航天推进技术研究院主办
LI Long-fei,WANG Yan-tao,YANG Wei-dong,et al.Thermal energy storage heater and its key technologies for supersonic combustion ground test facilities[J].Journal of Rocket Propulsion,2012,38(02):16-19.
超声速燃烧地面试验的蓄热式加热器及其关键技术
- Title:
- Thermal energy storage heater and its key technologies for supersonic combustion ground test facilities
- 文章编号:
- 1672-9374(2012)02-0016-05
- 分类号:
- V235-34
- 文献标志码:
- A
- 摘要:
- 为了模拟飞行状态下进入超燃冲压发动机燃烧室的高焓空气,在地面模拟试验中需要对空气加热,可再生蓄热式加热器是一种能提供相对纯净高焓空气的试验设备。介绍了蓄热式加热器的工作原理与特点,分析了关键技术。结果表明,蓄热式加热器具有加热空气总温高、流量大和相对纯净的优点,是我国超燃冲压发动机地面试验的发展趋势,但蓄热阵材料、加热器结构、超高温阀和大范围调节预热燃烧器等是关键技术,有待进一步研究和攻关。
- Abstract:
- In order to simulate the air temperature in the combustion chamber of scramjet, the air used by the ground simulation test should be heated. This paper presents the design specification of a cored brick storage heater, which can supply high temperature clean air to meet the demands of supersonic combustion experiments. Key technologies of developing thermal energy storage heater are analyzed. The results show that with proper material and structural design, it is possible to use a thermal energy storage heater to obtain clean air flow of Mach 6. However, real performance of materials, the heater structure, the ultra high-temperature valve and gas generator still need to be studied to solve the remaining issues in the thermal energy storage heater.
相似文献/References:
[1]朱舒扬.全尺寸超燃冲压发动机推力测量台架研制[J].火箭推进,2015,41(05):106.
ZHU Shuyang.Development of thrust measurement platform
for full-scale scramjet[J].Journal of Rocket Propulsion,2015,41(02):106.
[2]姚照辉,李光熙,张蒙正,等.燃油分配对超燃冲压发动机的性能影响仿真分析[J].火箭推进,2013,39(04):30.
YAO Zhao-hui,LI Guang-xi,ZHANG Meng-zheng,et al.Simulation and analysis for influence of fuel distribution on scramjet performance[J].Journal of Rocket Propulsion,2013,39(02):30.
[3]刘 昊,李光熙,杜 泉,等.超燃冲压发动机全流道反应流场仿真分析[J].火箭推进,2013,39(06):1.
LIU Hao,LI Guang-xi,DU Quan,et al.Numerical simulation of reaction flow field in full flowpath of scramjet[J].Journal of Rocket Propulsion,2013,39(02):1.
[4]张 倩,王 兵,张耘隆,等.RBCC的可实现性方案—DRBCC分析[J].火箭推进,2014,40(05):1.
ZHANG Qian,WANG Bing,ZHANG Yun-long,et al.An analysis of RBCC realizability scheme: DRBCC[J].Journal of Rocket Propulsion,2014,40(02):1.
[5]赵宏亮,张蒙正.超燃冲压发动机推阻力特性研究综述[J].火箭推进,2014,40(06):41.
ZHAO Hong-liang,ZHANG Meng-zheng.Investigation of thrust/drag property of scramjet[J].Journal of Rocket Propulsion,2014,40(02):41.
[6]张蒙正,邹 宇.美国典型高超飞行器项目研发及启示[J].火箭推进,2012,38(02):1.
ZHANG Meng-zheng,ZOU Yu.Development of American typical hypersonic flight vehicles and its enlightenment[J].Journal of Rocket Propulsion,2012,38(02):1.
[7]文 科,李旭昌,马岑睿,等.不同入口马赫数对超燃冲压发动机尾喷管的性能影响研究[J].火箭推进,2011,37(03):18.
WEN Ke,LI Xu-chang,MA Cen-rui,et al.Influence of nozzle inlet Mach number on performance of scramjet nozzle[J].Journal of Rocket Propulsion,2011,37(02):18.
[8]冯锦虎,高峰,何至林.超燃冲压发动机隔离段内附面层/激波串相互干扰研究[J].火箭推进,2010,36(02):5.
Feng Jinhu,Gao Feng,He Zhilin.Investigation of boundary layer/shock wave train interference in a scramjet isolator[J].Journal of Rocket Propulsion,2010,36(02):5.
[9]王玉峰,吴宝元,王东东.变比热对超燃冲压发动机尾喷管设计的影响分析[J].火箭推进,2010,36(02):43.
Wang Yufeng,Wu BaoYuan,Wang Dongdong.Scramjet engine nozzle design with variable specific heat[J].Journal of Rocket Propulsion,2010,36(02):43.
[10]杨事民,唐豪,黄胡.凹腔超声速燃烧室氢气燃烧流场数值模拟[J].火箭推进,2008,34(01):12.
Yang Shimin,Tang Hao,Huang Yue.Numerical simulation of hydrogen combustion on
flow field in supersonic combustor with cavity[J].Journal of Rocket Propulsion,2008,34(02):12.
备注/Memo
收稿日期:2011-09-22;修回日期:2011-10-25
基金项目:国防基础科研项目(B0320110012)
作者简介:李龙飞(1977—),男,高级工程师,研究领域为液体动力系统喷雾燃烧技术