纯净空气来流的超音速燃烧室试验与数值模拟研究  

Numerical Simulation and Experiments of Supersonic Combustion in Pure Air Stream

作　　者：肖隐利[1] 宋文艳[1] 陈亮[1] 冯喜平[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]西北工业大学航天工程学院,西安710072

出　　处：《机械科学与技术》2008年第9期1231-1235,共5页Mechanical Science and Technology for Aerospace Engineering

基　　金：西北工业大学博士论文创新基金项目(W016107)资助

摘　　要：超音速燃烧室试验设备需要加热空气达到所模拟的飞行状态的总焓,采用电阻加热器可以提供纯净的来流空气。西北工业大学建立了采用连续式电阻加热器的超音速燃烧室直连式试验平台。设备的初步调试结果显示:该电阻加热器最高可将流量0.73 kg/s的来流空气加热至1000 K,可以利用该平台进行低飞行马赫数的超音速燃烧室试验研究。本文利用该试验平台进行了超音速来流条件下的氢气燃烧试验研究,并在此基础上开展了氢气燃烧的数值模拟研究,数值模拟结果和试验结果吻合较好。： A unique supersonic wind tunnel facility has been built at the Supersonic Combustion Laboratory of Northwestern Polytechnical University to simulate the operation of a scramjet over a range of Mach numbers of 3 to 4. 5. The facility can provide clean air with high stagnation temperature up to 1000 K and mass flow rate of 0. 73 kg/s to the scramjet combustor using resistance heaters. In this paper, we present a number of preliminary experimental resuits in calibrating the resistance heaters. The ignition characteristics of the hydrogen have been investigated in the supersonic clean airstreams experimental facility with resistance heaters. In addition, numerical simulation of hydrogen supersonic combustion is performed, and the results are in good agreement with the experimental results.

关 键 词：超音速燃烧室 电阻加热器 纯净空气 超音速燃烧 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]