGC in⁃creases by 4.7%to 8.6%and the specific fuel consumption reduces by 4.6%to 8.5%.At the flight altitude of 15 km and Mach number of 0 to 3,the specific thrust of the turbofan engine with PGC increases by 4.1%to 17.1%and the specific fuel consumption reduces by 4.5%to 11.4%.Moreover,the higher the flight Mach number,the greater the performance advantage of the turbofan engine with PGC.