General Electric Company

John Drake Vanselow

Patrick Benedict Melton

David William Cihlar

Robert Joseph Rohrssen

Russell Pierson DeForest

Jonathan Dwight Berry

Lucas John Stoia

Wei A Chen

Ronald James Chila

Matthew Paul Berkebile

Jerome David Brown

Thomas Edward Johnson

Christian Xavier Stevenson

Kwanwoo Kim

Hsin-Pang Wang

Abdul Rafey Khan

James Harold Westmoreland

Donald Mark Bailey

Mark Allan Hadley

Jesse Ellis Barton

Michael Charles Ostrowski

Stephen Gerard Pope

Eric Moran

Luis Flamand

Glenn David Nelson

Erich Daniel Charters

Edward Richard Haupt

Patrick Bendict Melton

A late lean injection combustor assembly may include a first interior in which a first fuel supplied thereto is combustible, a flow sleeve annulus including a second interior in which a second fuel supplied thereto is combustible, at least one fuel injector disposed about the second interior, and at least one elongate premixing conduit disposed about the flow sleeve annulus and in fluid communication with the at least one fuel injector. The at least one elongate premixing conduit may be in fluid communication with a compressor discharge air and the second fuel such that the compressor discharge air and the second fuel are premixed within the elongate premixing conduit before entering the second interior by way of the at least one fuel injector.

Systems and methods for late lean injection premixing

A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements.

Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same

An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, the impingement sleeve includes a body configured to at least partially surround a transition piece of the combustor. The impingement sleeve further includes a plurality of cooling holes defined in the body, the plurality of cooling holes having a cooling hole pattern configured to provide a desired operational value for the transition piece. At least one of the plurality of cooling holes has a chamfer extending at least partially between an inlet and an outlet of the at least one of the plurality of cooling holes. At least a portion of the plurality of cooling holes are generally longitudinally asymmetric.

Impingement sleeve and methods for designing and forming impingement sleeve

Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. At least one shroud is secured to the baffle plate and includes at least one piston ring disposed at the shroud. The at least one piston ring is configured to meter a flow of diluent between the at least one shroud and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a piston ring gap defined by at least one piston ring disposed at a baffle plate and a fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the piston ring gap toward at least one airflow hole in the fuel nozzle.

Method and apparatus for introducing diluent flow into a combustor

A system includes a combustor transition piece configured to mount between a combustor and a turbine of a gas turbine engine. The combustor transition piece includes a hollow body with an internal flow passage extending from an upstream end portion to a downstream end portion. The combustor transition piece also includes an aft frame coupled to the downstream end portion of the hollow body, an aft flange coupled to the aft frame, and a mounting lug removably coupled to the aft frame at a first joint. The mounting lug is configured to removably couple to a mounting bracket at a second joint.

System for mounting combustor transition piece to frame of gas turbine engine

A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.

Gas turbine engine combustor with lobed, three dimensional contouring

An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, a method for designing an impingement sleeve is disclosed. The method includes determining a desired operational value for a transition piece, inputting a combustor characteristic into a processor, and utilizing the combustor characteristic in the processor to determine a cooling hole pattern for the impingement sleeve, the cooling hole pattern comprising a plurality of cooling holes, at least a portion of the plurality of cooling holes being generally longitudinally asymmetric, the cooling hole pattern providing the desired operational value.

A combustor assembly for a turbomachine includes combustor housing and a flow sleeve arranged between the combustor housing and a combustor liner. The flow sleeve defines a first annular fluid passage, and a second annular fluid passage. A quaternary cap is mounted to the combustor housing. The quaternary cap includes a first fluid plenum fluidly connected to the first annular fluid passage, a second fluid plenum fluidly connected to the second annular fluid passage, and a plurality of vanes fluidly connected to each of the first and second fluid plenums. Each of the plurality of vanes includes a body portion having a first fluid channel coupled to the first fluid plenum, and a second fluid channel coupled to the second fluid plenum. The first fluid channel extends completely through the body portion and the second fluid channel extends partially into the body portion.

Combustor assembly for a turbomachine

Disclosed herein is a spray coating process for a robotic spray gun assembly comprising importing a discretized model of an object geometry to be coated; importing a numerically characterized spray pattern file; importing a robot motion file comprising a plurality of motion positions, dwell times and orientations defining a spray direction of the robotic spray gun; reading each motion position within the motion file; determining which portions of the object geometry are visible at each motion position; computing a void volume fraction at each visible portion of the object geometry based on the core compression, the incident angle of the robotic spray gun and the ricocheting of the spray for each motion position; and calculating total coating thickness on portions of the object geometry for the complete motion step.

Methods for controlling plasma spray coating porosity on an article and articles manufactured therefrom

Growing community of inventors

Taylors, SC, United States of America

John Drake Vanselow