George H Cook

US Patent:

53076370, May 3, 1994

Filed:

Jul 9, 1992

Appl. No.:

7/910911

Inventors:

Richard W. Stickles - Loveland OH
Howard L. Foltz - West Chester OH
Keith K. Taylor - Cincinnati OH
George E. Cook - Cincinnati OH
Thomas MacLean - Loveland OH
Willard J. Dodds - West Chester OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F23R 304

US Classification:

60756

Abstract:

A gas turbine engine combustor is provided with a combustor dome plate film cooling means having an annular slotted ring to provide a film starting means upstream of a multi-hole film cooled single wall metal dome plate which is annular in shape. One particular embodiment provides a starting slot in the form of a plurality of rings surrounding the edges of the air/fuel nozzle inlet apertures in the dome plate. The cooling holes are disposed in concentric circles about the apertures and angled along radii emanating from the center of the apertures. This produces a cooling film emanating radially from the ring like circular slots around each air/fuel nozzle inlet aperture in the dome plate. Another embodiment provides a starting slot in the form of circumferential rails circumferentially disposed about the inner and outer circumferential edges of dome plate. The cooling holes are arranged in two section, the first to feed a radially inward directed cooling film that is initiated from an outer starting slot on a radially outer circumferential edge of the plate.

US Patent:

58516794, Dec 22, 1998

Filed:

Dec 17, 1996

Appl. No.:

8/768264

Inventors:

William R. Stowell - Rising Sun IN
John F. Ackerman - Cheyenne WY
Andrew J. Skoog - West Chester OH
George E. Cook - Cincinnati OH
Glenn E. Varney - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B32B 1706

US Classification:

428472

Abstract:

A metal or ceramic matrix composite part and corresponding method are provided exhibiting desired heat transfer characteristics. The part has a metal or ceramic matrix composite substrate and a multilayer dielectric coating. The coating has high reflectivity at wave lengths corresponding to radiation wavelengths of various combustion gases and has low reflectance at radiation wavelengths corresponding to the substrate. The multilayer coating allows the heat generated external of the part at wavelengths corresponding to combustion gases to be reflected from the part while permitting radiation wavelengths associated with the substrate to pass through the coating. The parts are useful for use in combustive gas atmospheres.

US Patent:

52318338, Aug 3, 1993

Filed:

Jun 1, 1992

Appl. No.:

7/891925

Inventors:

Thomas MacLean - Loveland OH
George E. Cook - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 100
F02G 300

US Classification:

60734

Abstract:

A fuel manifold is disclosed for providing fuel to a combustor disposed radially inside an annular casing. The manifold is disposed inside the casing and includes an arcuate manifold tube, a thermal insulation layer surrounding the tube, and a cover layer surrounding the insulation layer which is substantially rigid for protecting the insulation layer from physical damage.

US Patent:

52398188, Aug 31, 1993

Filed:

Mar 30, 1992

Appl. No.:

7/860635

Inventors:

Richard W. Stickles - Loveland OH
Willard J. Dodds - West Chester OH
Paul E. Sabla - Cincinnati OH
George E. Cook - Cincinnati OH
Craig L. Loconti - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 300
F23R 316

US Classification:

60 3936

Abstract:

An annular combustor includes a plurality of circumferentially spaced, radially extending dilution poles disposed in an intermediate zone thereof between a forward combustion zone and an aft combustion zone. Adjacent ones of the dilution poles define therebetween a throat for receiving the combustion gases from the forward zone. The dilution poles include circumferentially facing dilution holes for injecting dilution air into the throats for mixing with the combustion gases being channeled therethrough. The dilution poles are effective for blocking the combustion gases at a plurality of circumferentially spaced apart locations and accelerating the combustion gases through the throats for reducing residence time in the throat. The dilution air is injected through the dilution holes for improved penetration into the combustion gases in the throats for mixing therewith to form lean combustion gases which undergo final combustion in the aft zone for reducing NO. sub. x emissions.

US Patent:

57716960, Jun 30, 1998

Filed:

Oct 21, 1996

Appl. No.:

8/734164

Inventors:

Harold R. Hansel - Mason OH
George E. Cook - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 722

US Classification:

60739

Abstract:

A gas turbine engine fuel injection assembly includes a combustor case surrounding a combustor having a dome. An arcuate manifold is disposed inside the combustor case adjacent to the dome, and includes a plurality of fuel injectors disposed in flow communication therewith for receiving fuel for injection into the combustor. An inlet stem is joined in flow communication with the manifold for channeling fuel thereto, and includes an inner fitting disposed in a mounting port in the combustor case. A mounting adaptor is joined to the combustor case at the mounting port, and circumferentially engages the inner fitting to restrain torsional movement thereof. An outer fitting extends in the adaptor and engages the inner fitting in flow communication therewith for supplying fuel thereto.

US Patent:

59161426, Jun 29, 1999

Filed:

Oct 21, 1996

Appl. No.:

8/734163

Inventors:

Charles A. Snyder - Liberty IN
Harold R. Hansel - Mason OH
George E. Cook - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 720
F02G 300

US Classification:

60748

Abstract:

A swirler is provided for mixing air from a compressor and fuel from a fuel injector for discharge into a dome of a gas turbine engine combustor. The swirler includes a tubular ferrule for coaxially receiving the fuel injector. A plurality of circumferentially spaced apart swirl vanes are fixedly joined coaxially with the ferrule. An outlet tube is fixedly joined coaxially with the swirl vanes in flow communication therewith for receiving air from the swirlers and fuel from the fuel injector. An annular collar is fixedly joined around the outlet tube and has a convex spherical outer surface. An annular mounting flange for mounting the swirler to the combustor dome has a concave spherical inner surface disposed coaxially around the collar outer surface in a sliding fit therewith to define a ball joint for allowing relative rotation therebetween for self-aligning the fuel injector with the swirler.