Component, corresponding gas turbine engine and method of cooling

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(11)

EP 2 944 764 A8

(12)	CORRECTED EUROPEAN PATENT APPLICATION
	Note: Bibliography reflects the latest situation

(15)	Correction information:
	Corrected version no 1 (W1 A1)

(48)	Corrigendum issued on:
	07.06.2017 Bulletin 2017/23

(88)	Date of publication A3:
	18.11.2015 Bulletin 2015/47

(43)	Date of publication:
	18.11.2015 Bulletin 2015/47

(21)	Application number: 15001485.0

(22)	Date of filing: 18.05.2015

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International Patent Classification (IPC):

F01D 5/20^(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

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Priority:

16.05.2014 US 201461994270 P

(71)	Applicant: United Technologies Corporation
	Farmington, CT 06032 (US)

(72)	Inventors:
	Quach, San East Hartford CT 06108 (US) Propheter-Hinckley, Tracy A. Manchester CT 06042 (US) Gautschi, Steven Bruce Milton, MA 02186 (US)

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

(54)	Component, corresponding gas turbine engine and method of cooling

(57) A component includes an airfoil (62) that includes a pressure sidewall (70) and a suction sidewall (72) that meet together at both a leading edge (66) and a trailing edge (68). The airfoil extends to a tip (77). A tip pocket (80) is formed in the tip (77) and terminates prior to the trailing edge (68). A heat transfer augmentation device (92) is formed in the tip pocket (80).