IMECH-IR  > 高温气体动力学国家重点实验室
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.
Source PublicationACTA MECHANICA SINICA
2016
Volume32Issue:1Pages:75-82
ISSN0567-7718
AbstractA 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.
KeywordDual-mode Scramjet Engine Performance Thrust Optimization Heat Release Distribution Simulated Annealing Algorithm
DOI10.1007/s10409-015-0503-9
URL查看原文
Indexed BySCI ; EI ; CSCD
Language英语
WOS IDWOS:000371242000007
WOS KeywordDual-mode scramjet ; Engine performance ; Thrust ; Optimization ; Heat release distribution ; Simulated annealing algorithm
WOS Research AreaEngineering ; Mechanics
WOS SubjectEngineering, Mechanical ; Mechanics
Funding OrganizationThis work was supported by the National Natural Science Foundation of China (Grant 11002148).
CSCD IDCSCD:5660709
DepartmentLHD高超声速推进技术
Classification二类
Citation statistics
Cited Times:4[WOS]   [WOS Record]     [Related Records in WOS]
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/59514
Collection高温气体动力学国家重点实验室
Corresponding AuthorChen, LH (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
Recommended Citation
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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