Scott Gerald Carson

US Patent:

6345955, Feb 12, 2002

Filed:

Dec 17, 1999

Appl. No.:

09/466296

Inventors:

Todd S. Heffron - Indian Springs OH
John P. Heyward - Loveland OH
John H. Starkweather - Cincinnati OH
Scott M. Carson - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 514

US Classification:

415115, 415191, 4152082, 416241 R

Abstract:

A turbine nozzle includes outer and inner bands between which extend a plurality of vanes for channeling combustion gases. Each of the vanes includes leading and trailing edges, and pressure and suction sides extending therebetween, and also a bow along the trailing edge to increase pressure in the gases adjacent the inner band. The vanes also include a thermal barrier coating (TBC) selectively disposed solely along the suction side between the leading and trailing edges.

US Patent:

7249928, Jul 31, 2007

Filed:

Apr 1, 2005

Appl. No.:

10/907476

Inventors:

Kevin Samuel Klasing - Springboro OH, US
Scott Michael Carson - Mason OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 25/12

US Classification:

415115, 415191, 4151995, 4152112, 416193 A

Abstract:

A turbine nozzle for a gas turbine engine includes a nozzle segment having an airfoil-shaped vane with a root, a tip, a leading edge, a trailing edge and opposed curved pressure and suction sides. An arcuate inner band segment is attached to the root of the vane. The inner band segment includes an inner flowpath surface bounded at forward and aft ends thereof by a forward-facing surface and an aft-facing surface, respectively. A convex curved blended corner is formed between the inner flowpath surface and the aft-facing surface.

US Patent:

7510371, Mar 31, 2009

Filed:

Jun 6, 2005

Appl. No.:

11/145837

Inventors:

Robert Joseph Orlando - West Chester OH, US
Thomas Ory Moniz - Loveland OH, US
David Glenn Cherry - Loveland OH, US
Robert John Beacock - Cincinnati OH, US
William Larson Clifford - Cincinnati OH, US
Scott Michael Carson - Mason OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F04D 29/44

US Classification:

415191, 415193

Abstract:

A turbine nozzle includes a row of vanes joined to radially outwardly inclined outer and inner bands. Each vane has camber and an acute twist angle for importing swirl in combustion gases discharged at trailing edges thereof. The trailing edges are tilted forwardly from the inner band to the outer band for increasing aerodynamic efficiency.

US Patent:

7513102, Apr 7, 2009

Filed:

Jun 6, 2005

Appl. No.:

11/145875

Inventors:

Thomas Ory Moniz - Loveland OH, US
Scott Michael Carson - Mason OH, US
Robert Joseph Orlando - West Chester OH, US
David Glenn Cherry - Loveland OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02K 3/00
F02K 3/02
F02C 1/06

US Classification:

60268, 602261, 60 39162

Abstract:

A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation. First stage stator vanes in the low pressure turbine have camber and twist for carrying swirl directly between the rotor blades of the high and low pressure turbines.

US Patent:

7758306, Jul 20, 2010

Filed:

Dec 22, 2006

Appl. No.:

11/615514

Inventors:

Scott Andrew Burton - Cincinnati OH, US
Chander Prakash - Cincinnati OH, US
Joseph Machnaim - Bangalore, IN
David Glenn Cherry - Loveland OH, US
Robert John Beacock - Cincinnati OH, US
Scott Michael Carson - Mason OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 1/02

US Classification:

4152091, 4151995

Abstract:

A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.

US Patent:

7806653, Oct 5, 2010

Filed:

Dec 22, 2006

Appl. No.:

11/615556

Inventors:

Scott Andrew Burton - Cincinnati OH, US
Chander Prakash - Cincinnati OH, US
Joseph Machnaim - Bangalore, IN
David Glenn Cherry - Loveland OH, US
Robert John Beacock - Cincinnati OH, US
Scott Michael Carson - Mason OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 9/00

US Classification:

415191

Abstract:

A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.

US Patent:

7819626, Oct 26, 2010

Filed:

Oct 13, 2006

Appl. No.:

11/580789

Inventors:

Aspi Rustom Wadia - Loveland OH, US
David Glenn Cherry - Loveland OH, US
Scott Michael Carson - Mason OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 11/20
F01D 11/24

US Classification:

4151732, 415176, 415178, 415914

Abstract:

A gas turbine engine plasma blade tip clearance control system includes an annular shroud surrounding rotatable blade tips and an annular plasma generator spaced radially outwardly and apart from the blade tips. An exemplary embodiment of the annular plasma generator is mounted to the annular shroud and includes radially inner and outer electrodes separated by a dielectric material disposed within an annular groove in a radially inwardly facing surface of the annular shroud. The plasma generator is operable for producing an annular plasma between the annular shroud and blade tips and an effective clearance produced by the annular plasma between the annular shroud and blade tips that is smaller than a clearance between the annular shroud and blade tips.

US Patent:

7870719, Jan 18, 2011

Filed:

Oct 13, 2006

Appl. No.:

11/580788

Inventors:

Aspi Rustom Wadia - Loveland OH, US
David Glenn Cherry - Loveland OH, US
Scott Michael Carson - Mason OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02H 1/00

US Classification:

60202, 3133621

Abstract:

A plasma enhanced rapidly expanded duct system includes a gas turbine engine inter-turbine transition duct having radially spaced apart conical inner and outer duct walls extending axially between a duct inlet and a duct outlet. A conical plasma generator produces a conical plasma along the outer duct wall. An exemplary embodiment of the conical plasma generator is mounted to the outer duct wall and including radially inner and outer electrodes separated by a dielectric material. The dielectric material is disposed within a conical groove in a radially inwardly facing surface of the outer duct wall. An AC power supply is connected to the electrodes to supply a high voltage AC potential to the electrodes.