基于典型飞行任务的CCA技术优势分析

Superiority analysis of CCA technology under typical flight mission

基于典型飞行任务,在F-119发动机方案的循环参数基础上,对采用冷却冷却空气(CCA)技术的航空发动机性能开展研究,分析CCA技术对发动机总体性能及涡轮叶片温度的影响规律,评估采用CCA技术的涡扇发动机对其所装配飞机的飞行性能的影响。结果表明:针对仅预冷高压涡轮动叶冷却气方案,当保持冷却空气流量不变时,采用CCA技术可将涡轮冷气温度降低16.98%~41.21%,使得高压涡轮动叶表面最高温度降低8.89%~16.80%;当保持叶片表面最高温度不变时,采用CCA技术可减少高压涡轮动叶48.61%的冷却用气,且发动机的推力和耗油率等总体性能基本不变;针对同时预冷高压涡轮导叶和动叶冷却气方案,通过调整循环参数,在保持冷却空气流量和叶片温度不变的前提下,可使涡轮前最高温度提高6.91%,从而提高典型飞行状态下的航发推进性能,进而有效提升所配装飞机的起飞载质量、最大爬升率、最大马赫数、使用升限及航程等飞行性能。

To improve the overall aero-engine performance under typical flight mission,superiority analysis of cooled cooling air(CCA)technology was proposed to upgrade the cooling quality of turbine blade cooling air.The effects of introducing CCA technology into the aero-engine performance and further the flight performance of the aircraft equipped with the engine with CCA were evaluated based on the reported cycle parameters of F-119.The following conclusion can be obtained:in the case of only cooling the cooling air for the turbine rotor blade,when the mass flow rate of the cooling air kept constant,its temperature can be reduced by about16.98%-41.21%,which lowered the rotor blade temperature by about 8.89%-16.80%.When the turbine blade temperature kept constant,the cooling air for turbine rotor blade can be reduced by about 48.61% and aero-engine performance maintained at the same level;in the case of cooling the cooling air for both the turbine stator and rotor blade,when the mass flow rate of the cooling air and turbine blade temperature kept constant,the turbine inlet temperature can be increased by about 6.91%,which can improve the propulsion performance of aero-engine,and eventually improve the flight performance of the aircraft,such as takeoff load mass,maximum climb rate,maximum Mach number,service lift limit and range.