TBCC内涵流动模拟试验模型设计及研究  

Design and Experimental Study of Simulation Internal Bypass Flow Model for TBCC

作　　者：程晓军[1] 范育新[1] 宫继双[1] 韩启祥[1] 王家骅[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2013年第2期219-224,共6页Journal of Propulsion Technology

基　　金：江苏省普通高校研究生科研创新计划资助项目(CXZZ12_0167)

摘　　要：涡轮基组合循环发动机因其性能优越性,已引起世界各研究机构的广泛关注。为了模拟TBCC的试验条件,提供符合核心机条件的高温燃气是必要手段。本文设计了一个结构简单易于控制的TBCC核心射流试验模拟模型,并对此模型进行了实验研究。结果表明,所设计模型点火工作可靠,燃烧效率高,可以产生0.236～0.342kg/s的750～1050K的高温燃气,模型出口马赫数、温度和氧气的体积分数分布均匀,可以满足TBCC超级燃烧室试验进口条件要求。Turbine-based combined cycle has attracted widespread attention in the global research institutions because of its superior performance.In order to simulate the TBCC test conditions,it is necessary to provide the qualified high temperature gas.A simple and easy control simulation model of TBCC core jet was designed and experimentally studied.The results indicate that the model can provide reliable ignition,high combustion efficiency,and high temperature gas of 0.236～0.342kg/s from 750～1050K.The uniform distribution of outlet Mach number,temperature and oxygen volume fraction could meet the requirements of TBCC super combustion chamber test.The results provide strong technical support for the design and study of the core components of the TBCC combustion chamber mixer and flame stabilizer.

关 键 词：涡轮基组合循环发动机 核心射流 燃烧效率 当量比 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]