Abstract: Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a fuel injector having a first annular wall that about an axial centerline and extends from a primary inlet disposed at a first end to a primary outlet disposed at a second end. A second annular wall surrounds the first annular wall. A fuel plenum is defined between the first annular wall and the second annular wall. A fuel duct extends from a fuel outlet defined in the second annular wall to a fuel inlet. wherein the fuel duct is in fluid communication with the fuel plenum. The fuel duct includes a polygonal segment and a cylindrical inlet segment. The polygonal segment extends from the fuel outlet to the cylindrical inlet segment.

Abstract: An object includes an annular outer body having an end and an interior surface; a first annular inner body disposed inside the annular outer body, the first annular inner body having an exterior surface defining a first annular passage with the interior surface of the annular outer body. The first annular passage includes a first plurality of outlets formed on the end of the annular outer body, the first annular passage receiving a coolant and discharging the coolant adjacent the end of the annular outer body. The object also includes a second annular inner body disposed inside the first annular inner body, the second annular inner body defining a second annular passage with the first annular inner body. Further, the object includes a third annular inner body disposed inside the second annular inner body, with the third annular inner body defining a third annular passage with the second annular inner body; and a fourth annular passage opposite and surrounded by the third annular passage.

Abstract: Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a fuel injector having a first annular wall that about an axial centerline and extends from a primary inlet disposed at a first end to a primary outlet disposed at a second end. A second annular wall surrounds the first annular wall. A fuel plenum is defined between the first annular wall and the second annular wall. A fuel duct extends from a fuel outlet defined in the second annular wall to a fuel inlet. wherein the fuel duct is in fluid communication with the fuel plenum. The fuel duct includes a polygonal segment and a cylindrical inlet segment. The polygonal segment extends from the fuel outlet to the cylindrical inlet segment.

Abstract: An object includes an annular outer body having an end and an interior surface; a first annular inner body disposed inside the annular outer body, the first annular inner body having an exterior surface defining a first annular passage with the interior surface of the annular outer body. The first annular passage includes a first plurality of outlets formed on the end of the annular outer body, the first annular passage receiving a coolant and discharging the coolant adjacent the end of the annular outer body. The object also includes a second annular inner body disposed inside the first annular inner body, the second annular inner body defining a second annular passage with the first annular inner body. Further, the object includes a third annular inner body disposed inside the second annular inner body, with the third annular inner body defining a third annular passage with the second annular inner body; and a fourth annular passage opposite and surrounded by the third annular passage.

Abstract: An object includes a fluid chamber extending between a first surface and a vertically opposed second surface, the first surface including a fluid passage opening therethrough. A self-breaking support, initially configured to support the first surface, once broken creates a broken support disposed between the first surface and the vertically opposed second surface. The support includes: a base having a first end coupled to the first surface and a second opposing end. The first end of the base is wider than the second end, and a fluid passage extends through the first base for fluidly coupling the fluid chamber and the fluid passage opening in the first surface. A self-breaking link is disposed between the second opposing end of the first base and the second surface.

Abstract: An endcover assembly for a combustor includes an endcover and a fuel nozzle rigidly connected to the endcover. The fuel nozzle includes a plurality of tubes that extends axially through a first plate, a fuel plenum and a second plate where each tube includes an inlet defined upstream of the first plate and an outlet disposed downstream from the second plate. The endcover assembly further includes an inlet flow conditioner having a forward end connected to the endcover and an aft end axially spaced from the forward end. The inlet flow conditioner circumferentially surrounds at least a portion of the fuel nozzle. A support plate is joined to the aft end of the inlet flow conditioner. Each tube of the fuel nozzle extends through a corresponding tube hole defined by the support plate. The fuel nozzle is connected to the support plate.

Abstract: An endcover assembly for a combustor includes an endcover and a fuel nozzle rigidly connected to the endcover. The fuel nozzle includes a plurality of tubes that extends axially through a first plate, a fuel plenum and a second plate where each tube includes an inlet defined upstream of the first plate and an outlet disposed downstream from the second plate. The endcover assembly further includes an inlet flow conditioner having a forward end connected to the endcover and an aft end axially spaced from the forward end. The inlet flow conditioner circumferentially surrounds at least a portion of the fuel nozzle. A support plate is joined to the aft end of the inlet flow conditioner. Each tube of the fuel nozzle extends through a corresponding tube hole defined by the support plate. The fuel nozzle is connected to the support plate.

Abstract: An object includes an annular outer body having an interior surface; and an annular inner body disposed inside the annular outer body, the annular inner body having an exterior surface defining an annular passage with the interior surface of the annular outer body. A plurality of suspension elements connects the interior surface of the annular outer body to the exterior surface of the annular inner body, each suspension element configured to substantially rigidly locate a position of the annular outer body relative to the annular inner body in axial and lateral directions while permitting controlled deflection in a radial direction. Each suspension element has an at least partially tear-shaped cross-section.

Abstract: An object includes a fluid chamber extending between a first surface and a vertically opposed second surface, the first surface including a fluid passage opening therethrough. A self-breaking support, initially configured to support the first surface, once broken creates a broken support disposed between the first surface and the vertically opposed second surface. The support includes: a base having a first end coupled to the first surface and a second opposing end. The first end of the base is wider than the second end, and a fluid passage extends through the first base for fluidly coupling the fluid chamber and the fluid passage opening in the first surface. A self-breaking link is disposed between the second opposing end of the first base and the second surface.

Abstract: A system including a first multi-tube fuel nozzle including a plurality of first tubes extending in an axial direction, wherein each first tube of the plurality of first tubes includes a first air inlet, a first fuel inlet, and a first fuel-air mixture outlet, a second multi-tube fuel nozzle including a plurality of second tubes extending in an axial direction, wherein each second tube of the plurality of second tubes includes a second air inlet, a second fuel inlet, and a second fuel-air mixture outlet, and an aft plate including a plurality of first tube apertures and a plurality of second tube apertures, wherein the plurality of first tubes extend to the plurality of first tube apertures, and the plurality of second tubes extend to the plurality of second tube apertures.

Abstract: A micro-mixer nozzle for use in a combustor of a combustion turbine engine, the micro-mixer nozzle including: a fuel plenum defined by a shroud wall connecting a periphery of a forward tube sheet to a periphery of an aft tubesheet; a plurality of mixing tubes extending across the fuel plenum for mixing a supply of compressed air and fuel, each of the mixing tubes forming a passageway between an inlet formed through the forward tubesheet and an outlet formed through the aft tubesheet; and a wall mixing tube formed in the shroud wall.

Abstract: The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a conical liner support supporting the liner.

Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and providing the flow of fuel therethrough. The support struts may include an aerodynamic contoured shape so as to distribute evenly a flow of air to the micro-mixer fuel nozzles.

Abstract: A fuel injection head for use in a fuel injection nozzle comprises a monolithic body portion comprising an upstream face, an opposite downstream face, and a peripheral wall extending therebetween. A plurality of pre-mix tubes are integrally formed with and extend axially through the body portion. Each of the pre-mix tubes comprises an inlet adjacent the upstream face, an outlet adjacent the downstream face, and a channel extending between the inlet and the outlet. Each pre-mix tube also includes at least one fuel injector that at least partially extends outward from an exterior surface of the pre-mix tube, wherein the fuel injector is integrally formed with the pre-mix tube and is configured to facilitate fuel flow between the body portion and the channel.

Abstract: The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles.

Abstract: The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner.

Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and for providing the flow of fuel therethrough. The fuel injection system also may include a number of aerodynamic fuel flanges connecting the micro-mixer fuel nozzles and the support struts.

Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the micro-mixer fuel nozzles to deliver a flow of fuel thereto, and a linear actuator to maneuver the micro-mixer fuel nozzles and the fuel manifold system.

Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system.

Abstract: The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a center hub for providing the flow of fuel therethrough. The center hub may include a first supply circuit for a first micro-mixer fuel nozzle and a second supply circuit for a second micro-mixer fuel nozzle.