摘要
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.
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.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
1997年第2期145-148,共4页
Journal of Engineering Thermophysics
基金
国家自然科学基金
攀登B资助
