Combustor assembly for a turbine engine
A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and exten...
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| creator | Stowers, Robert Andrew Sutton, Chad Holden Johnson, Jeffrey Douglas Stieg, Michael Alan Phelps, Gregory Scott Senile, Darrell Glenn |
| description | A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow. |
| format | Patent |
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The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. 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At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.</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>2023</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFB3zs9NKi0uyS9SSCwuTs1NyqlUSANxFEpKi5Iy81IVUvPSgRQPA2taYk5xKi-U5mZQdHMNcfbQTS3Ij08tLkhMTs1LLYkPDTY0NDcytTA0cTIyJkYNAKYGKBE</recordid><startdate>20230815</startdate><enddate>20230815</enddate><creator>Stowers, Robert Andrew</creator><creator>Sutton, Chad Holden</creator><creator>Johnson, Jeffrey Douglas</creator><creator>Stieg, Michael Alan</creator><creator>Phelps, Gregory Scott</creator><creator>Senile, Darrell Glenn</creator><scope>EVB</scope></search><sort><creationdate>20230815</creationdate><title>Combustor assembly for a turbine engine</title><author>Stowers, Robert Andrew ; Sutton, Chad Holden ; Johnson, Jeffrey Douglas ; Stieg, Michael Alan ; Phelps, Gregory Scott ; Senile, Darrell Glenn</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US11725814B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2023</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>Stowers, Robert Andrew</creatorcontrib><creatorcontrib>Sutton, Chad Holden</creatorcontrib><creatorcontrib>Johnson, Jeffrey Douglas</creatorcontrib><creatorcontrib>Stieg, Michael Alan</creatorcontrib><creatorcontrib>Phelps, Gregory Scott</creatorcontrib><creatorcontrib>Senile, Darrell Glenn</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Stowers, Robert Andrew</au><au>Sutton, Chad Holden</au><au>Johnson, Jeffrey Douglas</au><au>Stieg, Michael Alan</au><au>Phelps, Gregory Scott</au><au>Senile, Darrell Glenn</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Combustor assembly for a turbine engine</title><date>2023-08-15</date><risdate>2023</risdate><abstract>A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.</abstract><oa>free_for_read</oa></addata></record> |
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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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