Design of a film cooled dual-bell nozzle
The design of a film cooled dual-bell nozzle is presented. The nozzle is part of a thrust chamber assembly that adopts an existing LOX/GH2 thrust chamber. The dual-bell base nozzle, including the gaseous hydrogen cooling film injection, is a downscaled redesign of an already tested film cooled TIC n...
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| Veröffentlicht in: | Acta astronautica 2019-05, Vol.158, p.342-350 |
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| container_title | Acta astronautica |
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| creator | Stark, Ralf Génin, Chloé Mader, Christian Maier, Dietmar Schneider, Dirk Wohlhüter, Michael |
| description | The design of a film cooled dual-bell nozzle is presented. The nozzle is part of a thrust chamber assembly that adopts an existing LOX/GH2 thrust chamber. The dual-bell base nozzle, including the gaseous hydrogen cooling film injection, is a downscaled redesign of an already tested film cooled TIC nozzle. Future hot flow tests at the test facility P8 will study the impact of a ROF variation and a cooling film mass flow variation on the operation mode transition of the dual-bell. For this reason, a homogeneous hot flow and cooling film distribution are mandatory. To meet those demands, extensive numerical studies were performed and design optimizations were derived. The test specimen will be operated under sea level conditions.
•Dual bell rocket nozzle with supersonic hydrogen cooling film.•Numerical study on coaxial injector head hydrogen inflow position.•Numerical study on cooling film layer mass flow distribution.•Impact of cooling film mass flow and ROF on dual-bell nozzle transition.•ALM gives new possibilities in design, fluid management and sensor application. |
| doi_str_mv | 10.1016/j.actaastro.2018.05.056 |
| format | Article |
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•Dual bell rocket nozzle with supersonic hydrogen cooling film.•Numerical study on coaxial injector head hydrogen inflow position.•Numerical study on cooling film layer mass flow distribution.•Impact of cooling film mass flow and ROF on dual-bell nozzle transition.•ALM gives new possibilities in design, fluid management and sensor application.</description><identifier>ISSN: 0094-5765</identifier><identifier>EISSN: 1879-2030</identifier><identifier>DOI: 10.1016/j.actaastro.2018.05.056</identifier><language>eng</language><publisher>Elmsford: Elsevier Ltd</publisher><subject>Additive layer manufacturing ; Cooling ; Design ; Design optimization ; Dual-bell nozzle ; Film cooling ; Hydrogen ; Injector head ; Liquid oxygen ; Mass flow ; Nozzles ; Numerical simulation ; Redesign ; Rocket engine ; Rockets ; Sea level ; Thrust chambers</subject><ispartof>Acta astronautica, 2019-05, Vol.158, p.342-350</ispartof><rights>2018 IAA</rights><rights>Copyright Elsevier BV May 2019</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c343t-359e460da4eaf0770199017e88ceeccdea4bc188570c76043565e1cf3b9634643</citedby><cites>FETCH-LOGICAL-c343t-359e460da4eaf0770199017e88ceeccdea4bc188570c76043565e1cf3b9634643</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://dx.doi.org/10.1016/j.actaastro.2018.05.056$$EHTML$$P50$$Gelsevier$$H</linktohtml><link.rule.ids>314,778,782,3539,27911,27912,45982</link.rule.ids></links><search><creatorcontrib>Stark, Ralf</creatorcontrib><creatorcontrib>Génin, Chloé</creatorcontrib><creatorcontrib>Mader, Christian</creatorcontrib><creatorcontrib>Maier, Dietmar</creatorcontrib><creatorcontrib>Schneider, Dirk</creatorcontrib><creatorcontrib>Wohlhüter, Michael</creatorcontrib><title>Design of a film cooled dual-bell nozzle</title><title>Acta astronautica</title><description>The design of a film cooled dual-bell nozzle is presented. The nozzle is part of a thrust chamber assembly that adopts an existing LOX/GH2 thrust chamber. The dual-bell base nozzle, including the gaseous hydrogen cooling film injection, is a downscaled redesign of an already tested film cooled TIC nozzle. Future hot flow tests at the test facility P8 will study the impact of a ROF variation and a cooling film mass flow variation on the operation mode transition of the dual-bell. For this reason, a homogeneous hot flow and cooling film distribution are mandatory. To meet those demands, extensive numerical studies were performed and design optimizations were derived. The test specimen will be operated under sea level conditions.
•Dual bell rocket nozzle with supersonic hydrogen cooling film.•Numerical study on coaxial injector head hydrogen inflow position.•Numerical study on cooling film layer mass flow distribution.•Impact of cooling film mass flow and ROF on dual-bell nozzle transition.•ALM gives new possibilities in design, fluid management and sensor application.</description><subject>Additive layer manufacturing</subject><subject>Cooling</subject><subject>Design</subject><subject>Design optimization</subject><subject>Dual-bell nozzle</subject><subject>Film cooling</subject><subject>Hydrogen</subject><subject>Injector head</subject><subject>Liquid oxygen</subject><subject>Mass flow</subject><subject>Nozzles</subject><subject>Numerical simulation</subject><subject>Redesign</subject><subject>Rocket engine</subject><subject>Rockets</subject><subject>Sea level</subject><subject>Thrust chambers</subject><issn>0094-5765</issn><issn>1879-2030</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2019</creationdate><recordtype>article</recordtype><recordid>eNqFkEtLw0AUhQdRsFZ_gwE3bhLvZN7LUp9QcKPrYTq5kQlpps6kgv31plTcCgfO5pxzuR8h1xQqClTedZXzo3N5TLGqgeoKxCR5QmZUK1PWwOCUzAAML4WS4pxc5NwBgKq1mZHbe8zhYyhiW7iiDf2m8DH22BTNzvXlGvu-GOJ-3-MlOWtdn_Hq1-fk_fHhbflcrl6fXpaLVekZZ2PJhEEuoXEcXQtKATUGqEKtPaL3DTq-9lRrocArCZwJKZD6lq2NZFxyNic3x91tip87zKPt4i4N00lb11RqA1zTKaWOKZ9izglbu01h49K3pWAPWGxn_7DYAxYLYpKcmotjE6cnvgImm33AwWMTEvrRNjH8u_EDq0Rtng</recordid><startdate>201905</startdate><enddate>201905</enddate><creator>Stark, Ralf</creator><creator>Génin, Chloé</creator><creator>Mader, Christian</creator><creator>Maier, Dietmar</creator><creator>Schneider, Dirk</creator><creator>Wohlhüter, Michael</creator><general>Elsevier Ltd</general><general>Elsevier BV</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>7TG</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>KL.</scope><scope>L7M</scope></search><sort><creationdate>201905</creationdate><title>Design of a film cooled dual-bell nozzle</title><author>Stark, Ralf ; Génin, Chloé ; Mader, Christian ; Maier, Dietmar ; Schneider, Dirk ; Wohlhüter, Michael</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c343t-359e460da4eaf0770199017e88ceeccdea4bc188570c76043565e1cf3b9634643</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2019</creationdate><topic>Additive layer manufacturing</topic><topic>Cooling</topic><topic>Design</topic><topic>Design optimization</topic><topic>Dual-bell nozzle</topic><topic>Film cooling</topic><topic>Hydrogen</topic><topic>Injector head</topic><topic>Liquid oxygen</topic><topic>Mass flow</topic><topic>Nozzles</topic><topic>Numerical simulation</topic><topic>Redesign</topic><topic>Rocket engine</topic><topic>Rockets</topic><topic>Sea level</topic><topic>Thrust chambers</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Stark, Ralf</creatorcontrib><creatorcontrib>Génin, Chloé</creatorcontrib><creatorcontrib>Mader, Christian</creatorcontrib><creatorcontrib>Maier, Dietmar</creatorcontrib><creatorcontrib>Schneider, Dirk</creatorcontrib><creatorcontrib>Wohlhüter, Michael</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Meteorological & Geoastrophysical Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Meteorological & Geoastrophysical Abstracts - Academic</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Acta astronautica</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Stark, Ralf</au><au>Génin, Chloé</au><au>Mader, Christian</au><au>Maier, Dietmar</au><au>Schneider, Dirk</au><au>Wohlhüter, Michael</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Design of a film cooled dual-bell nozzle</atitle><jtitle>Acta astronautica</jtitle><date>2019-05</date><risdate>2019</risdate><volume>158</volume><spage>342</spage><epage>350</epage><pages>342-350</pages><issn>0094-5765</issn><eissn>1879-2030</eissn><abstract>The design of a film cooled dual-bell nozzle is presented. The nozzle is part of a thrust chamber assembly that adopts an existing LOX/GH2 thrust chamber. The dual-bell base nozzle, including the gaseous hydrogen cooling film injection, is a downscaled redesign of an already tested film cooled TIC nozzle. Future hot flow tests at the test facility P8 will study the impact of a ROF variation and a cooling film mass flow variation on the operation mode transition of the dual-bell. For this reason, a homogeneous hot flow and cooling film distribution are mandatory. To meet those demands, extensive numerical studies were performed and design optimizations were derived. The test specimen will be operated under sea level conditions.
•Dual bell rocket nozzle with supersonic hydrogen cooling film.•Numerical study on coaxial injector head hydrogen inflow position.•Numerical study on cooling film layer mass flow distribution.•Impact of cooling film mass flow and ROF on dual-bell nozzle transition.•ALM gives new possibilities in design, fluid management and sensor application.</abstract><cop>Elmsford</cop><pub>Elsevier Ltd</pub><doi>10.1016/j.actaastro.2018.05.056</doi><tpages>9</tpages></addata></record> |
| fulltext | fulltext |
| identifier | ISSN: 0094-5765 |
| ispartof | Acta astronautica, 2019-05, Vol.158, p.342-350 |
| issn | 0094-5765 1879-2030 |
| language | eng |
| recordid | cdi_proquest_journals_2216890481 |
| source | ScienceDirect Journals (5 years ago - present) |
| subjects | Additive layer manufacturing Cooling Design Design optimization Dual-bell nozzle Film cooling Hydrogen Injector head Liquid oxygen Mass flow Nozzles Numerical simulation Redesign Rocket engine Rockets Sea level Thrust chambers |
| title | Design of a film cooled dual-bell nozzle |
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