Inverse Cycle Engine (ICE) is one of the candidate schemes for hypersonic air breathingpropulsion. In this paper, we use the constant specific heat method and the chemical equilib-rium thermodynamic method to analyse the specific thrust and specific impulse performancesof ICE. We also compare ICE with a ramjet engine and a turbojet with after burner. Finally,we analyses the effect of some factors on the performance of ICE, such as the temperaturelimit of the main combustor, the temperature limit of the front combustor, equivalent ratio,turbine expand ratio, etc. Based on the analysis result, we can conclude that the specificthrust performance of ICE is better than that of a ramjet engine in rich fuel mode, especiallywhen Mach number is very low (<1.5) and very high (>4.5). Some other useful results isalso obtained.
The paper focuses on the turbo ramjet engine, which is a kind of airbreathing engine.It is expected to apply for hypersonic transport propulsion system. In the process fromturbo mode to ramjet mode, the turbo ramjet composed engine operates through the way ofcombined cycle. In this paper the combined cycle performance was simulated for two layouts.The results show that the laws are feasible.
