Aerodynamically damping vibrations in a rotor stage of a turbomachine

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(11)

EP 0 921 274 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	06.09.2000 Bulletin 2000/36

(43)	Date of publication A2:
	09.06.1999 Bulletin 1999/23

(21)	Application number: 98309906.0

(22)	Date of filing: 03.12.1998

(51)	International Patent Classification (IPC)⁷: F01D 5/10

(84)	Designated Contracting States:
	AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE
	Designated Extension States:
	AL LT LV MK RO SI

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Priority:

03.12.1997 US 984400

(71)	Applicant: UNITED TECHNOLOGIES CORPORATION
	Hartford, CT 06101 (US)

(72)	Inventors:
	El-Aini, Yehia M. Jupiter, Florida 33477 (US) Cowles, Bradford A. Palm Beach Garders, Florida 33410 (US)

(74)	Representative: Leckey, David Herbert
	Frank B. Dehn & Co., European Patent Attorneys, 179 Queen Victoria Street London EC4V 4EL London EC4V 4EL (GB)

(54)	Aerodynamically damping vibrations in a rotor stage of a turbomachine

(57) A rotor stage for a gas turbine engine is provided which includes a rotor disk (34) and a plurality of rotor blades (36). The rotor blades extend radially outward from the outer radial surface of the disk, and are separated from one another by a distance (D). The distance is selectively varied to increase aerodynamic damping of the rotor blades.

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