Robert F Proctor

US Patent:

6550254, Apr 22, 2003

Filed:

Aug 17, 2001

Appl. No.:

09/932585

Inventors:

Robert Proctor - West Chester OH
Julius John Montgomery - Mason OH
Michael Jay Epstein - Mason OH
Roger Owen Barbe - Montgomery OH
Hai Buu Sam - Hamilton OH
James Bernar Ogzewalla - Maysville KY
Andrew David Kemp - Loveland OH
Bryan Keith Doloresco - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 608

US Classification:

60785, 415144

Abstract:

A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.

US Patent:

6722137, Apr 20, 2004

Filed:

Aug 17, 2001

Appl. No.:

09/932596

Inventors:

Robert Proctor - West Chester OH
John William Hanify - West Chester OH
Debra Lynn Prikkel - Dayton OH
Michael Jay Epstein - Mason OH
Julius John Montgomery - Mason OH

Assignee:

General Electric Co. - Schenectady NY

International Classification:

F16K 122

US Classification:

60782, 60785, 251305, 415178, 123337

Abstract:

A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides.

US Patent:

7048496, May 23, 2006

Filed:

Oct 31, 2002

Appl. No.:

10/285891

Inventors:

Robert Proctor - West Chester OH, US
James Patrick Dolan - Cincinnati OH, US
John Christopher Brauer - Lawrenceburg IN, US
Christopher Charles Glynn - Hamilton OH, US
Kenneth Martin Lewis - Middletown OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 25/12

US Classification:

415115, 415116, 4151745, 415 69, 416 95, 416128, 416204 A

Abstract:

A rotor system for a gas turbine engine is provided having an outer rotor which includes an annular outer spool that comprises at least one ring portion of increased thickness with respect to the remainder of the outer spool, attached to a relatively thinner, axially extending arm portion. A plurality of outer turbine blades are attached to the ring portion of the outer spool and extend radially inwardly into a working gas flowpath of the engine. A casing surrounds the outer spool and defines an annular cavity between the casing and the outer spool, which is sealed by forward and aft brush seals at the forward and aft ends thereof. At least one inlet port is formed through the casing for admitting a flow of cooling air to the annular cavity. Means are provided for directing this cooling air flow to the ring portion of the outer spool.

US Patent:

7341429, Mar 11, 2008

Filed:

Nov 16, 2005

Appl. No.:

11/280439

Inventors:

Julius John Montgomery - Mason OH, US
Robert Proctor - West Chester OH, US
Nathan Gerard Cormier - Cincinnati OH, US
Christopher Charles Glynn - Hamilton OH, US
Glen William Royal - Cincinnati OH, US
Richard William Jendrix - Liberty Township OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F03B 11/00

US Classification:

416 97R, 415115, 4151701

Abstract:

A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine mid-frame such that a cavity is defined between the rotor disk and the turbine mid-frame, and forming at least one opening extending through the turbine mid-frame to facilitate channeling cooling air into the gap, the opening configured to impart a high relative tangential velocity into the cooling air discharged from the opening.

US Patent:

7363762, Apr 29, 2008

Filed:

Nov 16, 2005

Appl. No.:

11/280440

Inventors:

Julius John Montgomery - Mason OH, US
Robert Proctor - West Chester OH, US
Nathan Gerard Cormier - Cincinnati OH, US
Christopher Charles Glynn - Hamilton OH, US
Glen William Royal - Pasadena CA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 3/04

US Classification:

60685, 415104, 415107, 415111, 4151735, 4151745, 29464, 298892, 2988922

Abstract:

A method of assembling a gas turbine engine includes providing a gas turbine engine including a compressor, a combustor downstream from the compressor, and a turbine coupled to the compressor, and coupling a seal assembly aft of the compressor such that air discharged through the seal assembly facilitates reducing the cavity pressure, and therefore reducing the axial forces induced to an aft side of the compressor.

US Patent:

7717667, May 18, 2010

Filed:

Sep 29, 2006

Appl. No.:

11/541715

Inventors:

Ryan Michael Urbassik - Cincinnati OH, US
Scott Anthony Estridge - Cincinnati OH, US
Rafael Ruiz - Liberty Township OH, US
Robert Proctor - West Chester OH, US
Robert J. Albers - Park Hills KY, US
Kevin Stephen Hansell - Okeana OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F04D 31/00
F01D 11/24

US Classification:

415 1, 415116

Abstract:

A method for operating a gas turbine engine is provided. The gas turbine engine includes a fan, a high pressure turbine coupled downstream from the fan, and a low pressure turbine downstream from the high pressure turbine. The method includes channeling a portion of air discharged from the fan through a clearance control system including an inlet assembly that includes a plurality of louvers, and directing air from the inlet assembly into a first pipe and second pipe coupled to the inlet assembly such that pressure losses associated with the airflow are facilitated to be reduced.

US Patent:

7935164, May 3, 2011

Filed:

Nov 28, 2007

Appl. No.:

11/946111

Inventors:

Ning Fang - West Chester OH, US
Duane Howard Anstead - Fairfield OH, US
Robert Proctor - West Chester OH, US
Pradeep Hemant Sangli - Bangalore, IN
Prasad Laxman Kane - Pune, IN
Gary Paul Moscarino - Cincinnati OH, US
Bala Corattiyil - Cincinnati OH, US
Ray Harris Kinnaird - Fort Thomas KY, US
David William Pugh - Fairfield OH, US
Mark Eden Zentgraf - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B01D 46/18
B01D 46/30

US Classification:

55406, 55DIG 19, 553853, 55400, 96216

Abstract:

The present invention provides a vortex generator that may be used in systems for separating oil from air oil mixtures. The vortex generator comprises a rotating disk having a rim having a plurality of passages extending through it and a cavity formed by the rotating disk and a cavity wall wherein a vortex is created when there is a flow through the plurality of passages into the cavity.

US Patent:

8292034, Oct 23, 2012

Filed:

Nov 28, 2007

Appl. No.:

11/946103

Inventors:

James Kevin Mount - Cincinnati OH, US
Richard Walker Nicholson - Cincinnati OH, US
Duane Howard Anstead - Fairfield OH, US
Robert Proctor - West Chester OH, US
Pradeep Hemant Sangli - Bangalore, IN
Prasad Laxman Kane - Pune, IN
Mark Leonard Hopper - West Chester OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B05B 12/00

US Classification:

184 611, 138 89, 60 3908

Abstract:

The present invention provides an air-oil separator comprising a first region having a mixture of air and oil, a second region wherein separation of at least some of the oil from the air-oil mixture occurs and at least one multi-directional injector plug located on a rotating component in flow communication with the first region and the second region, the multi-directional injector plug having a discharge head that is oriented such that at least a part of the air-oil mixture discharged therefrom has a component of velocity that is tangential to the direction of rotation of the rotating component.