Gas turbine engine airfoil comprising a conduction pedestal

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(11)

EP 2 434 096 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	29.04.2015 Bulletin 2015/18

(43)	Date of publication A2:
	28.03.2012 Bulletin 2012/13

(21)	Application number: 11182897.6

(22)	Date of filing: 27.09.2011

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International Patent Classification (IPC):

F01D 5/18^(2006.01)

(84)	Designated Contracting States:
	AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
	Designated Extension States:
	BA ME

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Priority:

28.09.2010 US 892056

(71)	Applicant: United Technologies Corporation
	Hartford, CT 06101 (US)

(72)	Inventors:
	Spangler, Brandon W. Vernon, CT 06066 (US) Learned, Amanda Jean Manchester, CT 06042 (US)

(74)	Representative: Leckey, David Herbert
	Dehns St Bride's House 10 Salisbury Square London EC4Y 8JD London EC4Y 8JD (GB)

(54)	Gas turbine engine airfoil comprising a conduction pedestal

(57) An airfoil (32) for a gas turbine engine includes an airfoil which defines a leading edge cavity (56) and a forward cavity (34A) between a pressure side wall (40P) and a suction side wall (40S). The leading edge cavity (56) is at least partially defined by a leading edge wall (40L) which extends between the pressure side wall (40P) and the suction side wall (40S). A rib (54) between the pressure side wall (40P) and the suction side wall (40S) separates the forward cavity (34A) and the leading edge cavity (56). A pedestal (60) extends between the leading edge wall (40L) and the rib (54).

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