| 新建高焓激波风洞Ma=8飞行模拟条件的实现与超燃实验 |
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| 引用本文： | 卢洪波,陈星,谌君谋,易翔宇,李辰,张冰冰,纪锋,毕志献,沈清. 新建高焓激波风洞Ma=8飞行模拟条件的实现与超燃实验[J]. 气体物理, 2019, 4(5): 13-24. DOI: 10.19527/j.cnki.2096-1642.0782 |
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| 作者姓名： | 卢洪波 陈星 谌君谋 易翔宇 李辰 张冰冰 纪锋 毕志献 沈清 |
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| 作者单位： | 中国航天空气动力技术研究院，北京 100074 |
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| 摘 要： | 针对高Mach数超燃冲压发动机实验能力空缺问题，基于航天十一院新建的FD-21高能脉冲风洞，进行了Ma=8超燃飞行条件的模拟能力设计与调试，获得了总焓2.9 MJ/kg、总压11.01 MPa实验条件，实现了Ma=8、高度31 km飞行条件的风洞模拟.在此基础上，研发了匹配的氢燃料供应及喷注时序控制系统，设计了超燃冲压发动机模型，开展了超燃冲压发动机模型自由射流应用性风洞实验，获得了氢气燃料与空气、氮气超声速气流耦合流动作用下的实验模型壁面压力数据.在当量比近似一致条件下，空气来流对应的燃烧室壁面压力明显高于氮气来流情况，表明氢气在1 ms有效实验时间内完成了与超声速空气来流的混合、点火与燃烧，获得燃烧释热特性，确认了在FD-21高能脉冲风洞开展高Mach数超燃实验是切实可行的，为后续研究奠定了良好的基础.
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| 关 键 词： | 高能脉冲风洞 Ma=8飞行条件复现 超燃实验 燃料供应系统 高Mach数自由射流实验 |
| 收稿时间： | 2019-06-28 |
Flight Condition Achievement of Mach Number 8 in a New Shock Tunnel of CAAA and its Scramjet Experimental Investigation |
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| Affiliation: | China Academy of Aerospace Aerodynamics, Beijing 100074, China |
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| Abstract: | Aimed at the lack of experimental conditions of high-Mach-number scramjet, the ability to simulate flight conditions of Mach number 8 was explored in FD-21 high-energy shock tunnel of CAAA. The simulation in total enthalpy of 2.9 MJ/kg and total pressure of 11.01 MPa was obtained, duplicating a flight Mach number of 8 at the altitude of 31 km. Furthermore, experimental techniques of hydrogen combustion were developed. A hydrogen fuel supply system with the time sequencer was equipped. A semi-free jet test model was designed to examine the possibility of scramjet test in FD-21 shock tunnel and check the performance of fuel supply system. Several commissioning tests were conducted at the Ma=8 simulation conditions. A comparison of wall pressure distributions between different test gas experiments with the almost identical hydrogen injection mass flow rate was made. It is shown that a pronounced pressure increment is observed in the downstream of the hydrogen injection location, while only a slight difference exists in the upstream of the hydrogen injection location. These phenomena indicate the achievement of hydrogen mixing, igniting and burning in supersonic airflow, which verifies the feasibility of scramjet test in FD-21 shock tunnel. The present achievements are helpful for experimental investigation of high-Mach-number scramjet. |
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