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文摘
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爆轰燃烧具有释热快、循环热效率高的特点.斜爆轰发动机利用斜爆轰波进行燃烧组织,在高超声速吸气式推进系统中具有重要地位.以往研究主要关注斜爆轰波的起爆、驻定以及波系结构等,缺少从整体层面出发对斜爆轰发动机开展推力性能分析.本文将斜爆轰发动机内的流动和燃烧过程分解成进气压缩、燃料掺混、燃烧释热和排气膨胀4个基本模块并分别进行理论求解,建立了斜爆轰发动机推力性能的理论分析模型.在斜爆轰波系研究成果的基础上,选取了过驱动斜爆轰、Chapman-Jouguet斜爆轰、过驱动正爆轰和斜激波诱导等容燃烧等4种燃烧模式来描述燃烧室内的燃烧释热过程,并对比分析了不同燃烧模式对发动机比冲性能的影响.此外,还获得了不同来流参数、燃烧室参数和进排气参数等对发动机推力的影响规律,发现来流马赫数和尾喷管的膨胀面积比是发动机理论燃料比冲的主要影响因素.最后,结合以往关于受限空间内斜爆轰波驻定特性等方面的研究成果,提出了斜爆轰发动机燃烧室的设计方向. |
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其他语种文摘
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Detonation combustion is characterized by the high thermodynamic efficiency and fast heat release.Benefitting from these potential advantages,an oblique detonation wave (ODW) is introduced into the combustion chamber and oblique detonation engine (ODE) plays an important role in hypersonic air-breathing propulsion systems.Previous studies mainly focused on the initiation structures,standing features and wave systems of oblique detonation,but the global analysis of ODE propulsive performance is still absent at the macro-level.In this paper,the flow and combustion processes of an ODE are decomposed into four basic modules,named as inlet model,mixing model,combustion mode and nozzle model,respectively.We solve these four basic flow processes using theoretical methods and propose a systematically theoretical approach that can be used to predict the ODE propulsion performance.On the basis of previous ODW initiation structures and waves systems,four different combustion modes,i.e.,over-driven ODW,Chapman-Jouguet ODW,over-driven normal detonation wave and oblique shock-induced constant-volume combustion,are chosen to describe the heat release processes of combustible mixture in the ODE combustor.The effects of different combustion modes on fuel specific impulse of the ODE are also analyzed.In addition,the influence mechanisms of inflow parameters,combustor parameters and intake-exhaust parameters on the thrust performance of ODE are also obtained,and the results show that the major factor of fuel specific impulse of an ODE consists mainly of the inflow Mach number and the expansion ratio of engine nozzle.Finally,combined with precious detonation research results,such as the standing features and initiation structures of oblique detonation in a confined space,the preliminary design direction of oblique detonation engine are proposed,which mainly involve some constrained conditions,such as geometrical constraints,inflow velocity limitations and stability ranges of a detonation wave in ODE combustor. |
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来源
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力学学报
,2021,53(10):2853-2864 【核心库】
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DOI
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10.6052/0459-1879-21-206
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关键词
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斜爆轰波
;
发动机
;
推力性能
;
燃烧模式
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地址
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1.
中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京, 100190
2.
中国科学院大学工程科学学院, 北京, 100049
3.
香港理工大学航空与民航工程学系, 香港, 999077
4.
北京理工大学宇航学院, 北京, 100081
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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0459-1879 |
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学科
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力学;航天(宇宙航行) |
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基金
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国家自然科学基金
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文献收藏号
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CSCD:7098632
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