CAST COMBUSTOR LINER PANEL WITH RADIUSED DILUTION PASSAGE GROMMET FOR A GAS TURBINE ENGINE COMBUSTOR

A liner panel (72, 74) for use in a combustor of a gas turbine engine (20), the liner panel (72, 74) includes a grommet (151) that forms a lip (130) and a seal boss (132), the lip (130) including a chamfer (160) with a first radius (162) and a second radius (164) adjacent to an entry (166) of a dilu...

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Bibliographic Details
Main Authors WERKHEISER, William F, HAZEL, Brian T, MOURA, Dennis M, EASTWOOD, Jonathan Jeffery
Format Patent
LanguageEnglish
French
German
Published 02.05.2018
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
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Summary:A liner panel (72, 74) for use in a combustor of a gas turbine engine (20), the liner panel (72, 74) includes a grommet (151) that forms a lip (130) and a seal boss (132), the lip (130) including a chamfer (160) with a first radius (162) and a second radius (164) adjacent to an entry (166) of a dilution passage (116A) defined by the grommet (151). A liner panel (72, 74) for use in a combustor of a gas turbine engine (20), the liner panel (72, 74) includes a grommet (151) that forms a lip (130) and a seal boss (132), the lip (130) including a chamfer (160) with a first radius (162) and a second radius (164) adjacent to an entry (166) of a dilution passage (116A) defined by the grommet (151) and a third radius (170) at an exit (172) of the dilution passage (116A) and a thermal barrier coating on the grommet (151).
Bibliography:Application Number: EP20170198181