Numerical simulation on thrust reverser based on secondary flow for high-bypass-ratio turbofan engine

The study for thrust reverser based on secondary flow injection was carried out with the method of CFD (computational fluid dynamics). The two-dimensional flow field of thrust reversers with secondary flow injection was numerically simulated to study the effect of location of secondary injection, angle of secondary injection, total pressure ratio of secondary injection and total fan nozzle pressure ratio on the performance of the thrust reverser. The important parameter is cascade flow ratio, which is in direct proportion to reverse thrust. The results show that the configuration of flow field presented in this thesis is similar to the referenced flow field. Location and angle of injection with optimum values are important factors while the total pressure ratio of injection has a fitting value. Due to the limitation of secondary mass flow, the injection depth is finite, so the new reverse thrust concept can not be adopted by super high-bypass-ratio turbofan engines.