Abstract: Turbomachines and methods of operating turbomachines are provided. The turbomachine may include a compressor, a turbine, and a plurality of combustors downstream from the compressor and upstream from the turbine. The turbomachine may also include a plurality of igniters. Methods of operating a turbomachine may include rotating a shaft of the turbomachine at a first speed and rotating the shaft of the turbomachine at a second speed different from the first speed after rotating the shaft of the turbomachine at the first speed. The methods may also include firing at least one igniter of the plurality of igniters repeatedly throughout the period of time at a regular interval and/or when the rotational speed reaches at least one predetermined speed threshold during the period of time.

Abstract: A fuel injector is provided for the radial introduction of a fuel/air mixture to a combustor. The fuel injector includes a frame having interior sides defining an opening for passage of a first fluid; at least one fuel injection body; and a conduit fitting. The at least one fuel injection body is coupled to the frame and positioned within the opening, thereby defining flow paths for the first fluid. The at least one fuel injection body defines a fuel plenum, and a set of fuel injection holes are defined through an outer surface of the at least one fuel injection body. The conduit fitting is coupled to the frame and conveys fuel from a fuel supply line to the fuel plenum. Fuel and the first fluid mix in the flow paths and are delivered through the outlet to the combustor.

Abstract: A fuel injector is provided for the radial introduction of a fuel/air mixture to a combustor. The fuel injector includes a frame having interior sides defining an opening for passage of a first fluid; at least one fuel injection body; and a conduit fitting. The at least one fuel injection body is coupled to the frame and positioned within the opening, thereby defining flow paths for the first fluid. The at least one fuel injection body defines a fuel plenum, and a set of fuel injection holes are defined through an outer surface of the at least one fuel injection body. The conduit fitting is coupled to the frame and conveys fuel from a fuel supply line to the fuel plenum. Fuel and the first fluid mix in the flow paths and are delivered through the outlet to the combustor.

Abstract: An aft frame for a duct of a combustor includes a rail or radial projection that extends circumferentially around the aft frame and that defines an outer surface of the aft frame. A preformed cover plate having an inner surface is attached to the outer surface of the aft frame. A plurality of micro-cooling channels is formed within at least one of the inner surface of the preformed cover plate and the outer surface of the aft frame. The preformed cover plate extends across the plurality of micro-cooling channels.

Abstract: A sealing arrangement for sealing between a stage-one nozzle and an aft frame includes a seal comprising a flexible sealing element. The flexible sealing element includes an intermediate portion, a first outer portion on one side of the intermediate portion, and a second outer portion on the other side of the intermediate portion. The intermediate portion is mechanically loaded against the first stage nozzle and the aft frame, and the first outer portion and the second outer portion are pressure-loaded against the aft frame and the stage-one nozzle.

Abstract: A fuel injector for a gas turbine combustor includes a fuel conduit fitting and a nozzle having an inlet portion defining a mixing chamber therein. The inlet portion includes a plurality of circumferentially-spaced vanes that define a plurality of inlet flow paths within the mixing chamber. Each vane has at least one port defined therein that is in flow communication with the fuel conduit fitting such that fuel from the fuel conduit fitting is dischargeable into at least one of the inlet flow paths via the at least one port. The resulting fuel/air mixture is delivered into a secondary combustion zone of the gas turbine combustor. A gas turbine including the fuel injector and a method of fabricating the fuel nozzle are also provided.

Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.

Abstract: A combustion liner assembly includes a combustion liner having an upstream end portion and a downstream end portion and a resonator disposed proximate to the upstream end portion of the combustion liner. The resonator includes a plurality of circumferentially spaced inlet apertures disposed along a radially outer surface of the resonator, an air chamber defined within the resonator and a plurality of outlet apertures disposed along a radially inner surface of the resonator. The plurality of inlet apertures provide for fluid flow into the air chamber and the plurality of outlet apertures provide for fluid flow out of the air chamber and into a radial flow passage defined within the combustor.

Abstract: A fuel nozzle assembly includes a forward plate and an aft plate which is axially spaced from the forward plate. The aft plate includes a first side surface and a second side surface. A cooling air plenum is defined within the bundled tube fuel nozzle assembly and is at least partially defined by the aft plate. A plurality of tubes extends through the forward plate, the cooling air plenum and the aft plate. A micro-cooling channel is disposed along the second side surface of the aft plate and is in fluid communication with the cooling air plenum and is in fluid communication with an exhaust aperture. A cover plate is connected to the aft plate and covers the micro-cooling channel.

Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. Each of the inner seals includes a wing extending radially inward at an oblique angle. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first wing extending radially outward at an oblique angle and a second wing extending radially outward at an oblique angle, the first wing of the side seal sealingly interfaces with the wing of the first inner seal and the second wing of the side seal sealingly interfaces with the wing of the second inner seal.

Abstract: An assembly for controlling a gap between a liner and a stationary nozzle within a gas turbine includes an annular liner having an aft frame that is disposed at an aft end of the liner, and a mounting bracket that is coupled to the aft frame. The assembly further includes a turbine having an outer turbine shell and an inner turbine shell that at least partially defines an inlet to the turbine. A stationary nozzle is disposed between the aft frame and the inlet. The stationary nozzle includes a top platform portion having a leading edge that extends towards the aft frame and a bottom platform portion. A gap is defined between the aft end of the aft frame and the leading edge of the top platform portion. The mounting bracket is coupled to the outer turbine shell, and stationary nozzle is coupled to the inner turbine shell.

Abstract: A combustor assembly includes a combustion liner defining a first radial opening, an outer sleeve that at least partially surrounds the combustion liner. The outer sleeve defines a second radial opening. A mounting body having a jacket portion and a flange portion surrounds the first radial opening and extends radially outwardly from an outer surface of the combustion liner towards the outer sleeve. The flange portion is at least partially disposed within the second radial opening. An auxiliary component extends radially within the jacket portion and includes a flange portion. The flange portion of the auxiliary component is connected to the flange portion of the mounting body via a first fastener, and the flange portion of the auxiliary component is connected to the outer sleeve via a second fastener.

Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor discharge casing, a number of combustors configured in an annular array, and a number of aft mounting assemblies. An aft mounting assembly mounts a combustor to an inner diameter of the compressor discharge casing.

Abstract: A fuel injector for a gas turbine combustor includes a fuel conduit fitting and a nozzle having an inlet portion defining a mixing chamber therein. The inlet portion includes a plurality of circumferentially-spaced vanes that define a plurality of inlet flow paths within the mixing chamber. Each vane has at least one port defined therein that is in flow communication with the fuel conduit fitting such that fuel from the fuel conduit fitting is dischargeable into at least one of the inlet flow paths via the at least one port. The resulting fuel/air mixture is delivered into a secondary combustion zone of the gas turbine combustor. A gas turbine including the fuel injector and a method of fabricating the fuel nozzle are also provided.

Abstract: A fuel injector is provided for the radial introduction of a fuel/air mixture to a combustor. The fuel injector includes a frame having interior sides defining an opening for passage of a first fluid; at least one fuel injection body; and a conduit fitting. The at least one fuel injection body is coupled to the frame and positioned within the opening, thereby defining flow paths for the first fluid. The at least one fuel injection body defines a fuel plenum, and a set of fuel injection holes are defined through an outer surface of the at least one fuel injection body. The conduit fitting is coupled to the frame and conveys fuel from a fuel supply line to the fuel plenum. Fuel and the first fluid mix in the flow paths and are delivered through the outlet to the combustor.

Abstract: A fuel injector is provided for the radial introduction of a fuel/air mixture to a combustor. The fuel injector includes a frame having interior sides defining an opening for passage of a first fluid; at least one fuel injection body; and a conduit fitting. The at least one fuel injection body is coupled to the frame and positioned within the opening, thereby defining flow paths for the first fluid. The at least one fuel injection body defines a fuel plenum, and a set of fuel injection holes are defined through an outer surface of the at least one fuel injection body. The conduit fitting is coupled to the frame and conveys fuel from a fuel supply line to the fuel plenum. Fuel and the first fluid mix in the flow paths and are delivered through the outlet to the combustor.

Abstract: A fuel nozzle assembly includes a forward plate and an aft plate which is axially spaced from the forward plate. The aft plate includes a first side surface and a second side surface. A cooling air plenum is defined within the bundled tube fuel nozzle assembly and is at least partially defined by the aft plate. A plurality of tubes extends through the forward plate, the cooling air plenum and the aft plate. A micro-cooling channel is disposed along the second side surface of the aft plate and is in fluid communication with the cooling air plenum and is in fluid communication with an exhaust aperture. A cover plate is connected to the aft plate and covers the micro-cooling channel.

Abstract: A combustor assembly includes a combustion liner defining a first radial opening, an outer sleeve that at least partially surrounds the combustion liner. The outer sleeve defines a second radial opening. A mounting body having a jacket portion and a flange portion surrounds the first radial opening and extends radially outwardly from an outer surface of the combustion liner towards the outer sleeve. The flange portion is at least partially disposed within the second radial opening. An auxiliary component extends radially within the jacket portion and includes a flange portion. The flange portion of the auxiliary component is connected to the flange portion of the mounting body via a first fastener, and the flange portion of the auxiliary component is connected to the outer sleeve via a second fastener.

Abstract: A combustion liner assembly includes a combustion liner having an upstream end portion and a downstream end portion and a resonator disposed proximate to the upstream end portion of the combustion liner. The resonator includes a plurality of circumferentially spaced inlet apertures disposed along a radially outer surface of the resonator, an air chamber defined within the resonator and a plurality of outlet apertures disposed along a radially inner surface of the resonator. The plurality of inlet apertures provide for fluid flow into the air chamber and the plurality of outlet apertures provide for fluid flow out of the air chamber and into a radial flow passage defined within the combustor.

Abstract: An igniter assembly and a combustor including an igniter assembly is disclosed herein. The igniter assembly comprises an igniter housing. The igniter housing includes an outer surface, a first end wall and a second end wall. The igniter assembly also includes a preformed cover plate having an inner surface that is attached to the outer surface of the igniter housing. A plurality of micro-cooling channels is formed within at least one of the inner surface of the preformed cover plate and the outer surface of the igniter housing.