COOLED ROTOR BLADE

A turbomachine component includes a platform (42), a shank (36), and an airfoil (40). The platform (42) includes a pressure side slash face (62) and a suction side slash face. The shank (36) extends radially inward from the platform (42). The airfoil (40) extends radially outward from the platform (...

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Bibliographische Detailangaben
Hauptverfasser:	AGUDO, Jan Emeric, GRAY, Brian Stephen, WONDRASEK, Michael Anthony
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	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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Beschreibung
Zusammenfassung:	A turbomachine component includes a platform (42), a shank (36), and an airfoil (40). The platform (42) includes a pressure side slash face (62) and a suction side slash face. The shank (36) extends radially inward from the platform (42). The airfoil (40) extends 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) further includes a plurality of exit channels (66) disposed along the trailing edge (54) of the airfoil (40). The cooling circuit (56) further includes at least one bypass conduit (88) that extends from an inlet (100) disposed in the cooling circuit (56) to an outlet (102) positioned on the pressure side slash face (62). The at least one bypass conduit (88) being positioned radially inward of the plurality of exit channels (66).