并联TBCC可调进气道并联方案  

Parallel plans for TBCC variable geometry inlet

作　　者：孙波[1] 邵庆龄 倪凯捷 卓长飞[1] 张堃元[3] 

机构地区：[1]南京理工大学航空宇航系,南京210094 [2]中国航天科工集团公司南京电子设备研究所,南京210016 [3]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2017年第12期2988-2996,共9页Journal of Aerospace Power

基　　金：江苏省自然科学基金(BK20150781)

摘　　要：对并联涡轮基组合循环(TBCC)可调进气道并联方案进行了归纳分析,提出了一种分类方法和两种并联方案。对4种典型并联方案在马赫数为2.5的模态转换工况进行了稳态仿真分析。结果表明:后开纯内并联方案在模态转换过程中总流量变化很小,其余3种的总流量系数随着涡轮通道的关闭都是逐渐减小的,涡轮通道流量系数逐渐降低,冲压通道升高。4种方案冲压通道流量系数在模态转换过程中均是逐渐升高的,后开纯内并联方案具有最低的冲压通道平均流量系数,变化幅度最大,其余3种方案变化幅度均较小。前开纯外并联和混合式内并联两种方案的涡轮通道出口总压恢复在模态转换过程中呈减小趋势,另外两种方案的总压恢复呈略微增大趋势,其中前开纯外并联平均总压恢复最低,而混合式内并联方案的平均总压恢复最高。With analysis on parallel plan for parallel turbine based combined cycle（TBCC）inlets,a method for classification and a type of parallel plan were proposed.Numerical simulations were conducted for four types of parallel plan inlet during the mode transition at Mach number of 2.5.Results showed that total mass flow rate kept nearly constant for pure internal parallel plan,contributing to stable thrust during mode transition;total mass flow rate decreased for other three plans.Pure external-parallel inlet with back door had the lowest mass flow rate of ramjet channel with a large change,other three plans had a small change.Total pressure recovery at turbine channel exit increased from a lower initial levelduring mode transition for pure internal plan;it decreased evidently from a high initial level for external parallel plan,but decreased within a narrow range for mixed internal plan.

关 键 词：涡轮基组合循环(TBCC) 可调进气道 并联方案 模态转换 涡轮通道 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]