串联式TBCC发动机模态转换模拟  

Analysis of Mode Transition Simulation of Co-axial and Tandem Configuration TBCC Engine

作　　者：王玉男[1] 胡秋晨 贾琳渊[2] 张彦军[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015 [2]西北工业大学动力与能源学院,西安710072

出　　处：《航空发动机》2015年第2期22-26,共5页Aeroengine

基　　金：国家重大基础研究项目资助

摘　　要：为开展涡轮基组合循环(TBCC)发动机模态转换过程研究,基于某小型涡喷发动机,应用串联式TBCC发动机总体性能数值计算程序进行性能计算。根据沿飞行轨道TBCC发动机冲压涵道与涡轮发动机涵道气流混合过程中的参数变化规律,开展模态转换过程模拟。分析了不同等动压头、加力/冲压燃烧室进口马赫数、出口温度等主要参数对发动机性能的影响。根据小型串联式TBCC发动机模态转换过程和沿飞行轨道的发动机稳态特性模拟,确定了较为合理的模态转换区间,并得到了推力、耗油率等发动机性能参数。研究表明:不同动压头对应不同的模态转换马赫数,加力/冲压燃烧室进口马赫数和出口总温对模态转换马赫数并无影响。In order to investigate the turbo/ramjet mode transition of TBCC engines, the performance calculations were conducted using overall performance numerical calculation program of co-axial and tandem configuration TBCC engine based on a monotype turbojet. According to the flight orbit, the thermodynamic parameters variation of ram duct and turbine duct during mode transition were studied. The influences of main parameters on engine performance were analyzed, which include different dynamic head,inlet Maeh number of afterburner,outlet temperature , etc, More reasonable mode transition regions were determined based on the simulation of mode transition process and the steady performance of the TBCC engine along the track. The thrust, oil consumption rate, performance parameters were obtained. The researches show that different dynamic heads are corresponding to different Mach number of mode transition,while the inlet Mach number and exit total temperature of after/ramjet burner have no influence on the Mach number.

关 键 词：涡轮基组合循环发动机 性能模拟 模态转换 涡轮发动机 冲压发动机 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]