Numerical simulation of parallel turbo-ramjet combined cycle propulsion system installed performance

摘要

To investigate the installed performance of turbine based combined cycle engines, parallel configuration was selected as a turbo-ramjet engine. Work process and selection of transition Mach number of turbo-ramjet were described. Both installed losses and installed performance computational model were established. Accordingly, the installed performance characteristics of turbofan-ramjet were simulated by numerical methods on basis of this model. As the numerical simulation results, in transonic and low supersonic conditions, installation losses are larger than other conditions, and the installed thrust which is continuous during the process of mode transition is decreased along flight trajectory. The specific fuel consumption is increased in trend while the specific impulse which is decreased in trend along the flight trajectory. The simulation results show that the installed performance is acceptable and considerable. In conclusion, we state that the scheme design of parallel configuration of turbo-ramjet engine is reasonable and feasible.