Rotor blade and rotor disc for a gas turbine engine with a reduced coefficient of friction at the blade and disc interface

(19)

(11)

EP 1 564 377 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	08.11.2006 Bulletin 2006/45

(43)	Date of publication A2:
	17.08.2005 Bulletin 2005/33

(21)	Application number: 05250384.4

(22)	Date of filing: 26.01.2005

(51)

International Patent Classification (IPC):

F01D 5/30^(2006.01)

F01D 5/06^(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 MC NL PL PT RO SE SI SK TR
	Designated Extension States:
	AL BA HR LV MK YU

(30)

Priority:

12.02.2004 GB 0403064

(71)	Applicant: ROLLS-ROYCE PLC
	London, SW1E 6AT (GB)

(72)	Inventor:
	Goldfinch, Keith Christopher Clifton Bristol BS8 4TE (GB)

(74)	Representative: Bird, Vivian John et al
	Rolls-Royce plc, Intellectual Property Dept WH 58, P.O. Box 3, Filton Bristol BS34 7QE Bristol BS34 7QE (GB)

(54)	Rotor blade and rotor disc for a gas turbine engine with a reduced coefficient of friction at the blade and disc interface

(57) A rotor blade, a rotor disc (24) or load bearing assembly having at least one bearing surface (22) for contact with a corresponding bearing surface (28). At least one selected area of the bearing surface (30,32) which, in operation, is an area of alternating stress greater than about 50 MPa (peak to peak), is configured to have a co-efficient of friction lower than the remainder of the bearing surface (34). The selected area (30,32) having a co-efficient of friction lower than the remainder of the bearing surface (34) may be provided by the application of a dry film lubricant, with the remaining area(s) (34) of said bearing surfaces (22) being substantially free of the said coating.

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