{"id":16189,"date":"2024-04-12T12:09:06","date_gmt":"2024-04-12T12:09:06","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=16189"},"modified":"2024-04-12T12:09:07","modified_gmt":"2024-04-12T12:09:07","slug":"experimental-investigation-of-transpiration-cooling-in-a-subscale-combustion-chamber-with-non-reactive-flow","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/04\/12\/experimental-investigation-of-transpiration-cooling-in-a-subscale-combustion-chamber-with-non-reactive-flow\/","title":{"rendered":"Experimental Investigation of Transpiration Cooling in a Subscale Combustion Chamber with Non-Reactive Flow"},"content":{"rendered":"\n<p><strong>Jonas Peichl, Andreas Schwab, Markus Selzer, Hannah B\u00f6hrk, Jens von Wolfersdor<\/strong><\/p>\n\n\n\n<p><strong>DOI Number XXX-YYY-ZZZ<\/strong><\/p>\n\n\n\n<p><strong>Conference Number HiSST-2022-231<\/strong><\/p>\n\n\n\n<p>This paper presents the first results of a study of transpiration cooling in a segmented ceramic matrix<br>composite specimen resembling a subscale rocket engine combustion chamber. The tests were conducted with a hot air mainstream flow with a temperature of Thg = 800 K, and cold air as coolant. For<br>the first experiments, a variation of the blowing ratio of F = 0-0.75% was investigated, with constant<br>blowing over all segments. The increase of cooling efficiency with rising blowing ratio is demonstrated.<br>For the nozzle contoured segment, a significant increase of the wall temperature could be determined<br>for low blowing ratios, which can be attributed to cross-flows caused by the higher pressure gradient in<br>the expansion section.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-231.pdf\" data-type=\"link\" data-id=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/HiSST-2022-231.pdf\">Read the full paper > <\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Jonas Peichl, Andreas Schwab, Markus Selzer, Hannah B\u00f6hrk, Jens von Wolfersdor<\/b><\/p>\n<p>DOI Number XXX-YYY-ZZZ<\/p>\n<p>Conference Number HiSST-2022-231<\/p>\n","protected":false},"author":1,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,1006,1015],"tags":[1019,1148,500],"class_list":["post-16189","post","type-post","status-publish","format-standard","hentry","category-events","category-hisst-2022","category-thermal-and-energy-management-systems-hisst-2022","tag-ceramic-matrix-composites","tag-rocket-engine-combustion-chambers","tag-transpiration-cooling","category-993","category-1006","category-1015","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16189","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=16189"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16189\/revisions"}],"predecessor-version":[{"id":16190,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16189\/revisions\/16190"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=16189"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=16189"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=16189"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}