{"id":16939,"date":"2024-05-24T12:12:39","date_gmt":"2024-05-24T12:12:39","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=16939"},"modified":"2025-09-15T13:26:50","modified_gmt":"2025-09-15T13:26:50","slug":"characterizations-of-combustion-destabilization-in-an-axisymmetric-supersonic-cavity-based-combustor","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/05\/24\/characterizations-of-combustion-destabilization-in-an-axisymmetric-supersonic-cavity-based-combustor\/","title":{"rendered":"Characterizations of Combustion Destabilization in an Axisymmetric Supersonic Cavity-based Combustor"},"content":{"rendered":"\n<p><strong>Qinyuan LI, Bo YAN, Mingbo SUN, Jiajian ZHU, Yifu TIAN, Minggang WAN, Tiangang LUO, Yongchao SUN<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2024-149<\/strong><\/p>\n\n\n\n<p>Three-dimensional characterizations and evolution laws of the flame structure during combustion<br>destabilization in an axisymmetric supersonic combustor were investigated. The multi-view OH-PLIF<br>imaging system was used to visualize the instantaneous flame structures distributing at multiple<br>typical cross-sections of a fully transparent axisymmetric supersonic glass combustor. The high-speed<br>photography and pressure measurement systems were employed to assist in the analysis of the flame<br>structure evolution during combustion destabilization. The experiments were conducted with an<br>inflow speed of Mach 2.5 and a total temperature of 1800 K. The global equivalence ratios (GER)<br>were 0.12, 0.15, 0.21 and 0.26, respectively. It was found that a loop-shaped flame with a central<br>hole is an essential flame structure characterization in the axisymmetric supersonic combustor. The<br>flame loop mainly distributes near the cavity shear-layer, and the instantaneous structure fluctuates<br>over time. There is the most intense combustion and thickened flame near the cavity ramp. As GER<br>exceeds 0.21, an excessive enhanced combustion induces thermal choking. The flame propagates<br>upstream away from the cavity along the boundary-layer near the jet wake. It leads to a violent<br>reciprocal flame propagation, marking an unsteady combustion. The thermal choking initiates near<br>the ramp where the most intense combustion occurs. The local flame loop is significantly expanded,<br>filling almost the entire flow path. The loop-shaped flame structure downstream the combustor is<br>affected slightly due to a low-speed and thickened cavity shear-layer. In contrast, the flame structure<br>near the middle part of the combustor is disrupted severely. A diffused and fragmented flame loop<br>fluctuates violently over time. A large amount of fragmented flames spread into the core flow<br>occasionally.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/05\/HiSST-2024-149.pdf\">Read the full paper here<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Qinyuan LI, Bo YAN, Mingbo SUN, Jiajian ZHU, Yifu TIAN, Minggang WAN, Tiangang LUO, Yongchao SUN<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: HiSST-2024-149<\/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":[1643,1642,858,614],"class_list":["post-16939","post","type-post","status-publish","format-standard","hentry","category-events","category-11-hisst-2024","category-propulsion-systems-and-components-11-hisst-2024","tag-axisymmetric-supersonic-combustor","tag-combustion-destabilization","tag-combustion-oscillation","tag-scramjet","category-993","category-1407","category-1414","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16939","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=16939"}],"version-history":[{"count":2,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16939\/revisions"}],"predecessor-version":[{"id":20887,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16939\/revisions\/20887"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=16939"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=16939"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=16939"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}