Abstract: A vibration damper for a fuel conduit of a gas turbine combustor includes a mounting portion and a damping portion. The mounting portion is secured to the fuel conduit, and the damping portion includes a stack of damping washers, a bushing on top of the stack of damping washers, a spring clip secured around the stack of damping washers and the bushing, and a shoulder bolt disposed through the bushing and the stack of damping washers and engaged to the mounting portion.

Abstract: In accordance with an embodiment of the disclosure, a system includes a combustor liner disposed about a combustion chamber of a combustor of a gas turbine system. The combustor liner includes an inner wall portion exposed to the combustion chamber, an outer wall portion disposed about the inner wall portion, and multiple channels between the inner and outer wall portions of the combustor liner. Each channel of the multiple channels is configured to direct a coolant along the combustor liner to convectively cool the combustor liner, and each channel of the multiple channels includes a cross-sectional area that progressively changes along a length of each channel of the plurality of channels.

Abstract: A vibration damper for a fuel conduit of a gas turbine combustor includes a mounting portion and a damping portion. The mounting portion is secured to the fuel conduit, and the damping portion includes a stack of damping washers, a bushing on top of the stack of damping washers, a spring clip secured around the stack of damping washers and the bushing, and a shoulder bolt disposed through the bushing and the stack of damping washers and engaged to the mounting portion.

Abstract: An aft frame assembly for a gas turbine transition piece includes a main body having an upstream facing surface and a downstream facing surface. A plurality of feed hole inlets are located on the upstream facing surface. The feed hole inlets are coupled to a plurality of cooling channels that pass through the main body towards the downstream facing surface. A plurality of plenums are located in or near the downstream facing surface, and each cooling channel is connected to and terminates in one of the plenums. The cooling channels are inputs to the plenums. A plurality of microchannel cooling slots are formed in or near the downstream facing surface, and each microchannel cooling slot is connected to one of the plenums. The microchannel cooling slots are outputs of the plenums. Two or more cooling channels and two or more microchannel cooling slots are connected to one of the plenums.

Abstract: A combustor cap assembly includes a cap plate and a cover panel. The cap plate defines an outer perimeter and fuel nozzle openings disposed through the cap plate. The cap plate has a hot side, and the cover panel has a cold side, which is attached to the hot side of the cap plate. The hot side of the cap plate and/or the cold side of the cover panel define a plurality of cooling microchannels extending in a transverse direction relative to a centerline of the combustor cap assembly. A first microchannel has a first channel outlet disposed along the outer perimeter of the cap plate, and/or a second microchannel has a second channel outlet disposed within one of the plurality of fuel nozzle openings. The cover panel may be coated with a bond coat and a thermal barrier coating.

Abstract: In accordance with an embodiment of the disclosure, a system includes a combustor liner disposed about a combustion chamber of a combustor of a gas turbine system. The combustor liner includes an inner wall portion exposed to the combustion chamber, an outer wall portion disposed about the inner wall portion, and multiple channels between the inner and outer wall portions of the combustor liner. Each channel of the multiple channels is configured to direct a coolant along the combustor liner to convectively cool the combustor liner, and each channel of the multiple channels includes a cross-sectional area that progressively changes along a length of each channel of the plurality of channels.

Abstract: An aft frame assembly has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. Feed hole inlets are located on the upstream facing surface and radially outward of the outer sleeve so that the feed hole inlets are located to receive input from a high pressure plenum. The feed hole inlets are coupled to cooling channels that pass through the main body. Microchannels are formed in or near the radially inner facing surface and the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. Exit holes are connected to the plurality of microchannels, and the exit holes are located radially outward of the transition piece and radially inward of the outer sleeve. The exit holes are located to exhaust into the cooling annulus.

Abstract: An aft frame assembly for a gas turbine transition piece has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. A plurality of feed hole inlets are located on the upstream facing surface. Each of the feed hole inlets are coupled to one of a plurality of cooling channels passing through the main body towards the radially inner facing surface. A plurality of microchannels are formed near the radially inner facing surface and extend at least partially along the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. A pre-sintered preform is located on the radially inner facing surface of the main body.

Abstract: A combustor cap assembly includes a cap plate and a cover panel. The cap plate defines an outer perimeter and fuel nozzle openings disposed through the cap plate. The cap plate has a hot side, and the cover panel has a cold side, which is attached to the hot side of the cap plate. The hot side of the cap plate and/or the cold side of the cover panel define a plurality of cooling microchannels extending in a transverse direction relative to a centerline of the combustor cap assembly. A first microchannel has a first channel outlet disposed along the outer perimeter of the cap plate, and/or a second microchannel has a second channel outlet disposed within one of the plurality of fuel nozzle openings. The cover panel may be coated with a bond coat and a thermal barrier coating.

Abstract: A combustor cap module is provided with a retention system to facilitate assembly and disassembly. The combustor cap module further includes a cap face assembly having a cooling plate; a cylindrical sleeve including a connecting surface for attaching the cap face assembly to the retention assembly; and a coupling member mounted in a downstream fuel nozzle opening in the cooling plate. The retention system includes a support plate having an inner panel that defines an upstream fuel nozzle opening. The coupling member extends through the upstream fuel nozzle opening, such that its upstream end extends upstream of the support plate. A retaining ring at least partially encircles the upstream end of the coupling member and is engaged by a spring plate that is removably secured to the support plate at multiple locations. A method for assembling a combustor cap module is also provided.

Abstract: An aft frame assembly for a gas turbine transition piece has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. A plurality of feed hole inlets are located on the upstream facing surface. Each of the feed hole inlets are coupled to one of a plurality of cooling channels passing through the main body towards the radially inner facing surface. A plurality of microchannels are formed near the radially inner facing surface and extend at least partially along the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. A pre-sintered preform is located on the radially inner facing surface of the main body.

Abstract: An aft frame assembly has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. Feed hole inlets are located on the upstream facing surface and radially outward of the outer sleeve so that the feed hole inlets are located to receive input from a high pressure plenum. The feed hole inlets are coupled to cooling channels that pass through the main body. Microchannels are formed in or near the radially inner facing surface and the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. Exit holes are connected to the plurality of microchannels, and the exit holes are located radially outward of the transition piece and radially inward of the outer sleeve. The exit holes are located to exhaust into the cooling annulus.

Abstract: An aft frame assembly for a gas turbine transition piece includes a main body having an upstream facing surface and a downstream facing surface. A plurality of feed hole inlets are located on the upstream facing surface. The feed hole inlets are coupled to a plurality of cooling channels that pass through the main body towards the downstream facing surface. A plurality of plenums are located in or near the downstream facing surface, and each cooling channel is connected to and terminates in one of the plenums. The cooling channels are inputs to the plenums. A plurality of microchannel cooling slots are formed in or near the downstream facing surface, and each microchannel cooling slot is connected to one of the plenums. The microchannel cooling slots are outputs of the plenums. Two or more cooling channels and two or more microchannel cooling slots are connected to one of the plenums.

Abstract: A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.

Abstract: A method of providing fuel to a combustion chamber of a combustion can in a radial direction of the combustion can, and a micromixer cap having axially arranged fuel stages that receive fuel from a radial direction, the fuel stages supplies fuel to different radial zones of micromixer tubes arranged in a concentric configuration to provide a mixture of fuel and air for combustion.

Abstract: The present application provides a combustor for a gas turbine engine. The combustor may include a number of fuel nozzles and an effusion plate assembly positioned about the fuel nozzles. The effusion plate assembly may include a cold pate, a hot plate, and a number of swirl inducing structures extending therebetween.

Abstract: A combustor cap module is provided with a retention system to facilitate assembly and disassembly. The combustor cap module further includes a cap face assembly having a cooling plate; a cylindrical sleeve including a connecting surface for attaching the cap face assembly to the retention assembly; and a coupling member mounted in a downstream fuel nozzle opening in the cooling plate. The retention system includes a support plate having an inner panel that defines an upstream fuel nozzle opening. The coupling member extends through the upstream fuel nozzle opening, such that its upstream end extends upstream of the support plate. A retaining ring at least partially encircles the upstream end of the coupling member and is engaged by a spring plate that is removably secured to the support plate at multiple locations. A method for assembling a combustor cap module is also provided.

Abstract: A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.

Abstract: A transition piece seal assembly includes a first seal, and a second seal joined to the first seal. The second seal being spaced from the first seal to define a coolant passage.

Abstract: A combustor nozzle includes a downstream surface having an axial centerline. A plurality of passages through the downstream surface provide fluid communication through the downstream surface, and a downstream section of each passage has at least one of a frusto-conical or frusto-spherical shape. A method for modifying a combustor nozzle includes machining a downstream side of a body to remove a recast surface in a plurality of passages that provide fluid communication through the body. The method may further include machining a downstream section in each passage to form at least one of a frusto-conical or frusto-spherical surface in each passage proximate to the downstream side of the body.