Combustor assembly for a turbine engine
A combustor assembly (100) for a gas turbine engine includes a dome having a forward surface (121) and an inner surface (120). The forward surface (121) and the inner surface (120) of the dome at least partially define a slot (122). The combustor assembly (100) also includes a liner at least partial...
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| creator | CHAD HOLDEN SUTTON ROBERT ANDREW STOWERS JEFFREY DOUGLAS JOHNSON GREGORY SCOTT PHELPS MICHAEL ALAN STIEG DARRELL GLENN SENILE |
| description | A combustor assembly (100) for a gas turbine engine includes a dome having a forward surface (121) and an inner surface (120). The forward surface (121) and the inner surface (120) of the dome at least partially define a slot (122). The combustor assembly (100) also includes a liner at least partially defining a combustion chamber (114) and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot (122) of the dome. The forward end of the liner includes an axial interface surface (183) and a radial interface surface (188). The axial interface surface (186) defines a radial gap (190) with the inner surface (120) of the dome and the radial interface surface (188) defines an axial gap (192) with the forward surface (121) of the dome. At least one of the radial gap (190) or the axial gap (192) is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.
本发明涉及种用于燃气涡轮发动机的燃烧器组件(100)，包括圆顶部，圆顶部具有前表面(121)和内表面(12 |
| format | Patent |
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本发明涉及种用于燃气涡轮发动机的燃烧器组件(100)，包括圆顶部，圆顶部具有前表面(121)和内表面(12</description><language>chi ; eng</language><subject>BLASTING ; COMBUSTION APPARATUS ; COMBUSTION PROCESSES ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; HEATING ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2018</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=20180306&DB=EPODOC&CC=CN&NR=107763664A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,777,882,25545,76296</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180306&DB=EPODOC&CC=CN&NR=107763664A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>CHAD HOLDEN SUTTON</creatorcontrib><creatorcontrib>ROBERT ANDREW STOWERS</creatorcontrib><creatorcontrib>JEFFREY DOUGLAS JOHNSON</creatorcontrib><creatorcontrib>GREGORY SCOTT PHELPS</creatorcontrib><creatorcontrib>MICHAEL ALAN STIEG</creatorcontrib><creatorcontrib>DARRELL GLENN SENILE</creatorcontrib><title>Combustor assembly for a turbine engine</title><description>A combustor assembly (100) for a gas turbine engine includes a dome having a forward surface (121) and an inner surface (120). The forward surface (121) and the inner surface (120) of the dome at least partially define a slot (122). The combustor assembly (100) also includes a liner at least partially defining a combustion chamber (114) and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot (122) of the dome. The forward end of the liner includes an axial interface surface (183) and a radial interface surface (188). The axial interface surface (186) defines a radial gap (190) with the inner surface (120) of the dome and the radial interface surface (188) defines an axial gap (192) with the forward surface (121) of the dome. At least one of the radial gap (190) or the axial gap (192) is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.
本发明涉及种用于燃气涡轮发动机的燃烧器组件(100)，包括圆顶部，圆顶部具有前表面(121)和内表面(12</description><subject>BLASTING</subject><subject>COMBUSTION APPARATUS</subject><subject>COMBUSTION PROCESSES</subject><subject>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</subject><subject>HEATING</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2018</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFB3zs9NKi0uyS9SSCwuTs1NyqlUSANxFEpKi5Iy81IVUvPSgRQPA2taYk5xKi-U5mZQdHMNcfbQTS3Ij08tLkhMTs1LLYl39jM0MDc3MzYzM3E0JkYNAKHWJ_M</recordid><startdate>20180306</startdate><enddate>20180306</enddate><creator>CHAD HOLDEN SUTTON</creator><creator>ROBERT ANDREW STOWERS</creator><creator>JEFFREY DOUGLAS JOHNSON</creator><creator>GREGORY SCOTT PHELPS</creator><creator>MICHAEL ALAN STIEG</creator><creator>DARRELL GLENN SENILE</creator><scope>EVB</scope></search><sort><creationdate>20180306</creationdate><title>Combustor assembly for a turbine engine</title><author>CHAD HOLDEN SUTTON ; ROBERT ANDREW STOWERS ; JEFFREY DOUGLAS JOHNSON ; GREGORY SCOTT PHELPS ; MICHAEL ALAN STIEG ; DARRELL GLENN SENILE</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN107763664A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2018</creationdate><topic>BLASTING</topic><topic>COMBUSTION APPARATUS</topic><topic>COMBUSTION PROCESSES</topic><topic>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</topic><topic>HEATING</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>CHAD HOLDEN SUTTON</creatorcontrib><creatorcontrib>ROBERT ANDREW STOWERS</creatorcontrib><creatorcontrib>JEFFREY DOUGLAS JOHNSON</creatorcontrib><creatorcontrib>GREGORY SCOTT PHELPS</creatorcontrib><creatorcontrib>MICHAEL ALAN STIEG</creatorcontrib><creatorcontrib>DARRELL GLENN SENILE</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>CHAD HOLDEN SUTTON</au><au>ROBERT ANDREW STOWERS</au><au>JEFFREY DOUGLAS JOHNSON</au><au>GREGORY SCOTT PHELPS</au><au>MICHAEL ALAN STIEG</au><au>DARRELL GLENN SENILE</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Combustor assembly for a turbine engine</title><date>2018-03-06</date><risdate>2018</risdate><abstract>A combustor assembly (100) for a gas turbine engine includes a dome having a forward surface (121) and an inner surface (120). The forward surface (121) and the inner surface (120) of the dome at least partially define a slot (122). The combustor assembly (100) also includes a liner at least partially defining a combustion chamber (114) and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot (122) of the dome. The forward end of the liner includes an axial interface surface (183) and a radial interface surface (188). The axial interface surface (186) defines a radial gap (190) with the inner surface (120) of the dome and the radial interface surface (188) defines an axial gap (192) with the forward surface (121) of the dome. At least one of the radial gap (190) or the axial gap (192) is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.
本发明涉及种用于燃气涡轮发动机的燃烧器组件(100)，包括圆顶部，圆顶部具有前表面(121)和内表面(12</abstract><oa>free_for_read</oa></addata></record> |
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| language | chi ; eng |
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| subjects | BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | Combustor assembly for a turbine engine |
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