JOSEPH D MONTY
Engineering in Boxford, MA

6675582, Jan 13, 2004

May 23, 2001

09/864019

Joseph Douglas Monty - Boxford MA
John C. Jacobson - Melrose MA

General Electric Company - Schenectady NY

F23R 306

60752, 60756, 60757

A combustor liner for use in a gas turbine engine includes an annular panel section having a cooling nugget formed on one end thereof. An annular cooling lip is formed on the cooling nugget so as to define a cooling slot. The cooling lip includes a hot side, a cold side and a trailing edge surface. The hot side defines a compound taper for minimizing the thickness of the trailing edge surface. In one embodiment, the compound taper includes a first tapered surface disposed on a forward portion of the cooling lip and a second tapered surface disposed on an aft portion of the cooling lip, wherein the second tapered surface has a greater taper than the first tapered surface.

6519850, Feb 18, 2003

Jul 10, 2002

10/192576

Timothy P. Mc Caffrey - Swampscott MA
Frank A. Lastrina - Andover MA
Joseph D. Monty - Boxford MA
David E. Hrencecin - Peabody MA

General Electric Company - Schenectady NY

B21D 5300

2989001

A combustor liner has a stepped combustor liner surface defining a combustion zone and an overhang portion forming an air cooling slot. A layer of thermal barrier material is applied to the combustor liner such that at least one portion of the combustor liner receives a layer of thermal barrier material with a thickness greater than 0. 01 inches. Thus, the combustor liner absorbs less heat, and the combustor may operate at higher temperatures. As a result, low cycle fatigue and thermal creep are reduced within the combustor and the life cycle for the combustor is extended.

6438958, Aug 27, 2002

Feb 28, 2000

09/513943

Timothy P. McCaffrey - Swampscott MA
Frank A. Lastrina - Andover MA
Joseph D. Monty - Boxford MA
David E. Hrencecin - Peabody MA

General Electric Company - Schenectady NY

F23R 300

60752, 60756

A combustor liner has a stepped combustor liner surface defining a combustion zone and an overhang portion forming an air cooling slot. A layer of thermal barrier material is applied to the combustor liner such that at least one portion of the combustor liner receives a layer of thermal barrier material with a thickness greater than 0. 01 inches. Thus, the combustor liner absorbs less heat, and the combustor may operate at higher temperatures. As a result, low cycle fatigue and thermal creep are reduced within the combustor and the life cycle for the combustor is extended.

7325403, Feb 5, 2008

Mar 26, 2007

11/728387

Aureen Cyr Currin - Reading MA, US
Kamil Bazyli Kaczorowski - Warszawa, PL
John Carl Jacobson - Melrose MA, US
Joseph Douglas Monty - Boxford MA, US

General Electric Company - Schenectady NY

F23R 3/14

60772, 2989002

A method for fabricating a dome assembly for a gas turbine engine combustor includes forming an annular dome plate including a plurality of substantially circular eyelets circumferentially spaced thereon, coupling a seal plate to the dome plate at each eyelet such that an opening defined in each seal plate is aligned substantially concentrically with respect to a respective eyelet, coupling a baffle to each seal plate such that an opening defined in each baffle is aligned substantially concentrically with respect to a respective eyelet, and coupling a swirler assembly having an integrally formed swirler and flare cone to each seal plate such that the flare cone extends at least partially through the baffle opening, and such that cooling air may be directed towards the flare cone through openings formed in the assembly.

7246494, Jul 24, 2007

Sep 29, 2004

10/953318

Aureen Cyr Currin - Reading MA, US
Kamil Bazyli Kaczorowski - Warsaw, PL
John Carl Jacobson - Melrose MA, US
Joseph Douglas Monty - Boxford MA, US

General Electric Company - Schenectady NY

F23R 3/14

60748, 60752

A method for fabricating a dome assembly for a gas turbine engine combustor includes forming an annular dome plate including a plurality of substantially circular eyelets circumferentially spaced thereon, coupling a seal plate to the dome plate at each eyelet such that an opening defined in each seal plate is aligned substantially concentrically with respect to a respective eyelet, coupling a baffle to each seal plate such that an opening defined in each baffle is aligned substantially concentrically with respect to a respective eyelet, and coupling a swirler assembly having an integrally formed swirler and flare cone to each seal plate such that the flare cone extends at least partially through the baffle opening, and such that cooling air may be directed towards the flare cone through openings formed in the assembly.

5623827, Apr 29, 1997

Jan 26, 1995

8/378703

Joseph D. Monty - Boxford MA

General Electric Company - Cincinnati OH

F23R 360

60748

A dome assembly for a single annular combustor of a gas turbine engine is disclosed as having a first dome wall in flow communication with compressed air supplied to the combustor, the first dome wall including a central opening therein and at least one cooling passage therethrough. A baffle is spaced downstream of and connected to the first dome wall at radially outward and inward ends, the baffle also including a central opening therein. A second dome wall defining the central opening in the first dome wall is provided which extends upstream of the first dome wall. A venturi is located within the central opening of the first dome wall, with the venturi including a flange extending radially outward from the central opening, wherein the second dome wall is connected to the flange at an upstream end. A flare cone is located within the central opening of the baffle and radially outward of the venturi, wherein a substantially radial passage is provided between the venturi flange and the flare cone, the radial passage having a swirler located therein. Accordingly, a chamber is formed by the first dome wall, the second dome wall, the baffle, the venturi, and the flare cone, the chamber being in flow communication with the compressed air entering the combustor by means of the cooling passage in the first dome wall, whereby the compressed air impinges on the baffle, circulates in the chamber, and exits through the swirler.

7013649, Mar 21, 2006

May 25, 2004

10/853091

Joseph Douglas Monty - Boxford MA, US

General Electric Company - Schenectady NY

F02C 7/22, F02K 3/14

60748

A gas turbine engine combustor fuel-air mixer includes a body having a substantially annular venturi and a longitudinal axis therethrough, an upstream end, a downstream end, and an inner surface. A primary radial jet swirler upstream of the venturi includes a plurality of radially extending primary air jets circumferentially and downstream angled with respect to the longitudinal axis. A plurality of axial jets axially extend through the primary swirler air and are circumferentially disposed around the longitudinal axis. An exemplary embodiment of the fuel-air mixer further includes the axial jets and the inner surface of a throat of the venturi being radially located at a radius from the longitudinal axis. The axial jets are located in an insert mounted to an upstream portion of the primary radial jet swirler and axially forward of the plurality of radially extending primary air jets. At least some of the axial jets have jet centerlines that intersect primary swirler centerlines of corresponding ones of the primary air jets downstream of outlets of the primary air jets.

5123248, Jun 23, 1992

Mar 28, 1990

7/501071

Joseph D. Monty - Boxford MA
Thomas G. Hill - Lynnfield MA
Jacob S. Hoffman - Ipswich MA

General Electric Company - Lynn MA

F02C 100, F02G 300

60740

A combustor effective for reducing exhaust emissions is disclosed. The combustor includes first and second liners defining a primary combustion zone, and a plurality of circumferentially spaced carburetors. Each of the carburetors includes a fuel injector providing fuel into an air swirler for mixing the air and fuel and providing a fuel/air mixture into the combustor primary zone. The combustor also includes means for obtaining a fuel distribution from each of the carburetors extending radially from a first liner upstream end through a center region of the combustor to a second liner upstream end with values of the fuel distribution at the center region being generally no greater than about values of the fuel distribution adjacent to at least one of the first and second liners. The first and second liners have upstream portions characterized by the absence of film cooling thereof.

6279323, Aug 28, 2001

Nov 1, 1999

9/431464

Joseph D. Monty - Boxford MA
John C. Jacobson - Melrose MA

General Electric Company - Cincinnati OH

F02G 300

60752

A combustor includes outer and inner liners joined at one end to an annular dome. A swirl cup is mounted to the dome and includes a flare cone extending therethrough. The flare cone has an obtuse flare angle for discharging fuel in a wide spray from an outlet of the cone. A flared beat shield surrounds the cone, and extends in part aft from the cone outlet, and is offset in part forwardly from the cone outlet to define a radially outwardly facing step.

6260359, Jul 17, 2001

Nov 1, 1999

9/431465

Joseph D. Monty - Boxford MA
John C. Jacobson - Melrose MA

General Electric Company - Cincinnati OH

F02C 314

60752

A combustor liner includes a row of primary dilution holes disposed aft of a forward end thereof, and a row of secondary dilution holes disposed between the primary holes and an aft end of the liner. The secondary holes vary in size circumferentially to a maximum size offset circumferentially from the primary holes.