Abstract: A method for manufacturing a stem for a fuel injector of gas turbine engine includes forging a material into a unitary workpiece, which includes forging a top disk having a cylindrical shape, forging a body extending from a base of the top disk, and forging a lower disk connected to the body, distal to the top disk, the lower disk having a cylindrical shape oriented transverse to the top disk. The method further including machining the lower disk to form a gas gallery having a ring shape, and to define a gallery opening through the gas gallery, and machining a first fluid passage through the top disk, the body, and a portion of the gas gallery to the gallery opening, wherein the first fluid passage is in fluid communication with the gallery opening.

Abstract: A method for manufacturing a metallic component is disclosed. The method includes forming a metallic component with a support structure using an additive manufacturing process. The support structure includes support walls arranged to form flow passages with a predetermined cross-sectional area. The method also includes placing the metallic component with the support structure into a chamber and sealing the chamber. The method further includes introducing a fuel mixture into the chamber after sealing the chamber. The method still further includes igniting the fuel mixture in the chamber to remove one or more of the support walls of the support structure from the metallic component.

Abstract: A method for manufacturing a metallic component is disclosed. The method includes forming a metallic component with a support structure using an additive manufacturing process. The support structure includes support walls arranged to form flow passages with a predetermined cross-sectional area. The method also includes placing the metallic component with the support structure into a chamber and sealing the chamber. The method further includes introducing a fuel mixture into the chamber after sealing the chamber. The method still further includes igniting the fuel mixture in the chamber to remove one or more of the support walls of the support structure from the metallic component.

Abstract: A swirler inlet valve plate for a fuel injector of a gas turbine engine includes a blocker ring and a pivot sleeve mechanically connected to the blocker ring. The blocker ring is formed from at least a portion of a toroid shape. The blocker ring includes a blocking surface perpendicular to an axis of the blocker ring formed from at least a portion of an annulus. The blocker ring also includes a flow surface, an inner circumferential surface of the toroidal shape. The pivot sleeve includes a sleeve portion extending adjacent the blocker ring. The sleeve portion includes a rotation transmission mechanism.

Abstract: A gas turbine engine fuel injector stem includes a single piece of material with a flange, a center body, a gas gallery, and a fluid passage. The flange includes a cylindrical shape, a plurality of mounting holes and a handle hole. The center body extends from a flange cap in the flange axial direction. The gas gallery is adjacent the center body and distal to the flange. The gas gallery includes a ring shape oriented transverse to the flange and includes a gallery opening. The fluid passage extends through the flange, center body, and gas gallery and is in flow communication with the gallery opening.

Abstract: A method for manufacturing a stem for a fuel injector of gas turbine engine includes forging a material into a unitary workpiece, which includes forging a top disk having a cylindrical shape, forging a body extending from a base of the top disk, and forging a lower disk connected to the body, distal to the top disk, the lower disk having a cylindrical shape oriented transverse to the top disk. The method further including machining the lower disk to form a gas gallery having a ring shape, and to define a gallery opening through the gas gallery, and machining a first fluid passage through the top disk, the body, and a portion of the gas gallery to the gallery opening, wherein the first fluid passage is in fluid communication with the gallery opening.

Abstract: A swirler inlet valve plate for a fuel injector of a gas turbine engine includes a blocker ring and a pivot sleeve mechanically connected to the blocker ring. The blocker ring is formed from at least a portion of a toroid shape. The blocker ring includes a blocking surface perpendicular to an axis of the blocker ring formed from at least a portion of an annulus. The blocker ring also includes a flow surface, an inner circumferential surface of the toroidal shape. The pivot sleeve includes a sleeve portion extending adjacent the blocker ring. The sleeve portion includes a rotation transmission mechanism.

Abstract: A gas turbine engine fuel injector stem includes a single piece of material with a flange, a center body, a gas gallery, and a fluid passage. The flange includes a cylindrical shape, a plurality of mounting holes and a handle hole. The center body extends from a flange cap in the flange axial direction. The gas gallery is adjacent the center body and distal to the flange. The. gas gallery includes a ring shape oriented transverse to the flange and includes a gallery opening. The fluid passage extends through the flange, center body, and gas gallery and is in flow communication with the gallery opening.

Abstract: A fuel nozzle for a turbine engine has a central body member with a pilot, a surrounding barrel housing, a mixing duct and an air inlet duct. The fuel nozzle additionally has a main fuel injection device located between the air inlet duct and the mixing duct. The main fuel injection device is configured to introduce a flow of fuel into the barrel member to create a fuel/air mixture which is then premixed with a swirler. The fuel/air mixture then further mixes in the mixing duct and exits the nozzle into a combustor for combustion. The geometry of the fuel nozzle ensures that pressure waves from the combustor do not create a time varying fuel to air equivalence ratio in the flow through the nozzle that achieves a resonance with the pressure waves.

Abstract: A fuel nozzle for a turbine engine has a central body member with a pilot, a surrounding barrel housing, a mixing duct and an air inlet duct. The fuel nozzle additionally has a main fuel injection device located between the air inlet duct and the mixing duct. The main fuel injection device is configured to introduce a flow of fuel into the barrel member to create a fuel/air mixture which is then premixed with a swirler. The fuel/air mixture then further mixes in the mixing duct and exits the nozzle into a combustor for combustion. The geometry of the fuel nozzle ensures that pressure waves from the combustor do not create a time varying fuel to air equivalence ratio in the flow through the nozzle that achieves a resonance with the pressure waves.

Abstract: A fuel nozzle for a turbine engine is disclosed. The fuel nozzle has a common axis, a body portion disposed about the common axis, a barrel portion located radially outward from the body portion. The fuel nozzle also has at least one swirler vane disposed between the body portion and the barrel portion and a liquid fuel jet disposed within the at least one swirler vane. The at least one swirler vane is configured to radially redirect an axial flow of air. The liquid fuel jet is configured to inject liquid fuel in a radial direction relative to the common axis.