CONTOURED DILUTION PASSAGES FOR A GAS TURBINE ENGINE COMBUSTOR
A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a...
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| Main Authors | , , , , |
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| Format | Patent |
| Language | English French German |
| Published |
14.09.2022
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| Subjects | |
| Online Access | Get full text |
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| Abstract | A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall. |
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| AbstractList | A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall. |
| Author | HOKE, James B SNYDER, Timothy S CUNHA, Frank J MCKINNEY, Randal G KOSTKA, JR. Stanislav |
| Author_xml | – fullname: MCKINNEY, Randal G – fullname: CUNHA, Frank J – fullname: HOKE, James B – fullname: KOSTKA, JR. Stanislav – fullname: SNYDER, Timothy S |
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| DocumentTitleAlternate | PASSAGES DE DILUTION PROFILÉS POUR CHAMBRE À COMBUSTION DE TURBINE À GAZ KONTURIERTE VERDÜNNUNGSDURCHGÄNGE FÜR EINE GASTURBINENBRENNKAMMER |
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| Notes | Application Number: EP20140840707 |
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| RelatedCompanies | Raytheon Technologies Corporation |
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| Snippet | A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a... |
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| SubjectTerms | 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 | CONTOURED DILUTION PASSAGES FOR A GAS TURBINE ENGINE COMBUSTOR |
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