超燃冲压发动机燃烧室主动冷却设计研究

推进技术 ›› 2014, Vol. 35 ›› Issue (2): 208-212.

超燃冲压发动机燃烧室主动冷却设计研究

杨样¹,张磊²,张若凌¹,蒋劲¹,赵国柱¹

中国空气动力研究与发展中心高超中心,四川绵阳 621000;西南交通大学机械工程学院,四川成都 610000;中国空气动力研究与发展中心高超中心,四川绵阳 621000;中国空气动力研究与发展中心高超中心,四川绵阳 621000;中国空气动力研究与发展中心高超中心,四川绵阳 621000

发布日期:2021-08-15
作者简介:杨样(1979—),男,博士,副研究员,研究领域为超燃冲压发动机主动冷却技术。 E-mail:yang_cardc@163.com

Design Research of an Actively Fuel-Cooled Scramjet Combustor

Air-breating Hypersonic Technology Research Center,China Aerodynamics Research and Development Center, Mianyang 621000,China;School of Mechanical Engineering, Southwest Jiaotong University, Chengdu 610000, China;Air-breating Hypersonic Technology Research Center,China Aerodynamics Research and Development Center, Mianyang 621000,China;Air-breating Hypersonic Technology Research Center,China Aerodynamics Research and Development Center, Mianyang 621000,China;Air-breating Hypersonic Technology Research Center,China Aerodynamics Research and Development Center, Mianyang 621000,China

Published:2021-08-15

摘要/Abstract

摘要： 超燃冲压发动机燃烧室主动冷却模型制造和热考核试验的费用高昂、周期长,为了降低试验风险,采用三维计算和经济的验证试验相结合的方法开展了超燃冲压发动机燃烧室主动冷却设计。冷却结构基本参数设计和侧壁冷却流动设计是确定设计方案的两大基础,前者采用三维传热计算结合冷却面板传热验证试验完成,后者采用超临界燃料流动三维并行计算结合水流动验证试验完成。在此基础上,经过多轮的结构设计与三维传热及强度计算评估迭代,确定了最终的燃烧室主动冷却结构。设计的主动冷却燃烧室在来流马赫数2.5,总温1700K条件下成功通过200s热考核试验,表明所采用的设计方法、验证试验和计算工具是有效和可信的。 

关键词: 超燃冲压发动机;燃烧室;主动冷却;传热;设计 

Abstract: In order to reduce risk of scramjet combustor heat transfer test which is expensive and time-consuming, a method with combination of calculation tools and inexpensive verification tests was adopted to design a typically fuel-cooled scramjet combustor. Basic cooling parameters design and flow structure design for side-wall are the two foundations of the design. The former was accomplished by three-dimensional thermal evaluation combined with heat transfer characteristic tests of fuel-cooled panels, while the latter was accomplished by three-dimensional parallel computation of flow for supercritical fuel combined with water-flowing tests of panels. After several rounds of structural design and three-dimensional thermo-structure calculation, the entire active cooling structure of the combustor was determined. The actively fuel-cooled combustor withstood heat transfer tests with the longest duration of 200s at the entrance condition of Mach 2.5and total temperature of 1700K. Test results show that the proposed design method, inexpensive verification test and computation tools are effective and credible. 

Key words: Scramjet; Combustor; Active cooling; Heat transfer; Design

杨样,张磊,张若凌,蒋劲,赵国柱. 超燃冲压发动机燃烧室主动冷却设计研究[J]. 推进技术, 2014, 35(2): 208-212.

YANG Yang¹, ZHANG Lei², ZHANG Ruo-ling¹, JIANG Jin¹, ZHAO Guo-zhu¹. Design Research of an Actively Fuel-Cooled Scramjet Combustor[J]. Journal of Propulsion Technology, 2014, 35(2): 208-212.

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