TY - GEN
T1 - Numerical simulation of parallel turbo-ramjet combined cycle propulsion system installed performance
AU - Wang, Yongsheng
AU - Wang, Zhanxue
AU - Liu, Zengwen
AU - Ma, Huimin
PY - 2010
Y1 - 2010
N2 - 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.
AB - 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.
KW - Installed performance
KW - Mode transition
KW - Numerical simulation
KW - Turbo-ramjet engine
UR - https://www.scopus.com/pages/publications/79952129149
U2 - 10.1109/ISSCAA.2010.5633031
DO - 10.1109/ISSCAA.2010.5633031
M3 - 会议稿件
AN - SCOPUS:79952129149
SN - 9781424460441
T3 - ISSCAA2010 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics
SP - 158
EP - 162
BT - ISSCAA2010 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics
T2 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics, ISSCAA2010
Y2 - 8 June 2010 through 10 June 2010
ER -