Analysis of energy saving and thrust characteristics of rotating detonation turbine engine

Abstract

The carbon emissions caused by the aviation industry are an urgent problem that requires attention. Efficient energy utilisation and control of pollutants and greenhouse gas emissions are future development trends. This study was conducted to systematically derive the formulae for cycle thermal efficiency, practical cycle work, fuel consumption, and unit thrust of rotating detonation aspirated turbojet, of separated exhaust turbofan and hybrid exhaust turbofan engines. The fuel consumption rate and unit thrust performance of different types of engines under diverse pressure ratio ranges were discussed based on two research methods. (I) In the first method the influence of the pressure ratio of the rotating detonation combustor to the total pressure ratio on the cycle parameters was examined under a constant total pressure ratio. It was found that the unit thrust performance of the rotating detonation turbine engine can be significantly improved if the fuel consumption was increased by less than 30% in the medium- and high-pressure ratio range. (II) Second, the existing parameters of the conventional turbine engine were maintained (compressor pressure ratio unchanged) and the influence of combustion chamber pressure ratio on engine performance was examined. The results show that under specific combustion chamber pressure ratios, within the range of medium and high-pressure ratios, the unit thrust performance of a rotating detonation turbine engine can be combined with energy-saving characteristics, which resulted in an improvement of up to four times or greater. Simultaneously, the fuel consumption rate was decreased by 20% or greater. Therefore, the rotating detonation turbine engine exhibits considerable application potential and can reduce energy consumption and improve engine performance.