General Electric Company

Donald Timothy Lemon

Patrick Benedict Melton

Wei A Chen

Keith Cletus Belsom

Gilbert Otto Kraemer

Richard Martin DiCintio

Ronald James Chila

Kwanwoo Kim

David William Cihlar

Donald Mark Bailey

Ronnie Ray Pentecost

Bradley Donald Crawley

Christopher Paul Willis

William Lawrence Byrne

Marcus Byron Huffman

Stephen Gerard Pope

Kyle Lee Kidder

Matthew Eugene Roberts

Mert Enis Berkman

Larry Lou Thomas

Ajay Kumar Gupta

David Kevin Spikings

Willis Christopher Paul Paul

A fuel injector is provided for the radial introduction of a liquid fuel/air mixture to a combustor. The fuel injector includes a body having a frame that defines an inlet portion and an outlet member that defines an outlet portion. A fuel plenum is defined within the outlet member, and a fuel injection port, which communicates with the fuel plenum, is defined through the outlet member. A fuel supply conduit, fixed to the body, communicates between a source of liquid fuel and the fuel injection port, via the fuel plenum. Alternately, the fuel injector may include a swirl-inducing device mounted to the outlet member in communication with the fuel injection port, and a fuel supply conduit fixed to the swirl-inducing device. In this embodiment, the fuel supply conduit communicates between the fuel injection port and a source of a liquid fuel and water mixture, via the swirl-inducing device.

Dual fuel injectors and methods of use in gas turbine combustor

An interface assembly for a combustor includes an interface housing having a channel defined by a forward wall and at least one aft wall segment, the aft wall segment operatively coupled to an aft flange of a flow sleeve. Also included is a piston ring fittingly disposed in the channel.

Interface assembly for a combustor

A transition piece aft frame assembly is provided, and includes a transition piece aft frame and a heat shield. The transition piece aft frame has an aft face. At least a portion of the aft face is exposed to an exhaust gas stream. The heat shield is connected to the transition piece aft frame. The heat shield is oriented to generally deflect the exhaust gas stream away from the aft face of the transition piece aft frame.

Transition piece aft frame assembly having a heat shield

A combustor casing fuel injector in a combustor of a combustion turbine engine, the combustor including a combustor casing that encloses internal structure of the combustor, wherein the combustor casing fuel injector includes a fuel manifold adjacent to an outer surface of the combustor casing. In certain embodiments, the combustor casing fuel injector includes a fuel injector; wherein the fuel injector extends through the combustor casing from a position within the fuel manifold to a predetermined fuel injection location; and wherein the fuel injector includes a protruding injector inlet within the fuel manifold.

Apparatus and systems relating to fuel injectors and fuel passages in gas turbine engines

An endcover assembly for a turbine combustor adapted to support one or more combustor nozzles includes a substantially flat plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel passage extends through the substantially flat plate. A fuel manifold porting block is secured to the opposite side of the flat plate with at least one port aligned with the at least one passage. A fuel restrictor insert formed with multiple flow orifices is located between the flat plate and the fuel manifold porting block in alignment with the at least one fuel passage and the at least one port.

Gas turbine combustor endcover assembly with integrated flow restrictor and manifold seal

An annular seal for use between coupled combustor components includes a segmented annular solid edge portion and a plurality of alternating spring fingers and slots extending from the solid edge portion and arranged about a circumference of the solid edge portion, wherein one or more of the plurality of spring fingers or one or more of the plurality of straight and angled slots have non-uniform width dimensions.

Hula seal with preferential cooling having spring fingers and/or adjacent slots with different widths

A combustor liner for a combustor of a turbine engine includes a single-walled generally cylindrical liner that extends from a head end to an aft end. A venturi is formed on the combustor liner at a location between the head and aft ends. The venturi is formed by first and second straight portions of the combustor liner that angle inward to form a reduced diameter portion. The combustor liner may also include an air deflector to deflect air down onto the exterior of the reduced diameter portion of the single-walled combustor liner. The combustor liner may also include dilution holes, and turbulator rings.

Combustor liner for a turbine engine with venturi and air deflector

The endcover assembly for a combustor includes an endcover having an aperture, an insert disposed in the stepped bore opening through an internal face of the endcover, a fuel cartridge extending through the insert and aperture and a seal cover on the external face of the endcover. Seal cover/endcover annular seals are disposed in registering axial cavities to seal against fluid leakage externally of the endcover assembly. Generally C-shaped and W-shaped seals are disposed in the cavities between the stepped shoulders of the insert and aperture to seal against leakage through the internal face of the endcover. The seals maintain sealing engagement during assembly and thermal distortion during turbine usage.

Turbine combustor endcover assembly

Variations in dilution air leakage paths in a gas turbine combustion liner assembly are minimized or eliminated to reduce emissions and variations in emissions from combustor to combustor. Leakage paths between the liner sleeve and venturi outer liner are minimized by using additional rivets at that joint. The leakage paths between the outer and inner sleeves of the venturi are eliminated by applying a peripheral weld to the end edges of the flanges of the outer and inner sleeves. The leakage paths between the venturi and outer liner are minimized while simultaneously maintaining accurate venturi throat area relative to the cap centerbody by match drilling holes through the liner sleeve and the overlapped flanges of the venturi and followed by riveting the parts together.

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Greenville, SC, United States of America

Donald Timothy Lemon