DC Field | Value | Language |
---|---|---|
dc.contributor.author | Chang, Eric Won Keun | ko |
dc.contributor.author | Yang, Sungmo | ko |
dc.contributor.author | Park, Gisu | ko |
dc.contributor.author | Choi, Hojin | ko |
dc.date.accessioned | 2018-08-20T08:06:39Z | - |
dc.date.available | 2018-08-20T08:06:39Z | - |
dc.date.created | 2018-07-09 | - |
dc.date.created | 2018-07-09 | - |
dc.date.created | 2018-07-09 | - |
dc.date.issued | 2018-09 | - |
dc.identifier.citation | AEROSPACE SCIENCE AND TECHNOLOGY, v.80, pp.413 - 423 | - |
dc.identifier.issn | 1270-9638 | - |
dc.identifier.uri | http://hdl.handle.net/10203/244947 | - |
dc.description.abstract | In this work, ethylene flame-holding in supersonic flows was investigated using a shock tunnel. The experiments were conducted at flow stagnation temperatures ranging from 1270 to 1810 K. The two-dimensional test model consisted of a double-ramp inlet and a constant-area combustor with a recessed wall cavity. The two fuel injectors were located at the inlet and the other upstream of the cavity. Shadowgraph and flame chemiluminescence images were captured for optical visualization. The inlet injection images showed various flame-holding patterns. At 1270 K, the flame was not maintained. At 1540 K, the flame was maintained inside the cavity, and the condition provided continuous combustion during the steady flow. At 1810 K, strong flame signals were observed from the inlet to the cavity and downstream. At 1540 K, the inlet injection with a low fuel pressure showed a gradual flame quenching in the cavity during flow establishment. On the other hand, the same injection in the combustor showed flame-holding in the shear layer above the cavity. The results showed that the flame patterns are strongly influenced by the flow stagnation temperature and the location of fuel-injection. | - |
dc.language | English | - |
dc.publisher | ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER | - |
dc.subject | CAVITY-STABILIZED FLAMES | - |
dc.subject | SUPERSONIC CROSS-FLOWS | - |
dc.subject | SCRAMJET COMBUSTOR | - |
dc.subject | SHOCK-TUNNEL | - |
dc.subject | FUEL-INJECTION | - |
dc.subject | MACH 8 | - |
dc.subject | IGNITION | - |
dc.subject | INLET | - |
dc.subject | ESTABLISHMENT | - |
dc.subject | HYDROCARBONS | - |
dc.title | Ethylene Flame-Holding in Double Ramp Flows | - |
dc.type | Article | - |
dc.identifier.wosid | 000445991100035 | - |
dc.identifier.scopusid | 2-s2.0-85050882742 | - |
dc.type.rims | ART | - |
dc.citation.volume | 80 | - |
dc.citation.beginningpage | 413 | - |
dc.citation.endingpage | 423 | - |
dc.citation.publicationname | AEROSPACE SCIENCE AND TECHNOLOGY | - |
dc.identifier.doi | 10.1016/j.ast.2018.07.012 | - |
dc.contributor.localauthor | Park, Gisu | - |
dc.contributor.nonIdAuthor | Chang, Eric Won Keun | - |
dc.contributor.nonIdAuthor | Yang, Sungmo | - |
dc.contributor.nonIdAuthor | Choi, Hojin | - |
dc.description.isOpenAccess | N | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordAuthor | Scramjet | - |
dc.subject.keywordAuthor | Inlet injection | - |
dc.subject.keywordAuthor | Cavity flame-holding | - |
dc.subject.keywordAuthor | Shock tunnel | - |
dc.subject.keywordPlus | CAVITY-STABILIZED FLAMES | - |
dc.subject.keywordPlus | SUPERSONIC CROSS-FLOWS | - |
dc.subject.keywordPlus | SCRAMJET COMBUSTOR | - |
dc.subject.keywordPlus | SHOCK-TUNNEL | - |
dc.subject.keywordPlus | FUEL-INJECTION | - |
dc.subject.keywordPlus | MACH 8 | - |
dc.subject.keywordPlus | IGNITION | - |
dc.subject.keywordPlus | INLET | - |
dc.subject.keywordPlus | ESTABLISHMENT | - |
dc.subject.keywordPlus | HYDROCARBONS | - |
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.