Transition piece for a gas turbine engine, corresponding system and method

(19)

(11)

EP 2 650 480 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	21.10.2015 Bulletin 2015/43

(43)	Date of publication A2:
	16.10.2013 Bulletin 2013/42

(21)	Application number: 13163218.4

(22)	Date of filing: 10.04.2013

(51)

International Patent Classification (IPC):

F01D 9/02^(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:

13.04.2012 US 201213446718

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

(72)	Inventors:
	DiCintio, Richard Martin Greenville, SC South Carolina 29615 (US) Melton, Patrick Benedict Greenville, SC South Carolina 29615 (US)

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

(54)	Transition piece for a gas turbine engine, corresponding system and method

(57) Disclosed herein are apparatus, method, and system for cross sectional area convergence reduction and selection of a transition piece (200) of a gas turbine engine. In an embodiment, an aft end cross sectional area (210) is determined for a transition piece and a forward end cross sectional area (205) is determined for the transition piece. The transition piece may be fabricated based on a constant slope of cross sectional area change between the aft end and the forward end.

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