Leading edge cooling of a gas turbine component using staggered turbulator strips

(19)

(11)

EP 1 870 561 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	22.12.2010 Bulletin 2010/51

(43)	Date of publication A2:
	26.12.2007 Bulletin 2007/52

(21)	Application number: 07252545.4

(22)	Date of filing: 22.06.2007

(51)

International Patent Classification (IPC):

F01D 5/18^(2006.01)

F01D 25/12^(2006.01)

(84)	Designated Contracting States:
	AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR
	Designated Extension States:
	AL BA HR MK RS

(30)

Priority:

22.06.2006 US 473893

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

(72)	Inventors:
	Levine, Jeffrey R. Vernon, CT 06066 (US) Kaufman, Eleanor Cromwell, CT 06416 (US) Abdel-Messeh, William Middletown, CT 06457 (US)

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

(54)	Leading edge cooling of a gas turbine component using staggered turbulator strips

(57) A turbine engine component has an airfoil portion (32) having a leading edge, a suction side (46), a pressure side (42) and a radial flow leading edge cavity (34) through which a cooling fluid flows for cooling the leading edge. The turbine engine component further has a staggered arrangement of trip strips (40; 44) for generating a vortex (49) in the leading edge cavity (34) which impinges on a nose portion (36) of the leading edge cavity (34).

Search report