Turbine nozzle assembly methods

(19)

(11)

EP 2 613 004 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	28.06.2017 Bulletin 2017/26

(43)	Date of publication A2:
	10.07.2013 Bulletin 2013/28

(21)	Application number: 13150147.0

(22)	Date of filing: 03.01.2013

(51)

Int. Cl.:

F01D 9/04 ^(2006.01)

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

(30)

Priority:

09.01.2012 US 201213345777

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

(72)	Inventors:
	Coign, Robert Walter Greenville, SC South Carolina 29615 (US) Winn, Aaron Gregory Greenville, SC South Carolina 29615 (US)

(74)	Representative: Cleary, Fidelma et al
	GPO Europe GE International Inc. The Ark 201 Talgarth Road Hammersmith London W6 8BJ London W6 8BJ (GB)

(54)	Turbine nozzle assembly methods

(57) The present application provides a method of installing an impingement cooling assembly in an inner platform of an airfoil of a turbine nozzle. The method includes the steps of positioning an insert within a cavity of the airfoil, positioning a core exit cover (220) about an opening (225) of the cavity, positioning an impingement plenum (190) within a platform cavity (160), inserting an unfixed spoolie (200) through an assembly port (260) of the impingement plenum and into an airflow cavity (170) of the insert, and closing the assembly port.