HOT GAS PATH COMPONENT AND METHODS OF MANUFACTURE

(19)

(11)

EP 3 040 522 A8

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

(15)	Correction information:
	Corrected version no 1 (W1 A2)

(48)	Corrigendum issued on:
	28.09.2016 Bulletin 2016/39

(43)	Date of publication:
	06.07.2016 Bulletin 2016/27

(21)	Application number: 15200043.6

(22)	Date of filing: 15.12.2015

(51)

International Patent Classification (IPC):

F01D 25/12^(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
	Designated Validation States:
	MA MD

(30)

Priority:

29.12.2014 US 201414584442

(71)	Applicant: General Electric Company
	Schenectady, NY 12345 (US)

(72)	Inventors:
	LACY, Benjamin Paul Greenville, SC South Carolina 29615 (US) KOTTILINGAM, Srikanth Chandrudu Greenville, SC South Carolina 29615 (US) PORTER, Christopher Donald Greenville, SC South Carolina 29615 (US) SCHICK, David Edward Greenville, SC South Carolina 29615 (US)

(74)	Representative: Lee, Brenda
	GE International Inc. Global Patent Operation - Europe The Ark 201 Talgarth Road Hammersmith London W6 8BJ London W6 8BJ (GB)

(54)	HOT GAS PATH COMPONENT AND METHODS OF MANUFACTURE

(57) Various embodiments of the disclosure include a turbomachine component (2) and methods of forming such a component (2). Some embodiments include a turbomachine component (2) including: a first portion (4) including at least one of a stainless steel or an alloy steel; and a second portion (6) joined with the first portion (4), the second portion (6) including a nickel alloy including an arced cooling feature (10) extending therethrough, the second portion (6) having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion (4), wherein the arced cooling feature (10) is located within the second portion (6) to direct a portion of a coolant to a leakage area (18) of the turbomachine component (2).