Performance analysis of the continuous rotating detonation aero-turbine engine

摘要

For the future demand of high performance airbreathing propulsion system for civil or military aircrafts, a continuous rotating detonation aero-turbine engine (RDATE) system is conducted in this paper. Composed mainly of an annular detonation combustor and a set of turbomachinery, the propulsion system combines the advantages of gas turbine and rotating detonation engines. Based on the analysis of the working processes of the propulsion system, the mathematical models of the working processes of the engine and the parametric cycle analysis model are established. On basis of the analysis model, the overall performance as well as the effects of flight conditions (the flight Mach number M_0 and the flight altitude H) on the overall performance of the engine is investigated. The results show that the parametric cycle analysis model is reasonable for estimating the overall performance of the RDATE. A C_8H_(18) fueled RDATE can reach a specific thrust of 1283 N·s/kg and a thermal efficiency of 0.46 with the compressor pressure ratio π_c=8.0 and the combustor outlet temperature T_4~*=2000K under the standard sea-level conditions (M_0=0).