Gas turbine engine wall

A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge la...

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Bibliographic Details
Main Authors Pearson, Shawn Michael, Feldmann, Kevin Robert, Bergholz, Robert Frederick, Smith, Douglas Ray, Buck, Frederick Alan, Molter, Stephen Mark
Format Patent
LanguageEnglish
Published 20.08.2019
Subjects
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
ENGINE PLANTS IN GENERAL
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Summary:A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.
Bibliography:Application Number: US201314407076