Cooling circuit for a turbomachine component

The rotor blade includes a platform (42) and a shank (36) extending radially inward from the platform (42). The rotor blade further includes an airfoil (40) extending radially outward from the platform (42). The airfoil (40) includes a leading edge (52) and a trailing edge (54). A cooling circuit (5...

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Bibliographic Details
Main Authors AGUDO, JAN EMERIC, JASPER, MARTIN JAMES
Format Patent
LanguageChinese
English
Published 01.10.2021
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:The rotor blade includes a platform (42) and a shank (36) extending radially inward from the platform (42). The rotor blade further includes an airfoil (40) extending radially outward from the platform (42). The airfoil (40) includes a leading edge (52) and a trailing edge (54). A cooling circuit (56) is defined within the shank (36) and the airfoil (40). The cooling circuit (56) includes a plurality of pins (68). The plurality of pins (68) includes a first pin group (72) positioned radially inward of the platform (42) and a second pin group (74) positioned within the airfoil (40). The cooling circuit (56) further includes a plurality of exit channels (66) disposed along the trailing edge (54). The plurality of exit channels (66) is downstream from the plurality of pins (68). The cooling circuit (56) also includes at least one bypass conduit (88) extending from an inlet (90) disposed in the cooling circuit (56) to an outlet (92) positioned on the trailing platform face (116). The at least one bypass conduit (
Bibliography:Application Number: TW202110106260