Chris A Rickert

US Patent:

7165944, Jan 23, 2007

Filed:

Jan 21, 2005

Appl. No.:

11/038038

Inventors:

James Charles Gautreau - Greenville SC, US
Nicholas Francis Martin - Simpsonville SC, US
Chris A. Rickert - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/16

US Classification:

416219R, 416239, 416248, 416500

Abstract:

A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.

US Patent:

20040213672, Oct 28, 2004

Filed:

Apr 25, 2003

Appl. No.:

10/422701

Inventors:

James Gautreau - Greenville SC, US
Nicholas Martin - Simpsonville SC, US
Chris Rickert - Greenville SC, US

International Classification:

F01D025/04

US Classification:

416/190000

Abstract:

A compressor blade includes an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion, the undercut defined by a narrow entry slot opening into a rearward transverse groove.

US Patent:

20050232777, Oct 20, 2005

Filed:

Dec 20, 2004

Appl. No.:

11/015746

Inventors:

James Gautreau - Greenville SC, US
Nicholas Martin - Simpsonville SC, US
Chris Rickert - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B63H001/16

US Classification:

41621900R

Abstract:

A blade of an turbomachine having an airfoil with a leading edge and a root; a base attached to the root of the airfoil; a dovetail portion of the base engageable with disk; a slot in the base generally parallel to a face of the base extending between opposite sides of the base, and a vibration adsorbing insert snuggly fitted into the slot.

US Patent:

20070137213, Jun 21, 2007

Filed:

Dec 19, 2005

Appl. No.:

11/305169

Inventors:

Chris Rickert - Greenville SC, US
Jeffrey Palmer - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/12

US Classification:

060782000, 060806000

Abstract:

A method of controlling wheelspace temperature in a gas turbine comprising: (a) extracting air from a compressor used to supply compressed air to the gas turbine for combustion; (b) supplying air extracted in step (a) to the wheelspaces in the gas turbine; and (c) controlling flow of air supplied in step (b) to achieve a desired wheelspace temperature.