Abstract: A tile for a combustor dome of a gas turbine engine includes a tile body defining an upstream surface and an axially opposed downstream surface with at least one injection orifice defined through the tile body from the upstream surface to the downstream surface. The tile body extends in a radial direction from a radially inner surface to a radially outer surface. The radially inner and outer surfaces define circular arcs that are concentric with one another. The tile body extends circumferentially from a first end face to a second end face. The first end face follows a sigmoid profile and the second end face follows a sigmoid profile configured to interlock with the sigmoid profile of the first end face of another identical tile body.

Abstract: An internal fuel manifold for a turbomachine can include an outer ring defining one or more fuel supply channels configured to allow fuel flow around at least a portion of a circumference of the outer ring, and a plurality of branches extending radially inward from the outer ring. The branches include a high aspect ratio shape. The plurality of branches can include one or more branch fuel channels in fluid communication with at least one of the one or more fuel supply channels. The manifold includes one or more injector connectors extending axially aft from each branch, each injector connector in fluid communication with a branch fuel channel and configured to connect to a fuel injector. The manifold can include an inner ring extending from the plurality of branches. The inner ring and the outer ring are configured to receive a fuel injector and combustor assembly therebetween and to allow retaining of the fuel injector assembly and combustor assembly to the internal fuel manifold.

Abstract: A multipoint injection system includes a manifold with a plurality of flow passages defined through the manifold in the circumferential direction. The flow passages are spaced apart from one another in an axial direction. A plurality of feed arms extends radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms to respective outlets. The feed arm portions of the flow passages are within the axial width of the manifold. A plurality of injection nozzles are included, each in fluid communication with a respective one of the outlets. Each injection nozzle includes an air passage therethrough with an air inlet. The feed arms each follow a path that is circumferentially offset from the air inlets so each of the feed arms is clear from a flow path directly upstream in the axial direction of each of the air inlets.

Abstract: A multipoint injection system includes a manifold with a plurality of flow passages defined through the manifold in the circumferential direction. The flow passages are spaced apart from one another in an axial direction. A plurality of feed arms extends radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms to respective outlets. The feed arm portions of the flow passages are within the axial width of the manifold. A plurality of injection nozzles are included, each in fluid communication with a respective one of the outlets. Each injection nozzle includes an air passage therethrough with an air inlet. The feed arms each follow a path that is circumferentially offset from the air inlets so each of the feed arms is clear from a flow path directly upstream in the axial direction of each of the air inlets.

Abstract: A fuel injector for a turbomachine includes an outer heat shield configured to sit on and/or within a combustor dome to orient the fuel injector relative to the combustor dome and/or a fuel manifold. An inner surface of the outer heat shield includes an outer heat shield seal surface. The injector also includes a fuel prefilmer seated at least partially within the outer heat shield. An outer surface of the fuel prefilmer includes a prefilmer seal surface configured to mate with the outer heat shield seal surface such that the fuel prefilmer seats on the outer heat shield seal surface and such that the prefilmer seal surface is configured to allow the surfaces to slide relative to one another in both a radial and axial direction.

Abstract: An internal fuel manifold for a turbomachine can include an outer ring defining one or more fuel supply channels configured to allow fuel flow around at least a portion of a circumference of the outer ring, and a plurality of branches extending radially inward from the outer ring. The branches include a high aspect ratio shape. The plurality of branches can include one or more branch fuel channels in fluid communication with at least one of the one or more fuel supply channels. The manifold includes one or more injector connectors extending axially aft from each branch, each injector connector in fluid communication with a branch fuel channel and configured to connect to a fuel injector. The manifold can include an inner ring extending from the plurality of branches. The inner ring and the outer ring are configured to receive a fuel injector and combustor assembly therebetween and to allow retaining of the fuel injector assembly and combustor assembly to the internal fuel manifold.

Abstract: A fuel injector for a turbomachine includes an inner heat shield having an air cavity wall defining an air cavity for allowing air to flow therethrough. The inner heat shield includes an integral air swirler forming a downstream end thereof. The integral air swirler extends in an axially downstream direction at least as far as a fuel distribution channel defined on or in a fuel distributor of the injector to direct airflow at an outlet of the fuel distributor.

Abstract: A fuel injector for a multipoint injection system can include a body defining an air cavity for allowing air to flow therethrough and an interior cavity. A fuel is tube disposed at least partially within the interior cavity of the body. The fuel tube can include a first end configured to connect to a fuel injector connector of a fuel manifold, and a second end configured to connect to a fuel distributor of the fuel injector, wherein the fuel injector is configured to be disposed at least partially in a combustor dome. The fuel tube is configured to move in an axial direction to allow flexibility between the fuel manifold and the combustor dome.

Abstract: In accordance with at least one aspect of this disclosure, a fuel injector can include an annular body defining a gas fuel inlet therein, and a structure extending radially outward from the annular body and configured to extend into an air circuit. The structure can include a gas channel defined within the structure at least partially along a radial length of the structure. The gas channel is in fluid communication with the gas fuel inlet where the structure meets the annular body. The structure also includes a slot opening defined at least partially along a radial length of the structure and configured to fluidically connect the gas channel and the air circuit to all gas fuel to effuse into the air circuit.

Abstract: A fuel cell nozzle includes a fuel circuit receiver configured to receive a fuel circuit and an air circuit. At least a portion of the air circuit is integrally formed with the fuel circuit receiver. The nozzle can further include a base portion that is configured to interface with a fuel cell. The fuel circuit receiver and the air circuit can extend from the base portion.

Abstract: A nozzle is provided including a nozzle body having an upstream end and a downstream end aligned about a central axis. A discharge portion is positioned adjacent the downstream end. A bore extends inwardly from the downstream end over the length of the discharge portion. An opening is formed in the nozzle body adjacent the discharge portion. The opening is fluidly connected to the bore to provide an interior air flow passage. A main fuel channel extends from the upstream end to the discharge portion. At least one fuel flow branch extends through the discharge portion between the bore and an outer surface of the nozzle body. The fuel flow branch is fluidly coupled to the main fuel conduit to provide a fuel flow passage. The outer air cap is positioned about the outer surface of the discharge portion of the nozzle body to form an exterior air flow passage.

Abstract: A fuel cell nozzle includes a fuel circuit receiver configured to receive a fuel circuit and an air circuit. At least a portion of the air circuit is integrally formed with the fuel circuit receiver. The nozzle can further include a base portion that is configured to interface with a fuel cell. The fuel circuit receiver and the air circuit can extend from the base portion.

Abstract: A method of additive manufacturing includes building a component having a top surface, attaching the component to a powder bed fusion plate that receives the component, filling the powder bed fusion chamber so the powder is flush with the top surface of the component, and adding a first layer of powdered metal level with the top surface of the component. The method of additive manufacturing also includes fusing the first layer of powdered metal to the top surface of the component to create a fusion joint, and building up an additively manufactured body from the top surface of the component in subsequent layers.

Abstract: A nozzle assembly includes a fuel distributor for issuing a spray of fuel. A fuel conduit is in fluid communication with the fuel distributor and has a first end and a second end. The first end and/or the second end of the fuel conduit is operatively connected to the fuel distributor. The fuel conduit is configured to allow relative movement between the first end and the second end to accommodate dimensional variations of at least one of the nozzle assembly or a combustor. A nozzle system includes the nozzle assembly and a combustor wall having a nozzle inlet. The nozzle assembly is positioned adjacent to the nozzle inlet.

Abstract: A combustor dome system includes an annular combustor dome defining a main axis therethrough. The combustor dome includes opposed upstream and downstream faces, wherein the upstream face is configured to face upstream toward a compressor discharge space, wherein the downstream face is configured to face downstream toward a combustor space. The downstream face has a curved cross-sectional profile. A plurality of nozzles extends at least partially through the combustor dome from the upstream face to the downstream face for injection of fuel into the combustor space. A fuel manifold is in fluid communication with the plurality of nozzles.

Abstract: A fuel injector for a gas turbine engine includes a monolithic nozzle body that defines within its interior one or more fuel circuits. Each fuel circuit includes an inlet, an outlet orifice, a main passage fluidly coupling the inlet with the outlet orifice, and a branch passage connected to the main passage. The branch passage connects to the main passage downstream of the inlet and upstream of the outlet orifice to form an effective metering flow area that is smaller than the flow area of the outlet orifice.

Abstract: A fuel cell nozzle includes a fuel circuit receiver configured to receive a fuel circuit and an air circuit. At least a portion of the air circuit is integrally formed with the fuel circuit receiver. The nozzle can further include a base portion that is configured to interface with a fuel cell. The fuel circuit receiver and the air circuit can extend from the base portion.

Abstract: In accordance with at least one aspect of this disclosure, a fuel injector system can include an air mixer defining an outer air circuit, at least one intermediate air circuit, and an inner air circuit. The fuel injector system can also include a fuel manifold defining a fuel circuit, at least a portion of which is operatively disposed within the air mixer such that the fuel circuit and the intermediate air circuit are in fluid communication with each other for atomization of fuel. At least one of the air mixer or the fuel manifold can be additively manufactured.

Abstract: A fuel injector for a gas turbine engine includes a monolithic nozzle body that defines within its interior one or more fuel circuits. Each fuel circuit includes an inlet, an outlet orifice, a main passage fluidly coupling the inlet with the outlet orifice, and a branch passage connected to the main passage. The branch passage connects to the main passage downstream of the inlet and upstream of the outlet orifice to form an effective metering flow area that is smaller than the flow area of the outlet orifice.

Abstract: A sealing device is provided for use with an assembly having radially inner and outer parts in fluid communication and movable relative to one another. The sealing device includes a first annular lip which defines an opening for receiving the radially inner part, and an annular channel disposed radially outward of the opening. The first annular lip is configured and adapted for deformation and compressive sealed engagement with the radially inner part while permitting movement of the radially inner part relative thereto. An annular body integrally formed with the first annular lip of the sealing device defines an interior space in communication with the annular channel and the opening. The annular body extends radially outward of the first annular lip and is configured and adapted for sealed engagement with the radially outer part.