Abstract: A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet, in response to fuel pressure received at the fuel inlet. Primary, secondary and auxiliary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the auxiliary circuit, which electrically-controlled valve is adapted and configured to actively control fuel through the auxiliary circuit in response to a control signal.

Abstract: A method includes forming fluid conduit inside a heat shield in an additive manufacturing process, removing powder from an interior passage of the fluid conduit and from an insulation gap defined between the fluid conduit and the heat shield, separating the heat shield and fluid conduit from the build platform, and shifting the fluid conduit to a shifted position relative to the heat shield. The method includes securing the fluid conduit to the heat shield in the shifted position.

Abstract: A valve system includes a spin chamber having an outlet drain configured to allow flow out of the spin chamber. A main spin surface of the spin chamber is defined around the outlet drain. A directional jet system is in fluid communication with the spin chamber. The directional jet system includes a member that is configured to move between a first position for directing a tangential flow around the drain, and a second position for directing a radial flow toward the drain.

Abstract: A fuel injector assembly can include a housing structure defining a circular shape, and one or more fuel injectors disposed in and/or formed integrally with the housing structure. The housing structure can be configured to angle the one or more fuel injectors in a direction such that the one or more fuel injectors effuse flow in a vector having a tangential flow component.

Abstract: A method of manufacturing a last chance screen for an aircraft engine includes forming an array of holes through a metal sheet with a wire electrode using electrical discharge machining. The array of holes comprises a plurality of holes. Each hole of the plurality of holes comprises a first end and a second end and is surrounded by a wall section such that the last chance screen is defined by the plurality of holes and the plurality of wall sections. The first and second end of each hole are widened by either applying a flow of an abrasive flow medium to the array of holes in two directions or using a conical sinker electrode on either side of the metal sheet. Shaping the first and second end of each hole results in an airfoil-shaped cross-section of each wall section.

Abstract: A fuel injector assembly has a fuel nozzle including a radial feed arm with an elongated axially extending nozzle portion having a central axis extending therethrough, the elongated nozzle portion has a distal spray tip with a frusto-conical outer surface and a planar front surface, wherein a primary pressure atomizer port is centrally provided in the planar front surface of the distal spray tip and a set of circumferentially spaced apart secondary flat spray slots are provided in the frusto-conical outer surface of the distal spray tip.

Abstract: An airblast fuel injector assembly for a gas turbine engine is disclosed, which includes an annular air swirler and a fuel injector, wherein the annular air swirler includes a main body, an inner air cooler, an inner air swirler and a prefilmer, and wherein the fuel injector includes a feed tube, which has at least one fuel tip projecting through a respective reception hole formed in the annular wall of the main body radially outboard from the inner air swirler.

Abstract: A system includes an engine case for a gas turbine engine defined around a longitudinal axis. An access opening is defined through the engine case for access from outside the engine case to a space inside the engine case. A combustor is housed in the space inside the engine case. The combustor includes an inner annular wall and an outer annular wall radially outboard from the inner annular wall. The inner annular wall includes a first rail on an upstream end thereof. The outer annular wall includes a second rail on an upstream end thereof. The first and second rails each include a respective access portion configured to receive line replaceable injector components from through the access opening of the engine case into the first and second rails to form a combustor dome of the combustor.

Abstract: A system includes an engine case for a gas turbine engine defined around a longitudinal axis. A combustor is housed in the space inside the engine case. The combustor includes an inner annular wall and an outer annular wall radially outboard from the inner annular wall. The inner annular wall includes a first rail on an upstream end thereof with a radially outward opening slot. The outer annular wall includes a second rail on an upstream end thereof. The combustor includes a plurality of circumferentially spaced apart dome liners extending from the first rail to the second rail. A plurality of fuel injector components can be assembled across the first and second rails to form a combustor dome together with the dome liners at an upstream end of a combustion space defined between the inner and outer annular walls of the combustor.

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 method of making a fluid injector for a gas turbine engine includes depositing material onto a piece of tube stock. The method includes machining the deposited material into a fluid injector component. Depositing can include laser cladding the material onto the piece of tube stock. The method can include placing or flowing braze into a braze joint location between the deposited material and another fluid injector component and forming the braze into a braze joint in the braze joint location.

Abstract: A system includes an engine case for a gas turbine engine defined around a longitudinal axis. A plurality of access openings are defined through the engine case. A combustor is housed in the space inside the engine case. The inner annular wall of the combustor includes a first rail on an upstream end thereof with a radially outward opening slot. The outer annular wall of the combustor includes a second rail on an upstream end thereof. A plurality of circumferentially spaced apart dome liners extending from the first rail to the second rail. Each dome liner extends tangentially in a direction oblique relative to a radius extending from the longitudinal axis. A plurality of multipoint fuel injector components are assembled across the first and second rails to from a combustor dome together with the dome liners.

Abstract: A system for depowdering additively manufactured parts includes a deflection plate, a hammer device mounted to a first side of the deflection plate, and a mounting plate operatively connected to a second side of the deflection plate relative to the hammer device, the mounting plate being configured for rotation relative to the deflection plate.

Abstract: A method of cooling a component during laser cladding can include attaching a flow adapter to the component, flowing cooling fluid through the flow adapter, flowing the cooling fluid through the component during laser cladding. Attaching a flow adapter to the component can fluidly communicate at least one adapter channel to one or more component channels, and flowing cooling fluid through the at least one adapter channel can pass cooling fluid through the one or more component channels to cool the component during laser cladding. The method can include laser cladding the component.

Abstract: In accordance with at least one aspect of this disclosure, a nozzle for a fuel injector includes, a nozzle body defining a central axis from a nozzle inlet to a nozzle outlet. A first fuel circuit is defined in the nozzle body configured to issue a first fuel flow from a first outlet orifice into a combustor. A second fuel circuit is defined in the nozzle body radially outward from the first fuel circuit configured to issue a second fuel flow from a second outlet orifice at a prefilmer surface of the nozzle body. A third fuel circuit is defined in the nozzle body radially outward from the second fuel circuit configured to issue a third fuel flow from a third outlet orifice at the prefilmer surface of the nozzle body. In embodiments, the first fuel circuit, the second fuel circuit, and the third fuel circuit can all be fluidly isolated from one another within the nozzle body.

Abstract: A system includes an injector having a scheduling valve assembly and a nozzle in fluid communication with the valve assembly. The scheduling valve assembly is configured for regulation of flow from an inlet of the injector to the nozzle. The injector includes two fluid circuits between the inlet of the injector and two respective outlets of the nozzle for staged flow output from the nozzle. A first one of the two fluid circuits is a primary circuit, and a second one of the two fluid circuits is a secondary circuit. A solenoid valve is connected in fluid communication with the scheduling valve assembly, wherein the solenoid valve is configured to adjust position of a hydromechanical valve spool of the valve assembly.

Abstract: A retention mechanism for releasably securing a receptacle to another component includes a ratchet lever pivotally mounted about a screw, a torsion spring having a first end attached to a first end of the lever and being biased to pivot the lever about the screw axis to a first, locked position. A second end of the lever engages, in use, with teeth provided on the receptacle to secure the receptacle against rotation relative to the other component. The mechanism has a compression spring arranged to bias the lever in an axial position such that, in the first, locked position, the second end of the lever engages the teeth. The first end of the lever is configured to receive pressure from a user against the force of the torsion spring to pivot the lever about the axis such that the second end of the lever disengages from the teeth.

Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage.

Abstract: A combustor section support structure can include a fuel manifold and one or more radial stud assemblies connected to the fuel manifold and configured to allow the fuel manifold to move radially relative to an engine case and to fix the fuel manifold axially relative to the engine case. Each of the one or more radial stud assemblies can include a first portion mounted to the fuel manifold and a second portion configured to mount to an engine case. The first portion and the second portion can be configured to slide relative to each other to allow relative radial movement, but to prevent axial relative movement. A system can include a fuel manifold configured to distribute fuel to one or more fuel nozzles of a turbomachine, and a fuel inlet assembly configured to connect to the fuel manifold through an engine case. The fuel inlet assembly can be configured to axially retain the fuel manifold relative to the engine case and to allow radial movement of the fuel manifold relative to the engine case.

Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle, and a torch igniter within the combustor case. The torch igniter includes a combustion chamber, a cap defining the upstream end of the combustion chamber and configured to receive a fuel injector and a surface igniter, a tip defining the downstream end of the combustion chamber, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip that fluidly connects the combustion chamber to the combustor. The torch igniter is situated such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case.