A system includes an air manifold, a fuel manifold, and a plurality of fuel injectors. At least one of the fuel injectors includes a heat exchanger portion for supplying compressed, cooled air form the heat exchanger portion to the air manifold. An air valve is operatively connected to an outlet of the air manifold for controlling release of air from the air manifold. A controller is operatively connected to the air valve, wherein the controller includes machine readable instructions configured to control the air valve to regulate flow of air through the air valve based on fuel temperatures in the fuel channel. The machine readable instructions can be configured to cause the controller to flow air through the air valve in a heat exchange mode if a fuel temperature in the fuel injectors is below a predetermined fuel temperature.

A system includes an air manifold, a fuel manifold and plurality of fuel injectors. Each fuel injector includes a fixture portion, a nozzle outlet, and a heat exchanger portion connecting between the fixture portion and the nozzle outlet. An air channel and a fuel channel are in thermal communication with one another for heat exchange between fuel and air passing through the heat exchanger portion. The respective inlet of the fuel channel of each of the fuel injectors in the plurality of fuel injectors is connected to the fuel manifold for fluid communication of fuel from the fuel manifold to the nozzle outlets for combustion. The respective outlet of the air channel of each of the fuel injectors in the plurality of fuel injectors is connected to the air manifold for fluid communication of air from the heat exchanger portions into the air manifold.

A monolithic combustion liner for use in a gas turbine engine includes fuel channels integrated into the wall of the combustion liner. The integrated fuel channels can have an aerodynamic shape to reduce flow losses of cooling air flowing around the exterior of the combustion liner. The monolithic combustion liner allows more cooling air to flow around the combustion liner, increasing the cooling of the combustor region of the gas-turbine engine.

A swirler assembly includes a swirler having a primary swirler and a secondary swirler, and a flare connected the secondary swirler, and a dome disposed radially outward of the flare. A flare oxidizer flow passage is defined by a flare outer surface and a dome inner surface, and the flare oxidizer flow passage includes a swirl inducing member therewithin that induces a swirled flow of an oxidizer passing through the flare oxidizer flow passage into a combustion chamber.

A fuel injector is provided for a turbine engine. This fuel injector includes a fuel nozzle, and the fuel nozzle includes a gallery, one or more feed passages and a plurality of exit passages. The gallery extends within the fuel nozzle circumferentially around an axis between a first end of the gallery and a second end of the gallery. A size of the gallery changes as the gallery extends circumferentially around the axis between the first end of the gallery and the second end of the gallery. The one or more feed passages extend within the fuel nozzle to the gallery. The one or more feed passages are configured to supply fuel to the gallery. The exit passages extend within the fuel nozzle from the gallery. The exit passages are configured to receive the fuel from the gallery.

In one aspect of the present disclosure, there is provided a nozzle assembly comprises a first fuel conduit defined between a nozzle body and a fuel swirler and extending along a longitudinal axis from an inlet of the first fuel conduit to an outlet of the fuel nozzle assembly. A second fuel conduit is defined between the fuel swirler and a heat shield and extending along the fuel swirler along the longitudinal axis from an inlet of the second fuel conduit to the outlet of the fuel nozzle assembly. An air conduit extends through the heat shield along the longitudinal axis from an inlet of the air conduit to the outlet of the fuel nozzle assembly.

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.

Fuel injectors having a fuel-air heat exchange system and methods thereof for use in a gas turbine engine. The fuel-air heat exchanger allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine to transfer heat to the flow of fuel and cool the cooling air.

A fuel distribution device is provided wherein an axis is defined. The device comprises a body housing a distribution path for fuel; the distribution path has one inlet and a plurality of outlets; the inlet is located on the external surface of the body at an end of an inlet branch of the distribution path; the plurality of outlets are located on the external surface of the body at ends of a corresponding plurality of outlet branches of the distribution path; the inlet branch and the outlet branches are fluidly connected to a distribution space; and the outlet branches are arranged radially.

A fuel injector includes a forward end wall and an aft end wall. The fuel injector further includes side walls that extend between the forward end wall and the aft end wall. The forward end wall, the aft end wall, and the side walls collectively define an opening for passage of air. At least one fuel injection member is disposed within the opening and extends between the end walls. A fuel circuit is defined within the fuel injector. The fuel circuit includes an inlet plenum defined within the forward end wall of the fuel injector. The fuel circuit further includes a fuel passage that extends from, and is in fluid communication with, the inlet plenum. The fuel passage is defined within the at least one fuel injection member. The fuel passage has a cross-sectional area that varies along a length of the fuel injection member.