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

Abstract: A system includes a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome. An injector defines a spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the spray axis. An actuator is operatively connected to the injector for movement of the injector relative combustor dome to adjust a relative position of the spray axis relative to the main axis to alter the position and/or direction of the spray injector during operation of the gas turbine engine.

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 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 torch igniter system for a combustor of a gas turbine engine includes a housing defining a combustion chamber, an ignition source disposed at least partially in the combustion chamber, a fuel injector, a first fluid path connecting a first fuel source to the fuel injector, a second fluid path connecting an air source to the fuel injector, and a third fluid path connecting a second fuel source to the combustion chamber. The fuel injector is configured to inject fuel, air, or a mixture of fuel and air into the combustion chamber and to impinge on the ignition source.

Abstract: A system includes a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome. An injector defines a spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the spray axis. An actuator is operatively connected to the injector for movement of the injector relative combustor dome to adjust a relative position of the spray axis relative to the main axis to alter the position and/or direction of the spray injector during operation of the gas turbine engine.

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 and secondary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the primary circuit, adapted and configured to actively control fuel through the primary circuit in response to a control signal.

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 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: 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 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: 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 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: 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 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.

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.