CAST COMBUSTOR LINER PANEL GATING FEATURE 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 radiused gate (150, 152, 154,156) blended into a hot side (112) of the liner panel (72, 74). A combustor for a gas turbine engine (20) including a liner panel (72, 74) mounted to a support...

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Bibliographic Details
Main Authors ZACCHERA, Kevin, WERKHEISER, William F, HAZEL, Brian T, EASTWOOD, Jonathan Jeffery
Format Patent
LanguageEnglish
French
German
Published 11.07.2018
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 radiused gate (150, 152, 154,156) blended into a hot side (112) of the liner panel (72, 74). A combustor for a gas turbine engine (20) including a liner panel (72, 74) mounted to a support shell (68, 70) via a multiple of studs (100), the liner panel (72, 74) including a radiused gate (150, 152, 154, 156) blended into a hot side (112) of the liner panel (72, 74), the hot side (112) including a thermal barrier coating. A method of manufacturing including casting a radiused gate (150, 152, 154, 156) tangentially cast into a hot side (112) of a liner panel (72, 74); and applying a thermal barrier coating to the hot side (112) of the liner panel (72, 74) over the remnants of the radiused gate (150, 152, 154, 156).
Bibliography:Application Number: EP20170198179