A new kind of gas turbine cycle with exhaust gas recirculation and water injection is analyzed and optimized in this paper. Thus the effect of main thermodynamic parameters on the performance of this cycle and optimum efficiency can be obtaind. The minimum temperature difference has also been discussed.
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.
