基于涡轮导向器增燃技术的总体性能与燃烧组织  

Overall performance and combustion organization based on turbine inter-vane burning technology

作　　者：郑海飞[1] 唐豪[1] 李明[2] 莫妲[3] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航空工业集团公司空天发动机研究院有限公司,北京100009 [3]中国航空工业集团公司沈阳发动机设计研究所,沈阳110015

出　　处：《航空动力学报》2014年第5期1053-1061,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(51076064);江苏省"六大人才高峰"第五批高层次人才项目(2008136);江苏省普通高校研究生科研创新计划(CXLX12_0152);中央高校基本科研业务费专项资金

摘　　要：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.The turbine inter-vane burning technology was applied to achieve the purpose of high thrust-weight ratio,low specific fuel consumption,low pollution and expanded stable working range of aero-engine.For this purpose,the burner placed between the turbine vanes was reheated to increase the gas temperature in the turbine,and then improve the overall performance of aero-engine.This works elaborated the potential advantage of the turbine inter-vane burning technology of enhancing the aero-engine overall performance based on overall thermodynamic cycle performance analysis,helping to research key technology,parameters and mechanism problem about combustion in this technology.And it is observed that：（1）for the jet-swirl scheme,radial vane cavity plays a decisive role in temperature distribu-tion at the exit of combustor,and combustion efficiency can be improved by reducing the equivalence ratio in combustion ring cavity while leading to lower pollutant emissions quantity of CO,UHC（unburned hydrocarbon）,NOx;（2）the jet-vortex scheme has better combustion performance when the secondary jet-flow angle is 60degrees.

关 键 词：涡轮导向器增燃 航空发动机 总体性能 射流旋流 射流涡流 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]