旁路放气循环高速单轴涡喷发动机安装性能模拟

The turbine engine installed performance simulation model based on the inlet/exhaust system characteristics database was developed, and an approach to model the compressor bypass bleed was proposed, for a Mach 3.5 single-shaft turbojet engine with bypass bleed cycle. The effects of compressor bypass bleed on the compressor work line and engine thrust performance under high-altitude high-speed conditions were analyzed, the adjustment principle for the compressor bypass bleed was put forward, and variation of the engine installed performance and inlet/exhaust system installation drags along the flight trajectory was simulated. The simulation results show that the compressor bypass bleed should be opened when the flight Mach number exceeds 2.3, and both the valve area and air mass flow of the bypass duct are essentially proportional to the flight Mach number. Through the compressor bypass bleed, the stability and installed thrust performance of the single-shaft turbojet under high-altitude high-speed conditions were significantly improved, and the installed thrust can be increased by more than 30% at the flight Mach number of about 3.0. The installation loss of thrust is maximized, about 25%~30% of the uninstalled thrust, between transonic speeds to the flight Mach number of 2.0.