Rongqian Chen , Yangcan Huang , Chengxiang Zhu , Ruofan Qiu , Yancheng You
DoI Number XXX-YYY-ZZZ
Conference Number HiSST 2018_41601152
Hypersonic flight is regarded as the third “revolution” in the history of aeronautical development following the propeller propulsion and the jet propulsion, which is the commanding height of aerospace technology in the twenty-first century. The core of hypersonic technology is propulsion technology. At present, it cannot satisfy full-speed flight of a hypersonic vehicle from the level to the supersonic speed depend on a single turbine or a ramjet. The combined cycle engine composed of turbine and ramjet is referred to as Turbo-Based Combined Cycle (TBCC) engine, which is a potential power form to achieve full-speed flight. When TBCC engine is switched from turbine-based mode to ramjet mode, there is an insufficient thrust problem called “thrust traps”. Rockets can be used to ensure the continuity of the thrust during the modal transformation process. In this paper, a common exhaust system is designed for this type of multi-channel TBCC power system consisting of a turbine, a scramjet, and an ejector rocket. The scramjet channel is designed first using an asymmetric single expansion ramp nozzle, while the turbine and rocket channel using Laval nozzles. The exhaust gas of these two channels flows into the scramjet nozzle. Throat area of the turbine nozzle and the rocket nozzle can be adjusted according to the flow requirements. Numerical simulations show that the proposed method can be used to design a common nozzle that meets thrust requirements of hypersonic vehicles for the full-speed flight.