Method and apparatus for reducing axial compressor blade tip flow

(19)

(11)

EP 1 793 089 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	24.10.2007 Bulletin 2007/43

(43)	Date of publication A2:
	06.06.2007 Bulletin 2007/23

(21)	Application number: 06125091.6

(22)	Date of filing: 30.11.2006

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International Patent Classification (IPC):

F01D 11/04^(2006.01)

F01D 5/08^(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 NL PL PT RO SE SI SK TR
	Designated Extension States:
	AL BA HR MK YU

(30)

Priority:

30.11.2005 US 164636

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

(72)	Inventors:
	Dong, Zhifeng Cincinnati, OH 45241 (US) Rahaim, John Joseph Cincinnati, OH 45220 (US)

(74)	Representative: Bedford, Grant Richard
	London Patent Operation GE International Inc. 15 John Adam Street London WC2N 6LU London WC2N 6LU (GB)

(54)	Method and apparatus for reducing axial compressor blade tip flow

(57) A turbine machine (T1) of the type having a high pressure compressor positioned in a casing is provided with a plurality of rotating compressor blades (10-14) with at least one air channel (10C-14C) formed in the blades (10-14) for air flow communication from the base to the tip for extracting and pressurizing air from an inner area proximate the disk (20) and conveying the extracted and pressurized air into an area between the blade tip and casing (C1) for blocking air flow across the tips of the blades (10-14).

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