串联式涡轮冲压发动机加力/冲压燃烧室设计及流场计算  

Design and Flow Field Simulation of Tandem TBCC After-ramjet-burner

作　　者：李锋[1] 尚守堂[1,2] 郭瑞卿[1] 唐正府[1,2] 吕付国[1] 陈骏博 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2014年第1期22-25,共4页Aeroengine

基　　金：航天创新重点基金(CASC03);航天支撑基金(13131001)资助

摘　　要：以串联式TBCC加力/冲压燃烧室为研究对象,提出包含一体化整流支板、加力内锥及长短交错的径向火焰稳定器组成的TBCC加力/冲压燃烧室方案。针对TBCC发动机加力/冲压燃烧室进行了数值模拟,获得该燃烧室在不同模态下的流场特性。计算结果显示,在涡轮工作状态和涡轮/冲压共同工作状态下,TBCC发动机加力/冲压燃烧室的总压恢复系数均在95%左右;在冲压工作状态下,其总压恢复系数在86%左右。可以满足在不同模态下加力/冲压燃烧室对总压恢复系数的要求。Taking the tandem TBCC （Turbine Based Combined Cycle Engine）after-ramjet-burner as research object, the plan of TBCC after-ramjet-burner contained the integration rectifier plate, the cone and the flame holder was proposed, The flow characteristics of the TBCC after-ramjet-burner were obtained in the different model by numerical simulation. The simulation results show that the total pressure recovery coefficient is more than 95% when the afterburner work or the afterburner and ramjet-burner work together, the total pressure recovery coefficient is more than 86% when the ramjet-burner work alone. It can meet the requirement of the total pressure recovery coefficient for the TBCC after-ramjet-burner.

关 键 词：加力 冲压燃烧室 涡轮冲压发动机 组合动力装置 流场 总压恢复系数 数值模拟 

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]