John R Greene

US Patent:

7029228, Apr 18, 2006

Filed:

Dec 4, 2003

Appl. No.:

10/728198

Inventors:

Sze Bun Brian Chan - Greer SC, US
John Ellington Greene - Greenville SC, US
Linda Jean Farral - Greenville SC, US

Assignee:

General Electric Company - Schenecady NY

International Classification:

F01D 25/12

US Classification:

415 1, 415115, 415139

Abstract:

A turbine nozzle includes, in an exemplary embodiment, an outer band portion, an inner band portion at least one nozzle vane extending between the inner band portion and the outer band portion, and at least one cooling channel extending axially at least partially through at least one of the outer band portion and the inner band portion. The at least one nozzle vane, the inner band portion, and the outer band portion define a flowpath for flowing hot gases of combustion. Each cooling channel includes at least one inlet with each inlet isolated from the flowing hot gases of combustion.

US Patent:

7094025, Aug 22, 2006

Filed:

Nov 20, 2003

Appl. No.:

10/716449

Inventors:

Brian Peter Arness - Simpsonville SC, US
John Ellington Greene - Greenville SC, US
Linda Jean Farral - Greenville SC, US
Sze Bun Brian Chan - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F04D 29/44

US Classification:

415189, 415191, 4152092, 4152093

Abstract:

Nozzle segments are secured to a retention ring against circumferential rotation by anti-rotation pins extending generally axially between the outer bands of the nozzle segments and the retention ring. Retention plate segments overlie the ends of the pins, preventing axial removal thereof. To remove a selected nozzle segment, inner diameter retention plate segments and selected retention plate segments are removed, the latter exposing the ends of the pins for axial withdrawal. Upon removal of a predetermined number of pins, the nozzle segments adjacent the selected segment are displaced away from the latter segment to open a gap between the selected segment and adjacent segments whereby the selected segment can be removed in an axial direction.

US Patent:

7329093, Feb 12, 2008

Filed:

Jan 27, 2006

Appl. No.:

11/340577

Inventors:

Thomas W. Vandeputte - Simpsonville SC, US
John E. Greene - Greenville SC, US
Peter C. Selent - Taylors SC, US
Linda J. Farral - Greenville SC, US
Sze Bun Brian Chan - Greer SC, US
Brian P. Arness - Simpsonville SC, US

Assignee:

General Electric Company - Schnectady NY

International Classification:

F01D 9/00

US Classification:

415191, 416223 A, 416DIG 2

Abstract:

First stage stator vanes for a turbine comprised airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I, which define a plurality of radially spaced profile sections forming the nominal profile. The Z coordinate values for each profile section are radial distances from the turbine axis to a portion of the surface of revolution about the axis containing the profile section. The X and Y values for each profile section are coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion. The radially spaced profile sections are joined smoothly with one another to form the nominal airfoil profile.

US Patent:

7600970, Oct 13, 2009

Filed:

Dec 8, 2005

Appl. No.:

11/164866

Inventors:

Nitin Bhate - Rexford NY, US
Thomas Allen Wells - West Chester OH, US
Ian Francis Prentice - Cincinnati OH, US
John Greene - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 9/02

US Classification:

415191, 415200, 4152112, 4152094, 4152101

Abstract:

A ceramic matrix composite nozzle assembly. The ceramic matrix composite nozzle assembly may include a ceramic matrix composite vane, a number of metallic components positioned about the ceramic matrix composite vane, and a number of metallic seals positioned between the ceramic matrix composite vane and one or more of the metallic components.

US Patent:

7625170, Dec 1, 2009

Filed:

Sep 25, 2006

Appl. No.:

11/526501

Inventors:

John Greene - Greenville SC, US
Ronald Ralph Cairo - Greer SC, US
Paul Steven Dimascio - Greer SC, US
Nitin Bhate - Rexford NY, US
Jason Thurman Stewart - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 11/00

US Classification:

415110, 4152094, 4152101

Abstract:

A method for assembling a gas or steam turbine is provided. The method includes providing an insulator and positioning the insulator between a vane support and a vane such that the insulator facilitates preventing hot gas migration into the vane, and such that during operation, hot gas is channeled from a high pressure side of the vane to a low pressure side of the vane. A vane assembly for a turbine rotor assembly is also provided. The vane assembly includes a vane support and an insulator including a projecting portion. The assembly also includes a vane. The insulator is coupled to the vane support such that the projecting portion is between the vane and a nozzle support strut to facilitate hot gas flow from a pressure side of the projecting portion to a suction side of the projecting portion.

US Patent:

8038389, Oct 18, 2011

Filed:

Jan 4, 2006

Appl. No.:

11/325185

Inventors:

Brian P. Arness - Simpsonville SC, US
John E. Greene - Greenville SC, US
Sze Bun B. Chan - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 9/04

US Classification:

415190, 415189, 4152092, 4152094, 4152101, 60752, 60796, 60800

Abstract:

A turbine nozzle assembly and a method for assembling the turbine nozzle assembly with respect to a combustor of a gas turbine engine are provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles are provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.

US Patent:

8398374, Mar 19, 2013

Filed:

Jan 27, 2010

Appl. No.:

12/694834

Inventors:

Herbert Chidsey Roberts - Simpsonville SC, US
John Ellington Greene - Greenville SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/28

US Classification:

416193R, 416223 A

Abstract:

A turbine bucket that includes a platform and an airfoil extending radially outward from the platform. The airfoil includes a root segment and a tip segment. The root segment includes a first end and a second end. The root first end extends from a radially outer surface of the platform. The root segment extends from the root first end to the root second end. The tip segment includes a tip first end and a tip second end. The tip first end is removably coupled to the root second end. The tip segment extends outward from the root second end to the tip second end.

US Patent:

8403634, Mar 26, 2013

Filed:

Aug 24, 2011

Appl. No.:

13/216347

Inventors:

Brian P. Arness - Simpsonville SC, US
John E. Greene - Greenville SC, US
Sze Bun B. Chan - Greer SC, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 9/04

US Classification:

415135, 415136, 415190, 415189, 4152092, 4152094, 4152101, 60752, 60796, 60800

Abstract:

A retaining seal assembly for use in a gas turbine engine is provided. The retaining seal assembly comprises an outer retaining ring coupled to an aft end of a gas turbine engine combustor. A turbine nozzle is coupled to the outer retaining ring and comprises an outer band. The outer band comprises a leading edge and an opposing trailing edge that defines a slot. A retention seal comprises a first end positioned within the slot, a generally opposing second end that contacts the outer retaining ring, and a body extending between the first end and the second end. The body further comprises an insertion portion positioned within a passage formed in the outer band. The retention seal is fabricated from a resilient material and is configured to facilitate coupling the turbine nozzle to the outer retaining ring.