General Electric Company

General Electric Environmental Services, Inc.

Mitchell R Cohen

Warren James Mick

Eli Gal

Michael B Sciocchetti

Melvin Robert Jackson

Lewis Berkley Davis, Jr

Ann Melinda Ritter

Nesim Abuaf

Constantinos Minas

David Orus Fitts

Adrian M Beltran

David Robert Schumacher

Sanjay M Correa

William Theodore Bechtel

Robert Patrick Campbell

Lance Gordon Peterson

Ross Anthony McLean

Jeffrey Alan Graves

Myron Clyde Muth

A combustor/transition piece for a gas turbine including a double walled structure having a plurality of cooling channels, both axially and, in some cases, circumferential cross-flow passages positioned between the structure's inner member and the outer member to provide cooling air thereto, are formed in the area between the inner member of the combustor and the outer member thereof. The passages preferably extend both axially and circumferentially with respect to the direction of flow through the combustor/transition piece. The axial passages extend completely from one end to the other and the circumferential passages extend around the circumference of the combustor/transition piece. The addition of a circumferential cross-flow passage connecting axial flow coolant passages in double wall turbine components can prevent combustor/transition piece part failure due to axial passage inlet blockage without affecting normal, unblocked cooling. Double wall cooling structures are constructed using two unbonded members. The inner member is machined to form cooling passages. Differential thermal expansion (expansion of the outside diameter of the hot inner wall until contact is established with the inside diameter of the cooler outer wall) keeps the cylinders held tightly together. Double wall cooling structures are also constructed using two members shrink-fitted and then bonded together such as by welding. The inner member is machined to form the cooling passages. The improved thermal contact between the outer and inner members due to the joint reduces the thermally induced stresses in the two members.

Combustor for a gas turbine with cooling structure

A liquid fuel injector nozzle for a gas turbine combustor delivers liquid fuel to the combustion chamber in discrete jets. The liquid fuel injector nozzle includes a fuel passage that terminates with a swirl pilot including a plurality of swirl slots for imparting swirl to the liquid fuel. The spin chamber disposed downstream of the swirl pilot is configured to deliver the liquid fuel to the discharge orifice in discrete jets. The discrete fuel streams are concentrated in a fashion to minimize atomization until the fuel adequately penetrates the premixer air stream, resulting in burning properties that lead to increased efficiency, lower emissions, greater flame stability and improved pattern factor when compared to hollow cone spray pattern injection techniques.

Air atomized discrete jet liquid fuel injector and method

A method of operating a combustor for a turbine in the premixed mode includes flowing fuel through a symmetrical annular array of fuel nozzles to provide an asymmetrical fuel pattern across the combustor. Each nozzle includes an air swirler and the fuel is injected at axially spaced locations on opposite sides of the swirler. The asymmetrical fuel flow is provided during a diffusion mode of operation prior to transition between the diffusion mode and also during the transition. Near full power, the fuel is supplied equally among the fuel nozzles operating in the premixed mode. The asymmetric fuel flow stabilizes the combustor and inhibits high amplitude combustion noise and the axial staging of the fuel achieves low emission operation in the premixed mode.

Method for staging fuel in a turbine in the premixed operating mode

A method of operating a combustor for a turbine includes flowing fuel through a symmetrical annular array of fuel nozzles to provide an asymmetrical fuel pattern across the combustor. The asymmetrical fuel flow is provided during a diffusion mode of operation prior to transition between the diffusion mode and a premixed mode of operation, during the transition and during the premixed mode of operation. Near full power, the fuel is supplied equally among the fuel nozzles operating in the premixed mode. The asymmetric fuel flow stabilizes the combustor and inhibits high amplitude combustion noise while achieving low emission operation in the premixed mode.

Method for staging fuel in a turbine between diffusion and premixed

A process and system for simultaneously removing from a gaseous mixture, sulfur oxides by a solid sulfur oxide acceptor sorbent on a porous carrier, nitrogen oxides by ammonia gas and particulate matter by filtration and for the regeneration of loaded solid sulfur oxide acceptor sorbent. Finely-divided solid sulfur oxide acceptor sorbent is entrained in a gaseous mixture to deplete sulfur oxides from the gaseous mixture, the finely-divided solid sulfur oxide acceptor sorbent being dispersed on a porous carrier material having a particle size up to about 200 microns. In the process, the gaseous mixture is optionally prefiltered to remove particulate matter and thereafter finely-divided solid sulfur oxide acceptor sorbent is injected into the gaseous mixture to form an entrained bed. Ammonia gas is also injected into the exhaust gas stream. A filter separates spent solid sorbent and particulate matter from clean gas. A classifier is used to separate mixtures of spent sorbent from particulate matter. A regenerator receives spent sorbents for regeneration and regenerated finely-divided solid sorbent is passed from the regenerator to the entrained bed reactor. A preferred sorbent is copper oxide on porous alumina carrier.

Regenerative system for the simultaneous removal of particulates and the

A process and system for simultaneously removing from a gaseous mixture, sulfur oxides by means of a solid sulfur oxide acceptor on a porous carrier, nitrogen oxides by means of ammonia gas and particulate matter by means of filtration and for the regeneration of loaded solid sulfur oxide acceptor. Finely-divided solid sulfur oxide acceptor is entrained in a gaseous mixture to deplete sulfur oxides from the gaseous mixture, the finely-divided solid sulfur oxide acceptor being dispersed on a porous carrier material having a particle size up to about 200 microns. In the process, the gaseous mixture is optionally pre-filtered to remove particulate matter and thereafter finely-divided solid sulfur oxide acceptor is injected into the gaseous

Regenerative process and system for the simultaneous removal of

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Troy, NY, United States of America

Mitchell R Cohen