Gap filler for a fuel system gallery
A nozzle assembly for a gas turbine engine, comprising: a nozzle at a downstream end of the assembly relative to fuel flow; a first and a second body upstream of the nozzle, the first body defining a first passage between a first inlet connectable to a source and a first outlet, and the second body...
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| creator | Swaby, Nadia Sreekanth, Sri |
| description | A nozzle assembly for a gas turbine engine, comprising: a nozzle at a downstream end of the assembly relative to fuel flow; a first and a second body upstream of the nozzle, the first body defining a first passage between a first inlet connectable to a source and a first outlet, and the second body defining a second passage between a second inlet and a second outlet in fluid communication with the nozzle, the inlets in fluid communication with each other; the bodies matingly engaged together along an axis, the inlets spaced apart relative to the axis to define a gallery having a depth in an axial direction and a width in a transverse direction; and a gap filler within the gallery, compressible in at least one of the directions, having an uncompressed dimension greater than a corresponding dimension of the gallery in the at least one of the directions. |
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| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US11466859B2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US11466859B2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US11466859B23</originalsourceid><addsrcrecordid>eNrjZFBxTyxQSMvMyUktUkjLL1JIVEgrTc1RKK4sLknNVUhPBElU8jCwpiXmFKfyQmluBkU31xBnD93Ugvz41OKCxOTUvNSS-NBgQ0MTMzMLU0snI2Ni1AAA3BYmjg</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Gap filler for a fuel system gallery</title><source>esp@cenet</source><creator>Swaby, Nadia ; Sreekanth, Sri</creator><creatorcontrib>Swaby, Nadia ; Sreekanth, Sri</creatorcontrib><description>A nozzle assembly for a gas turbine engine, comprising: a nozzle at a downstream end of the assembly relative to fuel flow; a first and a second body upstream of the nozzle, the first body defining a first passage between a first inlet connectable to a source and a first outlet, and the second body defining a second passage between a second inlet and a second outlet in fluid communication with the nozzle, the inlets in fluid communication with each other; the bodies matingly engaged together along an axis, the inlets spaced apart relative to the axis to define a gallery having a depth in an axial direction and a width in a transverse direction; and a gap filler within the gallery, compressible in at least one of the directions, having an uncompressed dimension greater than a corresponding dimension of the gallery in the at least one of the directions.</description><language>eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION APPARATUS ; COMBUSTION ENGINES ; COMBUSTION PROCESSES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2022</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20221011&DB=EPODOC&CC=US&NR=11466859B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20221011&DB=EPODOC&CC=US&NR=11466859B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Swaby, Nadia</creatorcontrib><creatorcontrib>Sreekanth, Sri</creatorcontrib><title>Gap filler for a fuel system gallery</title><description>A nozzle assembly for a gas turbine engine, comprising: a nozzle at a downstream end of the assembly relative to fuel flow; a first and a second body upstream of the nozzle, the first body defining a first passage between a first inlet connectable to a source and a first outlet, and the second body defining a second passage between a second inlet and a second outlet in fluid communication with the nozzle, the inlets in fluid communication with each other; the bodies matingly engaged together along an axis, the inlets spaced apart relative to the axis to define a gallery having a depth in an axial direction and a width in a transverse direction; and a gap filler within the gallery, compressible in at least one of the directions, having an uncompressed dimension greater than a corresponding dimension of the gallery in the at least one of the directions.</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COMBUSTION APPARATUS</subject><subject>COMBUSTION ENGINES</subject><subject>COMBUSTION PROCESSES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>GAS-TURBINE PLANTS</subject><subject>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2022</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFBxTyxQSMvMyUktUkjLL1JIVEgrTc1RKK4sLknNVUhPBElU8jCwpiXmFKfyQmluBkU31xBnD93Ugvz41OKCxOTUvNSS-NBgQ0MTMzMLU0snI2Ni1AAA3BYmjg</recordid><startdate>20221011</startdate><enddate>20221011</enddate><creator>Swaby, Nadia</creator><creator>Sreekanth, Sri</creator><scope>EVB</scope></search><sort><creationdate>20221011</creationdate><title>Gap filler for a fuel system gallery</title><author>Swaby, Nadia ; Sreekanth, Sri</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US11466859B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2022</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COMBUSTION APPARATUS</topic><topic>COMBUSTION ENGINES</topic><topic>COMBUSTION PROCESSES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>GAS-TURBINE PLANTS</topic><topic>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Swaby, Nadia</creatorcontrib><creatorcontrib>Sreekanth, Sri</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Swaby, Nadia</au><au>Sreekanth, Sri</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Gap filler for a fuel system gallery</title><date>2022-10-11</date><risdate>2022</risdate><abstract>A nozzle assembly for a gas turbine engine, comprising: a nozzle at a downstream end of the assembly relative to fuel flow; a first and a second body upstream of the nozzle, the first body defining a first passage between a first inlet connectable to a source and a first outlet, and the second body defining a second passage between a second inlet and a second outlet in fluid communication with the nozzle, the inlets in fluid communication with each other; the bodies matingly engaged together along an axis, the inlets spaced apart relative to the axis to define a gallery having a depth in an axial direction and a width in a transverse direction; and a gap filler within the gallery, compressible in at least one of the directions, having an uncompressed dimension greater than a corresponding dimension of the gallery in the at least one of the directions.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | Gap filler for a fuel system gallery |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2024-12-25T21%3A57%3A33IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=Swaby,%20Nadia&rft.date=2022-10-11&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS11466859B2%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |