Abstract: An additive manufacturing apparatus includes: a coater including: at least one trough including a plurality of side-by-side deposition valves.

Abstract: An additive manufacturing apparatus includes: a coater including: at least one trough including a plurality of side-by-side deposition valves.

Abstract: The present disclosure is directed to a gas turbine engine including a housing circumferentially surrounding an electric machine. The electric machine is supported within the housing. The housing defines a cooling passage proximate to the electric machine. The cooling passage circumferentially surrounds the electric machine and is extended at least partially along a lengthwise direction of the electric machine. The cooling passage provides a flow of fluid therethrough.

Abstract: The present disclosure generally relates to methods for additive manufacturing (AM) that utilize integrated ribs to support thin walled annular structures. An annular wall fabricated using AM has a thickness less than 0.022 inches across a majority of a surface of the annular wall and a plurality of ribs having a thickness greater than 0.030 inches. The annular wall has a mean thickness less than 0.100 inches. The annular wall conforms to a surface of the component and a mean distance between the annular wall and the component is less than 0.080 inches.

Abstract: A system includes a gas turbine engine having a first combustor and a second combustor. The first combustor includes a first fuel conduit having a first plurality of injectors. The first plurality of injectors are disposed in a first configuration within the first combustor along a first fuel path, and the first plurality of injectors are configured to route a fuel to a first combustion chamber. The system further includes a second combustor having a second fuel conduit having a second plurality of injectors. The second plurality of injectors are disposed in a second configuration within the second combustor along a second fuel path, and the second plurality of injectors are configured to route the fuel to a second combustion chamber. The second configuration has at least one difference relative to the first configuration.

Abstract: A system includes an oxidant compressor and a gas turbine engine turbine, which includes a turbine combustor, a turbine, and an exhaust gas compressor. The turbine combustor includes a plurality of diffusion fuel nozzles, each including a first oxidant conduit configured to inject a first oxidant through a plurality of first oxidant openings configured to impart swirling motion to the first oxidant in a first rotational direction, a first fuel conduit configured to inject a first fuel through a plurality of first fuel openings configured to impart swirling motion to the first fuel in a second rotational direction, and a second oxidant conduit configured to inject a second oxidant through a plurality of second oxidant openings configured to impart swirling motion to the second oxidant in a third rotational direction. The first fuel conduit surrounds the first oxidant conduit and the second oxidant conduit surrounds the first fuel conduit.

Abstract: The present disclosure generally relates to methods for additive manufacturing (AM) that utilize rail support structures in the process of building objects, as well as novel rail support structures to be used within these AM processes. The rail support structures include a plurality of substantially parallel vertical walls, each wall extending substantially parallel to a direction from the first side to the second side. Adjacent walls of the plurality of substantially parallel vertical walls are separated by a portion of unfused powder. An object is formed above the plurality of substantially parallel vertical walls.

Abstract: A system and method for reducing modal coupling of combustion dynamics generally include multiple combustors, and each combustor includes multiple fuel nozzle groups for mixing fuel with a compressed working fluid prior to combustion. A fuel circuit is in fluid communication with each fuel nozzle, and orifice plates in the fuel circuit upstream from the fuel nozzles control the fuel split between the fuel nozzles in each combustor and/or between different combustors to produce a frequency difference between combustors.

Abstract: A gas turbine engine system including a first combustor having a first fuel nozzle and a second combustor having a second fuel nozzle. The system further includes a first acoustic adjuster having a first drive coupled to a first piston with a first fuel orifice. The first piston is disposed along a first fuel passage leading to the first fuel nozzle of the first combustor. The system further includes a second acoustic adjuster having a second drive coupled to a second piston with a second fuel orifice. The second piston is disposed along a second fuel passage leading to the second fuel nozzle of the second combustor.

Abstract: A system and method for reducing modal coupling of combustion dynamics among multiple combustors are provided. Each combustor may include one or more fuel nozzles axially aligned with a combustion chamber; one or more fuel injectors downstream from the fuel nozzles; and a set of flow openings integrated with the combustor. The fuel injectors provide fluid communication through a liner that circumferentially surrounds each combustion chamber. The flow rate of compressed working fluid diverted through the fuel injectors may be different and/or variable between the combustors to produce different combustion instability frequencies.

Abstract: An additive manufacturing apparatus includes: a coater including: at least one trough including a plurality of side-by-side deposition valves.

Abstract: An additive manufacturing apparatus includes: a support surface configured to support a build platform thereon; a powder dispenser disposed above the support surface, the powder dispenser configured to dispense powder, and movable laterally over the support surface; a scraper moveable over the build platform and configured to scrape powder dispensed thereon by the powder dispenser, so as to provide a layer increment of powder above the build platform; and a directed energy source configured to melt and fuse the layer increment of powder in predetermined pattern so as to form a part.

Abstract: Embodiments of the present application include a combustor assembly. The combustor assembly may include a combustion chamber, a first plenum, a second plenum, and one or more elongate air/fuel premixing injection tubes. Each of the elongate air/fuel premixing injection tubes may include a first length at least partially disposed within the first plenum and configured to receive a first fluid from the first plenum. Moreover, each of the elongate air/fuel premixing injection tubes may include a second length disposed downstream of the first length and at least partially disposed within the second plenum. The second length may be formed of a porous wall configured to allow a second fluid from the second plenum to enter the second length and create a boundary layer about the porous wall.

Abstract: 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.

Abstract: A nozzle for use in a combustor of a combustion turbine engine, the nozzle including: radial sections defined by sidewalls; a gap formed between opposing sidewalls of adjacent ones of the radial sections; a groove formed on each of the sidewalls that define the gap, the grooves positioned correspondingly so to together form a pocket; and a seal having a zigzagging profile disposed within the pocket. The pocket may intercept the gap over a seal length, and the seal may extend longitudinally within the pocket such that the zigzagging profile intersects the gap over the seal length.

Abstract: A system includes a gas turbine engine having a first combustor and a second combustor. The first combustor includes a first fuel conduit having a first plurality of injectors. The first plurality of injectors are disposed in a first configuration within the first combustor along a first fuel path, and the first plurality of injectors are configured to route a fuel to a first combustion chamber. The system further includes a second combustor having a second fuel conduit having a second plurality of injectors. The second plurality of injectors are disposed in a second configuration within the second combustor along a second fuel path, and the second plurality of injectors are configured to route the fuel to a second combustion chamber. The second configuration has at least one difference relative to the first configuration.

Abstract: A gas turbine engine system including a first combustor having a first fuel nozzle and a second combustor having a second fuel nozzle. The system further includes a first acoustic adjuster having a first drive coupled to a first piston with a first fuel orifice. The first piston is disposed along a first fuel passage leading to the first fuel nozzle of the first combustor. The system further includes a second acoustic adjuster having a second drive coupled to a second piston with a second fuel orifice. The second piston is disposed along a second fuel passage leading to the second fuel nozzle of the second combustor.

Abstract: A system and method for reducing modal coupling of combustion dynamics generally include multiple combustors, and each combustor includes multiple fuel nozzle groups for mixing fuel with a compressed working fluid prior to combustion. A fuel circuit is in fluid communication with each fuel nozzle, and orifice plates in the fuel circuit upstream from the fuel nozzles control the fuel split between the fuel nozzles in each combustor and/or between different combustors to produce a frequency difference between combustors.

Abstract: A system and method for reducing modal coupling of combustion dynamics among multiple combustors are provided. Each combustor may include one or more fuel nozzles axially aligned with a combustion chamber; one or more fuel injectors downstream from the fuel nozzles; and a set of flow openings integrated with the combustor. The fuel injectors provide fluid communication through a liner that circumferentially surrounds each combustion chamber. The flow rate of compressed working fluid diverted through the fuel injectors may be different and/or variable between the combustors to produce different combustion instability frequencies.

Abstract: A gas turbine includes one or more combustors, and each combustor may include one or more fuel nozzles for mixing fuel with a compressed working fluid prior to combustion. The gas turbine further includes various structures for reducing the modal coupling of the combustion dynamics by producing a different convective time, fuel flow, and/or compressed working fluid flow through at least one fuel nozzle.