基于典型飞行任务的 CCA 技术优势分析

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‑en‑gine 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 about 16. 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， maxi‑ mum climb rate，maximum Mach number，service lift limit and range.