General Electric Company

Ge Infrastructure Technology, LLC

Robert Joseph Rohrssen

Patrick Benedict Melton

David William Cihlar

Stuart Craig Hanson

Michael Alan Davi

Thomas Alan Mogle, Ii

John Drake Vanselow

Jonathan Dwight Berry

Lucas John Stoia

Abdul Rafey Khan

Donald Mark Bailey

Bradley Donald Crawley

Kyle Joseph Conger

Thomas Edward Johnson

Ronald James Chila

Kwanwoo Kim

Ronnie Ray Pentecost

Mark Allan Hadley

Wayne David Sullivan

Jesse Ellis Barton

Mohan Krishna Bobba

Maxwell Evan Miller

James Joseph Murray, Iii

Clay Thomas Griffis

Chad Joseph Dulkiewicz

Evan John Dozier

Luis Flamand

Jun Yang

John Bryan Pourcho

Nazar Ahmed Elwasila

Glenn David Nelson

Erich Daniel Charters

Michael Ryan Horton

Luis M Flamand

Patrick Bendict Melton

Embodiments of the disclosure relate to the aligning of a melting beam source in an additive manufacturing (AM) system. Methods of the disclosure may include forming a first test article and a second test article of different shapes on a build plate. The method further includes measuring a vertical scale, vertical alignment, horizontal scale, and an alignment of the melting beam source using the first and second test articles. The method includes determining whether one of the vertical scale, the vertical alignment, the horizontal scale, or the horizontal alignment of the melting beam source is not within a corresponding tolerance of a target specification. If at least one of the vertical scale, the vertical alignment, the horizontal scale, or the horizontal alignment is within the corresponding tolerance, the method includes adjusting the melting beam source of the AM system to align the melting beam source to yield the target specification.

Aligning of melting beam source in additive manufacturing system

A fuel supply system for a gas turbine combustor includes a fuel distribution manifold. A first fuel circuit extends from the fuel distribution manifold in a first circumferential direction around an outer surface of the outer casing and provides for fluid communication from the fuel distribution manifold, through the outer casing and to at least one fuel injector disposed within the outer casing. A second fuel circuit extends from the fuel distribution manifold in a second circumferential direction around the outer surface of the outer casing. The second fuel circuit provides for fluid communication from the fuel distribution manifold, through the outer casing and to at least one fuel injector within the outer casing. In particular configurations, the fuel supply system includes a shield that surrounds at least a portion of the outer casing and at least partially encases the first fuel circuit and the second fuel circuit.

Fuel supply system for a gas turbine combustor

Systems for the positioning of equipment are disclosed. A system of the present disclosure can provide an apparatus including: a height adjustable table; an arm support structure coupled to and positioned above the height adjustable table; a length adjustable arm slidably connected to the arm support structure, the length adjustable arm being configured to support a piece of equipment; and an equipment support bracket coupled to the length adjustable arm configured to removably attach the piece of equipment.

System for positioning of equipment

A fuel delivery system for a gas turbine combustor is provided. The fuel delivery system includes a fuel tube and an attachment assembly. The fuel tube extends from a downstream injector (e.g., a late lean injector) towards a mounting ring of the combustor and is moveably attached to the mounting ring using the attachment assembly. Accordingly, the exemplary fuel delivery system may provide fuel to a downstream injector while accommodating a thermal expansion or contraction of the fuel tube along an axial direction of the combustor.

Fuel delivery system with moveably attached fuel tube

Methods for the positioning of equipment are disclosed. One method of the present disclosure can include substantially aligning an equipment support structure with an equipment fixture point of a casing structure; adjusting the equipment support structure to have a selected height and a selected angle; sliding the equipment support structure across a platform having the selected height and the selected angle to reach the equipment fixture point; and coupling a piece of equipment to one of the equipment support structure and the equipment fixture point.

Method for positioning of equipment

Embodiments of the present disclosure include apparatuses and systems used for the positioning of equipment. An apparatus according to an embodiment of the present disclosure can include a height adjustable table; a platform coupled to the height adjustable table; a tilt adjuster coupled to the platform, the tilt adjuster being configured to tilt the platform relative to the height adjustable table; an equipment support structure slidably connected to the platform, the equipment support structure being configured to support a piece of equipment; a drive mechanism coupled to the platform and configured to slidably move the equipment support structure across the platform; and a bracket coupled to the equipment support structure, wherein the bracket is configured to removably attach the piece of equipment.

Apparatus and system for positioning of equipment

One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion.

Combustor cap assembly

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

The present application and the resulting patent provide a pre-nozzle mixing cap assembly positioned about a cap member of a combustor for mixing a flow of air and a flow of fuel. The pre-nozzle mixing cap assembly may include a fuel plenum in communication with the flow of fuel and a number of tubes in communication with the flow of air and extending through the fuel plenum. Each of the tubes may include a number of fuel holes therein such that the flow of fuel in the fuel plenum passes through the fuel holes and mixes with the flow of air.

Combustor with a pre-nozzle mixing cap assembly

A cooling circuit for a fuel nozzle in a gas turbine includes an end cap cavity receiving passive purge flow from a compressor of the turbine, and fuel nozzle swozzles disposed in a swozzle shroud that impart swirl to incoming fuel and air. Purge slots are formed in the swozzle shroud and through the fuel nozzle swozzles in fluid communication with the end cap cavity. The purge slots are positioned upstream of a quat fuel injection passage, and the passive purge flow enters fuel nozzle tip cavities of the fuel nozzle to provide tip cooling and tip purge volume without mixing the passive purge flow with quat fuel.

Fuel nozzle passive purge cap flow

A system for supplying pressurized fluid to a combustor of a gas turbine is disclosed. The system may include an end cover and a fuel nozzle extending from the end cover. The fuel nozzle may include a downstream end. Additionally, the system may include a cap assembly configured to receive at least a portion of the fuel nozzle. The cap assembly may include an upstream wall spaced apart from the downstream end, a downstream wall disposed proximate to the downstream end and a cap chamber defined between the upstream and downstream walls. Moreover, a conduit may extend through the end cover and the upstream wall such that a discharge end of the conduit is in flow communication with the cap chamber.

System for supplying pressurized fluid to a cap assembly of a gas turbine combustor

Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.

Turbine combustor system having aerodynamic feed cap

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

A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an aerodynamic mounting assembly disposed in the air passage. The aerodynamic mounting assembly is configured to retain the combustion liner within the flow sleeve. The aerodynamic mounting assembly includes a flow sleeve mount coupled to the flow sleeve and a liner stop coupled to the combustion liner. The flow sleeve mount includes a first portion of an aerodynamic shape and the liner stop includes a second portion of the aerodynamic shape, which is configured to direct an airflow into a wake region downstream of the aerodynamic mounting assembly. The flow sleeve mount and the liner stop couple with one another to define the aerodynamic shape.

System and method for turbine combustor mounting assembly

A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure.

Growing community of inventors

Greenville, SC, United States of America

Robert Joseph Rohrssen