Method and apparatus for cooling gas turbine engine rotor blade

A rotor blade (40) for a gas turbine engine, includes a platform (62) including a radially outer surface (152) and a radially inner surface (144). An airfoil (60) extends radially outward from the platform. A shank (64) extends radially inward from the platform. A dovetail (66) extends from the shan...

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Bibliographische Detailangaben
Hauptverfasser:	HONKOMP, MARK STEVEN, COLLADO, CARLOS ALBERTO, BENJAMIN, EDWARD DURELL, WASSYNGER, STEPHEN PAUL, FERNANDEZ, EMILIO, BUTKIEWICZ, JEFFREY JOHN
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS 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 rotor blade (40) for a gas turbine engine, includes a platform (62) including a radially outer surface (152) and a radially inner surface (144). An airfoil (60) extends radially outward from the platform. A shank (64) extends radially inward from the platform. A dovetail (66) extends from the shank such that an internal cavity is defined at least partially by the airfoil, the platform, the shank, and the dovetail. A cooling circuit extends through a portion of the shank for supplying cooling air from the cavity for impingement cooling of the platform radially inner surface.