GAS TURBINE ENGINE WALL ASSEMBLY WITH ENHANCED FLOW ARCHITECTURE

A liner panel is provided for use in a gas turbine engine. The liner panel includes an intermediate rail that extends from a cold side of a liner panel. The liner panel also includes a multiple of heat transfer augmentors, which generally decrease in height with respect to a distance from the interm...

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Bibliographic Details
Main Authors CUNHA, Frank J, KOSTKA, Stanislav
Format Patent
LanguageEnglish
French
German
Published 11.01.2017
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FORCOMBUSTION CHAMBERS, e.g. FIREBRIDGES
COMBUSTION APPARATUS
COMBUSTION ENGINES
COMBUSTION PROCESSES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDEDFOR
DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS INCOMBUSTION CHAMBERS
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
SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTIONAPPARATUS
WEAPONS
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Summary:A liner panel is provided for use in a gas turbine engine. The liner panel includes an intermediate rail that extends from a cold side of a liner panel. The liner panel also includes a multiple of heat transfer augmentors, which generally decrease in height with respect to a distance from the intermediate rail.
Bibliography:Application Number: EP20140876414