Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions

doi:10.1007/s10409-015-0503-9

	Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions
	Tian L; Chen LH(陈立红); Chen Q(陈强); Zhong FQ(仲峰泉); Zhang XY(张新宇); Chen, LH (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
发表期刊	ACTA MECHANICA SINICA
	2016
卷号	32 期号:1 页码:75-82
ISSN	0567-7718
摘要	A dual-mode scramjet can operate in a wide range of flight conditions. Higher thrust can be generated by adopting suitable combustion modes. Based on the net thrust, an analysis and preliminary optimal design of a kerosene-fueled parameterized dual-mode scramjet at a crucial flight Mach number of 6 were investigated by using a modified quasi-one-dimensional method and simulated annealing strategy. Engine structure and heat release distributions, affecting the engine thrust, were chosen as analytical parameters for varied inlet conditions (isolator entrance Mach number: 1.5-3.5). Results show that different optimal heat release distributions and structural conditions can be obtained at five different inlet conditions. The highest net thrust of the parameterized dual-mode engine can be achieved by a subsonic combustion mode at an isolator entrance Mach number of 2.5. Additionally, the effects of heat release and scramjet structure on net thrust have been discussed. The present results and the developed analytical method can provide guidance for the design and optimization of high-performance dual-mode scramjets. A dual-mode scramjet can achieve high thrust in a wide range of flight conditions. The present work uses modified quasi-1-D analysis model and simulated annealing strategy to investigate the engine performance of kerosene-fueled parameterized dual-mode scramjet at a crucial flight Mach number of 6. Engine structure and heat release distributions were optimized to obtain optimal engine net thrust for varied inlet conditions. The highest net thrust can be achieved by subsonic combustion mode at an isolator entrance Mach number of 2.5. The present results and analytical method can provide guidance for the design and optimization of high-performance dual-mode scramjets.
关键词	Dual-mode Scramjet Engine Performance Thrust Optimization Heat Release Distribution Simulated Annealing Algorithm
DOI	10.1007/s10409-015-0503-9
URL	查看原文
收录类别	SCI ; EI ; CSCD
语种	英语
WOS记录号	WOS:000371242000007
关键词[WOS]	Dual-mode scramjet ; Engine performance ; Thrust ; Optimization ; Heat release distribution ; Simulated annealing algorithm
WOS研究方向	Engineering ; Mechanics
WOS类目	Engineering, Mechanical ; Mechanics
项目资助者	This work was supported by the National Natural Science Foundation of China (Grant 11002148).
CSCD记录号	CSCD:5660709
课题组名称	LHD高超声速推进技术
论文分区	二类
引用统计	被引频次：6[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/59514
专题	高温气体动力学国家重点实验室
通讯作者	Chen, LH (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
推荐引用方式 GB/T 7714	Tian L,Chen LH,Chen Q,et al. Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions[J]. ACTA MECHANICA SINICA,2016,32,1,:75-82.
APA	Tian L,陈立红,陈强,仲峰泉,张新宇,&Chen, LH .(2016).Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions.ACTA MECHANICA SINICA,32(1),75-82.
MLA	Tian L,et al."Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions".ACTA MECHANICA SINICA 32.1(2016):75-82.

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