General Electric Company

Marcus Byron Huffman

Wei A Chen

Scott Robert Simmons

Donald Mark Bailey

Matthew Paul Berkebile

Joseph Vincent Pawlowski

Dullal Ghosh

Saurav Dugar

Krishnakumar Pallikara Gopalan

Gilbert Otto Kraemer

Ronnie Ray Pentecost

Donald Timothy Lemon

Kyle Lee Kidder

Kesavan Dhanasekaran

Stephen Wayne Tilley

David James Taylor

Clamping device including sheet metal, wedge-washers, and fastening members. Sheet metal includes first segments and second segment, where each of the first and second segments include conduit-facing end and outwardly-extending end. Conduit-facing ends are joined to each other and wrapped around conduit in opposite directions. Outwardly-extending ends extend in opposite direction to outwardly-extending end. Each outwardly-extending end is bent at bend angle towards a respective conduit-facing end. Wedge-washers are disposed on first and second segments. Each wedge-washer includes sidewall inclined in a direction opposite to bend angle and in contact with a respective outwardly-extending end. Fastening members are disposed on respective wedge-washer.

Clamping device and an associated method thereof

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

A fuel nozzle assembly for a gas turbine engine includes a flange and a pre-mix tube. The flange includes a first end that is configured to couple to an end cover of the combustor, and a second end that is opposite said first end. The pre-mix tube is coupled at a first end to the flange second end. The flange and the pre-mix tube are fabricated to operate at a natural frequency that is different from an operating frequency of the gas turbine engine.

Fuel nozzle assembly for a gas turbine engine

A system, including a combustor cap assembly, including a first plate configured to divide a combustion chamber from a head end chamber of a combustor, a first sleeve disposed about the first plate, and a first stiffening rib coupled to the combustor cap assembly, wherein the combustor cap assembly is configured to mount in a combustor, and the first stiffening rib is configured to damp vibration caused by combustion dynamics in the combustor.

System for reducing vibrational motion in a gas turbine system

A method and apparatus are described that include a transition piece including a cooling sleeve. The cooling sleeve includes a first end and an opposite second end, the cooling sleeve is coupled to an inner wall of the transition piece, such that an annular passage is defined between the inner wall and the cooling sleeve. The first end defines an annular inlet and second end defines an annular outlet.

Method and apparatus to enhance transition duct cooling in a gas turbine engine

A method of assembling a fuel nozzle assembly for a gas turbine engine having a natural operating frequency includes providing a flange and providing a premix tube. The flange is fabricated from a first alloy such that the flange is configured to exhibit a first frequency that is different than the natural operating frequency of the gas turbine engine. The premix tube is fabricated from a second alloy such that the premix tube is configured to exhibit a second frequency that is different from the natural operating frequency of the gas turbine engine. The premix tube is coupled to the flange.

Fuel nozzle assembly that exhibits a frequency different from a natural operating frequency of a gas turbine engine and method of assembling the same

A combustor includes a combustion chamber and an interior wall circumferentially surrounding at least a portion of the combustion chamber and defining an exterior surface. A plurality of turbulators are on the exterior surface. The combustor further includes means for preferentially directing fluid flow across a predetermined position of the turbulators. A method for cooling a combustion chamber includes locating a plurality of turbulators to an exterior surface of the combustion chamber and preferentially directing fluid flow across a predetermined position of the plurality of turbulators.

Apparatus and method for cooling a combustor

A combustor for a gas turbine includes a first combustor component and a second combustor component. The second combustor component is at least partially insertable into the first combustor component, and the first combustor component and second combustor component define a combustion fluid pathway. A combustor seal is located between the first combustor component and the second combustor component. The combustor seal defines at least one inner cooling pathway between the combustor seal and the second combustor component and at least one outer cooling pathway between the combustor seal and the first combustor component for cooling the first combustor component and second combustor component. A method for cooling a first combustor component and a second combustor component is also disclosed.

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Simpsonville, SC, United States of America

Marcus Byron Huffman