斜爆轰发动机的推力性能理论分析

杨鹏飞; 张子健; 杨瑞鑫; 滕宏辉; 姜宗林

doi:10.6052/0459-1879-21-206

斜爆轰发动机的推力性能理论分析

doi: 10.6052/0459-1879-21-206

杨鹏飞^{*, †},
张子健^{*, **},
杨瑞鑫^{*, †},
滕宏辉^††,,
姜宗林^{*, †}

*.
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
†.
中国科学院大学工程科学学院, 北京 100049
**.
香港理工大学航空与民航工程学系, 香港九龙 999077
††.
北京理工大学宇航学院, 北京 100081

基金项目: 国家自然科学基金资助项目(11822202)

详细信息

作者简介:
滕宏辉, 教授, 主要研究方向: 爆轰物理及其应用. E-mail: hhteng@bit.edu.cn

中图分类号: V439, O381
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- 被引次数: 0
出版历程
- 收稿日期: 2021-05-13
- 录用日期: 2021-08-23
- 网络出版日期: 2021-08-24
- 刊出日期: 2021-10-26

THEORICAL STUDY ON PROPULSIVE PERFORMANCE OF OBLIQUE DETONATION ENGINE

Yang Pengfei^{*, †},
Zhang Zijian^{*, **},
Yang Ruixin^{*, †},
Teng Honghui^{††
,},
Jiang Zonglin^{*, †}

*.
State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
†.
School of Engineering Sciences, University of Chinese Academy of Sciences, Beijing 100049, China
**.
Department of Aeronautical and Aviation Engineering, The Hong Kong Polytechnic University, Kowloon 999077, Hong Kong, China
††.
School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

摘要

摘要: 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.
- 斜爆轰波 /
- 发动机 /
- 推力性能 /
- 燃烧模式
Abstract: 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.
- oblique detonation wave /
- engine /
- propulsive performance /
- combustion mode

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图 1 斜爆轰发动机原理图

Figure 1. Schematic diagram of the oblique detonation engine

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图 2 斜爆轰发动机4个典型工作过程示意图

Figure 2. Schematics of four typical processes in oblique detonation engine

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图 3 斜爆轰发动机燃烧室内复杂流动波系

Figure 3. Complex flow structures in a combustor of oblique detonation engine

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图 4 分析软件流程图

Figure 4. The flowchart of performance analysis software

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图 5 等动压飞行条件下, 燃料比冲I_sp和飞行马赫数Ma随着飞行高度H的变化(动压q = 57.9 kPa)

Figure 5. Fuel specific impulse I_sp and flight Mach number Ma as a function of flight altitude H with a constant dynamic pressure q = 57.9 kPa

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图 6 燃料比冲I_sp随(a)飞行高度H和(b)飞行马赫数Ma的变化, (a) Ma = 12, (b) H = 35 km

Figure 6. Fuel specific impulse I_sp as a function of (a) flight altitude H and (b) fuel specific impulse I_sp as a function of flight Mach number Ma. (a) Ma = 12, (b) H = 35 km

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图 7 燃料比冲I_sp随着(a)楔面角度θ和(b)当量比φ的变化

Figure 7. Fuel specific impulse I_sp as a function of (a) wedge angle θ and (b) fuel specific impulse I_sp as a function of equivalence ratio φ

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图 8 燃料比冲I_sp随(a)进气压缩角度δ₂和(b)尾喷管膨胀面积比ε_ex的变化

Figure 8. Fuel specific impulse I_sp as a function of (a) inlet angle δ₂ and (b) fuel specific impulse I_sp as a function of expansion ratio ε_ex

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图 9 起爆区长度L和燃烧室入口温度T随飞行马赫数Ma的变化

Figure 9. Initiation length L and entrance temperature T as a function of inflow Mach number Ma

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表 1 4个工作过程的物理模型和关键参数

Table 1. Physical models and key parameters of four modules

Process	Physical model	Key parameters
compression	multi-wedges	δ₁, δ₂, ···, δ_n
mixing	parallel jets	φ, T_t, p_t
heat release	detonation/constant-volume combustion	Ma_c, θ
exhaust	isentropic expansion with a varying specific heat	ε_ex

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表 2 默认参数下不同燃烧模式的燃料比冲

Table 2. Fuel specific impulse with the default engine parameters

Combustion modes	I_sp/s
OV-ODW	1480.1
CJ-ODW	1927.3
OV-NDW	697.2
SIC-CVC	1865.8

下载: 导出CSV

表 3 不同燃烧模式下燃烧产物的状态

Table 3. States of combustion product with different combustion modes

Combustion modes	p/kPa	T/K	U/(m·s⁻¹)	σ
OV-ODW	268.9	3103.5	2817.7	0.162
CJ-ODW	129.5	2848.2	3168.1	0.178
OV-NDW	798.9	3768.7	496.8	0.003
SIC-CVC	372.4	3136.7	2970.3	0.278

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