{"id":16199,"date":"2024-04-12T12:16:56","date_gmt":"2024-04-12T12:16:56","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=16199"},"modified":"2024-04-12T12:16:56","modified_gmt":"2024-04-12T12:16:56","slug":"combustion-characteristics-of-a-supersonic-combustor-model-for-a-jaxa-flight-experiment","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/04\/12\/combustion-characteristics-of-a-supersonic-combustor-model-for-a-jaxa-flight-experiment\/","title":{"rendered":"Combustion Characteristics of a Supersonic Combustor Model for a JAXA Flight Experiment"},"content":{"rendered":"\n<p><strong>Masahiro Takahashi, Kan Kobayashi, Sadatake Tomioka<\/strong><\/p>\n\n\n\n<p><strong>DOI Number XXX-YYY-ZZZ<\/strong><\/p>\n\n\n\n<p><strong>Conference Number HiSST-2022-250<\/strong><\/p>\n\n\n\n<p>A flight-ground test comparison program is undergoing at JAXA to clarify so-called \u201cfacility effect\u201d on<br>hypersonic aerodynamics and combustion phenomena, and to develop a CFD tool, which can predict<br>actual data in flight from ground test data. The final goal is to conduct a flight experiment to obtain<br>data of aerodynamic heating and supersonic combustion in a real flight and to validate the CFD tool<br>using the flight data and corresponding ground test data. The present study is related to design of a<br>supersonic combustor flow-path suitable to clarify influence of differences in test flow composition<br>between flight and ground test conditions on combustion. The candidate configurations proposed by<br>CFD study were evaluated by direct-connect combustion tests with ethylene fuel. The results showed<br>that a combustor flow was symmetric when fuel equivalence ratio was low, while it became asymmetric<br>when the equivalence ratio became high and the pressure in the combustor rose. Such the asymmetric<br>flow is not suitable for the CFD validation so that the total equivalence ratio was limited. The upper<br>limit of the total equivalence ratio to maintain the symmetric combustor flow was 0.44 in the present<br>flow condition. The combustor model equipped two-stage fuel injectors and cavity flame holders to<br>obtain ethylene combustion. A depth of the cavity flame holder had little influence on combustion, but<br>the number of injection holes for the 2nd injector located downstream of the cavity affected the<br>combustor pressure. Based on the combustion test results, the combustor flow-path design was<br>finalized. In addition, an ethylene fuel ignition method using a pilot hydrogen injection, which is<br>adopted for the flight experiment, was also demonstrated successfully.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-250.pdf\" data-type=\"link\" data-id=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-250.pdf\">Read the full paper ><\/a> <\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Masahiro Takahashi, Kan Kobayashi, Sadatake Tomioka<\/b><\/p>\n<p>DOI Number XXX-YYY-ZZZ<\/p>\n<p>Conference Number HiSST-2022-250<\/p>\n","protected":false},"author":1,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,1006,1013],"tags":[442,977,585,1163,470],"class_list":["post-16199","post","type-post","status-publish","format-standard","hentry","category-events","category-hisst-2022","category-propulsion-systems-and-components-hisst-2022","tag-cfd","tag-flight-experiment","tag-ground-testing","tag-hydrocarbon-fuel","tag-supersonic-combustion","category-993","category-1006","category-1013","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16199","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/users\/1"}],"replies":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/comments?post=16199"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16199\/revisions"}],"predecessor-version":[{"id":16200,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16199\/revisions\/16200"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=16199"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=16199"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=16199"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}