{"id":17341,"date":"2024-06-07T09:28:48","date_gmt":"2024-06-07T09:28:48","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=17341"},"modified":"2025-09-21T13:27:06","modified_gmt":"2025-09-21T13:27:06","slug":"numerical-study-of-reactive-flow-dynamics-in-a-hydrogen-fueled-direct-connect-scramjet-combustor-depending-on-number-of-injector","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/06\/07\/numerical-study-of-reactive-flow-dynamics-in-a-hydrogen-fueled-direct-connect-scramjet-combustor-depending-on-number-of-injector\/","title":{"rendered":"Numerical Study of Reactive Flow dynamics in a Hydrogen-fueled Direct-Connect Scramjet Combustor depending on Number of Injector"},"content":{"rendered":"\n<p><strong>Seung-Min JEONG, Jae-Eun KIM, Jeong-Yeol CHOI<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: 10.82241\/ceas-hisst-2024-350<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2024-350<\/strong><\/p>\n\n\n\n<p>This study numerically investigated the reactive flow dynamics of a laboratory-scale gaseous hydrogenfueled scramjet combustor depending on a number of injectors. The main goal of the present study is not only to investigate a flame structure and combustion dynamics by changing fueling schemes but also to reveal the effect of injector schemes on combustion performance. A numerical simulation was performed using an improved delayed detached eddy turbulent model (IDDES) and Jachimowski\u2019s hydrogen-air reaction mechanism. The simulation utilized high-order accuracy-based numerical schemes to ensure high-resolution and fidelity results. For a quantitative comparison of the effect of injector schemes, single and multi-injectors with five equivalence ratio cases in one set were considered. Numerical results found an intricate coupled fluid-combustion dynamics and its transition depending on the number of injectors and global equivalence ratio. Comprehensive numerical results showed completely different fluid-combustion dynamics by injector schemes. Specifically, a counter-rotating vortex pair of the multi-injector case was not maintained, resulting in decreased fuel\/air mixing and combustion. Due to this phenomenon induced by an interaction between the injector-injector and injector-wall surface, it was revealed that the combustion efficiency is significantly reduced for the multi-injector compared to the single-injector under the same global equivalence ratio. These findings indicated that increasing the number of injectors cannot guarantee an increase in the mixing and combustion performance of a scramjet combustor.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/06\/HiSST-2024-350.pdf\">Read the full paper here<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Seung-Min JEONG, Jae-Eun KIM, Jeong-Yeol CHOI<\/b><\/p>\n<p>DOI Number: https:\/\/doi.org\/10.82241\/ceas-hisst-2024-350<\/p>\n<p>Conference number: HiSST-2024-350<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,1407,1414],"tags":[1910,1527,1530,1909],"class_list":["post-17341","post","type-post","status-publish","format-standard","hentry","category-events","category-11-hisst-2024","category-propulsion-systems-and-components-11-hisst-2024","tag-combustion-performance","tag-direct-connect-scramjet-combustor","tag-high-resolution-numerical-simulation","tag-number-of-injector","category-993","category-1407","category-1414","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17341","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\/2"}],"replies":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/comments?post=17341"}],"version-history":[{"count":4,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17341\/revisions"}],"predecessor-version":[{"id":21206,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17341\/revisions\/21206"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=17341"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=17341"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=17341"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}