Brian Kelly Keith

US Patent:

6672829, Jan 6, 2004

Filed:

Jul 16, 2002

Appl. No.:

10/196623

Inventors:

David Glenn Cherry - Loveland OH
Chander Prakash - Cincinnati OH
Aspi Rustom Wadia - Loveland OH
Brian David Keith - Cincinnati OH
Steven Robert Brassfield - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 518

US Classification:

415115, 416 97 R

Abstract:

A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.

US Patent:

6786696, Sep 7, 2004

Filed:

May 6, 2002

Appl. No.:

10/139534

Inventors:

William Charles Herman - Blue Ash OH
Brian Alan Norton - Cincinnati OH
Brian David Keith - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 530

US Classification:

416 96R, 416193, 416248

Abstract:

A turbine blade includes an airfoil and dovetail. The dovetail includes a pair of supporting tangs. A rectangular root block bridges the tangs over a majority of the root end thereof. The block terminates short of one endface of the dovetail to form a root notch thereat for preferentially reducing weight.

US Patent:

6932568, Aug 23, 2005

Filed:

Feb 27, 2003

Appl. No.:

10/375441

Inventors:

Andrew Charles Powis - Maderia OH, US
Jonathan Philip Clarke - West Chester OH, US
Jonathan Jordan Peterman - West Chester OH, US
Robert Alan Frederick - West Chester OH, US
Edward Eugene Gibler - West Chester OH, US
Brian David Keith - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D009/04

US Classification:

415189, 4152092

Abstract:

A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.

US Patent:

6969233, Nov 29, 2005

Filed:

Feb 27, 2003

Appl. No.:

10/375585

Inventors:

Andrew Charles Powis - Maderia OH, US
Jonathan Philip Clarke - West Chester OH, US
Jonathan Jordan Peterman - West Chester OH, US
Robert Alan Frederick - West Chester OH, US
Edward Eugene Gibler - West Chester OH, US
Brian David Keith - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D009/04

US Classification:

415191, 416191, 416233

Abstract:

A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.

US Patent:

7008185, Mar 7, 2006

Filed:

Feb 27, 2003

Appl. No.:

10/375415

Inventors:

Jonathan Jordan Peterman - West Chester OH, US
Andrew Charles Powis - Maderia OH, US
Jonathan Philip Clarke - West Chester OH, US
Robert Alan Frederick - West Chester OH, US
Edward Eugene Gibler - West Chester OH, US
Brian David Keith - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 9/02
F01D 5/18

US Classification:

416 96A, 415115

Abstract:

A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.

US Patent:

7497663, Mar 3, 2009

Filed:

Oct 26, 2006

Appl. No.:

11/586952

Inventors:

Brian David Keith - Cincinnati OH, US
Andrew Edward Obermeyer - West Chester OH, US
Leslie Eugene Leeke - Burlington KY, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/14

US Classification:

416191, 416223 A, 416DIG 2, 416243

Abstract:

An airfoil for a rotor blade including an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z to facilitate balancing performance and durability of the rotor blade and to facilitate improving an operating efficiency of a high-pressure turbine is provided. The profile is carried only to four decimal places, wherein Y represents a distance from a platform on which the airfoil is mounted, and X and Z are coordinates defining the profile at each distance Y from the platform.

US Patent:

7607893, Oct 27, 2009

Filed:

Aug 21, 2006

Appl. No.:

11/507132

Inventors:

Kevin Samuel Klasing - Springboro OH, US
Paul Hadley Vitt - Hamilton OH, US
Brian David Keith - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/20

US Classification:

416228, 4151731

Abstract:

A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a tip baffle. The baffle extends chordally in counter profile with the first rib to define a first pocket, and in counter profile with the second rib to define a second pocket.

US Patent:

7686578, Mar 30, 2010

Filed:

Aug 21, 2006

Appl. No.:

11/507121

Inventors:

Kevin Samuel Klasing - Springboro OH, US
Paul Hadley Vitt - Hamilton OH, US
Brian David Keith - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/20

US Classification:

4151731, 416228

Abstract:

A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested transversely between the ribs, and conforms with the second rib to bifurcate the airfoil tip into first and second tip pockets extending along the corresponding pressure and suction sides.