Study on Performance of Pre-cooling Turbine-Based Combined Cycle Engine

As Turbine-based combined cycle engine (TBCC) can make full use of the atmosphere layer air and has good economic and technical feasibilities, it is the main power plant of future hypersonic vehicle. However, as a combined cycle propulsion device which combines aspirating and turbine engine highly integrated, the thrust gap of TBCC engine on mode transition is the most critical technology challenges of application. Therefore, the pre-cooling engine Geometries are analyzed and optimized via the working principle of turbine engine, instead of optimizing them directly. Based on the analysis, this paper researches the method of expanding the upper limit of turbine engine working Mach number. Results show that, when the temperature of inlet export air decreases 135k because of pre-cooling, the airflow of the engine can increase obviously. Thus, the turbine engine installed performance improves greatly to realize the requirements of aerospace vehicle.