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为了使航空发动机达到高推质比、低燃油消耗率、低污染以及拓宽稳定工作范围的目标,应使用涡轮导向器增燃技术在涡轮导向器叶片间喷油点火再次燃烧,提高涡轮内燃气温度,从而提高发动机的总体性能.阐述了涡轮导向器增燃技术具有提高航空发动机总体性能的潜在优势,分析研究了该技术中组织燃烧的关键技术、参数和机理问题,得出如下结论:①对于射流旋流方案,径向凹槽对燃烧室出口温度分布起决定性作用;降低燃烧凹环内当量比,可提高燃烧效率,从而降低CO,UHC(未燃碳氢化合物),NOx等污染物排放量.②当二次气流角为60°时,射流涡流方案各项燃烧性能较好.
In order to achieve a high thrust-to-mass ratio, low fuel consumption rate, low pollution and a wide range of stable working range for aeroengines, a turbocharging combustion technology should be used to ignite and re-combust the fuel between the turbine guide blades to increase the gas temperature in the turbine , So as to improve the overall performance of the engine.This paper describes the potential advantages of turbo-guide combustion technology to improve the overall performance of aeroengine, analyzes the key technologies, parameters and mechanism of the combustion in this technology, and draws the following conclusions: Jet cyclone scheme and radial groove play a decisive role in the outlet temperature distribution of the combustion chamber. Reducing the equivalence ratio in the combustion concave ring can improve the combustion efficiency and reduce the emission of CO, UHC (unburned hydrocarbon), NOx and other pollutants ② When the secondary air flow angle is 60 °, the combustion performance of the jet vortex scheme is better.