Integrated Performance Numerical Simulation Of Turbo-ramjet

As a hypersonic propulsion system, turbo-ramjet received recognition because of the widely flight envelope and excellent performance such as Isp. Based on a future reusable hypersonic aerospace vehicle, a hypersonic air-breathing propulsion system is studied in this dissertation.Based on Quicksat concept which was described as a hypersonic vehicle in early reference, structure, shape, weight and flight trajectory are given according to mission. All of these are the foundation of this study.The arrangement of turbine based combined cycle engines are investigated. Finally, co-axial and tandem configuration was selected as the turbofan-ramjet combined engine. Based on a modular structure program, the performance characteristic of turbo-ramjet is simulated by numerical method. According to the modular synthesis program, the design parameters of the turbofan and ramjet are presented after a particular research on selection and calculation of thermodynamic parameters. In this paper, the turbo-ranjet's performance characteristic along the flight trajectory is also calculated by numerical simulation software which is developed by Jet Propulsion Group of NWPU.Inlet and exhaust system are very important for performance of propulsion system, based on equal shock intensity method, a hypersonic mix-pressure inlet is designed and the regulation is described in this dissertation. In addition, an SREN with linear extend afterbody is designed.Because of highly integration of hypersonic vehicle/air-breathing propulsion system, installation losees should not be ignored. The installation losees including spillage, bleed, bypass, and nozzle drag are calculated by engineering method.