Gas turbine engine component having wavy cooling channels with pedestals

A gas turbine engine component (40;82) comprises a plurality of walls, a cooling channel (54;92), a plurality of ribs (58A-F;94A-D) and a plurality of pedestals (64A-F;96A-F). The plurality of walls has a pair of major surfaces (56A;56B) opposed to define an interior chamber. The cooling channel (54...

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Bibliographic Details
Main Authors Trindade, Ricardo, Piggush, Justin D
Format Patent
LanguageEnglish
French
German
Published 29.05.2019
Subjects
BLASTING
ENGINE PLANTS IN GENERAL
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 component (40;82) comprises a plurality of walls, a cooling channel (54;92), a plurality of ribs (58A-F;94A-D) and a plurality of pedestals (64A-F;96A-F). The plurality of walls has a pair of major surfaces (56A;56B) opposed to define an interior chamber. The cooling channel (54;92) extends through the interior chamber of the plurality of walls between the major surfaces (56A;56B). The plurality of ribs (58A-F;94A-D) extends through the cooling channel to form a plurality of wavy passages (65A-E;98A-B) having bowed-out sections (68A-B;102A-B). The plurality of pedestals (64A-F;96A-F) is positioned between adjacent ribs (58A-F;94A-D), each pedestal (64A-F;96A-F) being positioned in a bowed-out section (68A-B;102A-B).
Bibliography:Application Number: EP20120186707