Abstract: The present application provides a combustor with a radial penetration. The combustor may include a combustion chamber, a liner surrounding the combustion chamber, a flow sleeve surrounding the liner, a penetration tube extending through the liner and the flow sleeve with the radial penetration positioned within the penetration tube, a flange extending from the penetration tube about the flow sleeve, and a ferrule positioned about the flange and the radial penetration so as to limit leakage about the radial penetration.

Abstract: A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and a flow distributor configured to distribute an exhaust flow circumferentially around the head end chamber. The flow distributor includes at least one exhaust gas flow path.

Abstract: A system includes a heat recovery steam generator (HRSG) having a plurality of evaporator sections. At least one evaporator section includes a forced circulation evaporator configured to generate a saturated steam, a once-through evaporator configured to generate a first superheated steam, and a first superheater configured to receive the saturated steam and the first superheated steam.

Abstract: A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and a flow distributor configured to distribute at least one of an exhaust flow, an oxidant flow, an oxidant-exhaust mixture, or any combination thereof circumferentially around the head end chamber.

Abstract: A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and a flow separator configured to separate a first exhaust flow from an oxidant flow. The flow separator is configured to direct the first exhaust flow into the head end chamber. The turbine combustor also includes a mixing region configured to mix the first exhaust flow with the oxidant flow to provide an oxidant-exhaust mixture.

Abstract: An aft frame for a transition duct of a gas turbine combustor includes a main body having an outer rail, an inner rail, a first side rail circumferentially separated from an opposing second side rail, a forward portion, an aft portion and an outer surface. An inlet port extends through the outer surface and an exhaust port extends through the forward portion. A serpentine cooling passage is defined within the main body beneath the outer surface. The serpentine cooling passage is in fluid communication with the inlet port and the exhaust port. A conduit may be connected to the exhaust port for routing a compressed working fluid away from aft frame.

Abstract: A transition piece frame assembly includes a first frame having an inner frame member and a first inner seal extending along the inner frame member of the first frame. The first inner seal includes a first end section, a second end section, and an intermediate section extending therebetween. A second frame includes an inner frame member and a second inner seal extending along the inner frame member of the second frame. The second inner seal includes a first end section, a second end section, and an intermediate section extending therebetween. A flexible bridge member extends from one of the first and second end sections of the first inner seal and seals against one of the first and second end sections of the second inner seal.

Abstract: A sealing assembly for a turbine engine includes a first stationary component. Also included is a second stationary component, wherein the first stationary component and the second stationary component define a gap therebetween. Further included is a discourager seal in contact with at least one of the first stationary component and the second stationary component, the discourager seal having a lip portion disposed within the gap to reduce a fluid flow through the gap.

Abstract: A system includes a heat recovery steam generator (HRSG) including a plurality of evaporator sections. At least one evaporator section includes a natural circulation evaporator configured to generate a saturated steam, a once-through evaporator configured to generate a first superheated steam, a first superheater configured to receive the saturated steam from the natural circulation evaporator, and a second superheater configured to receive the first superheated steam from the once-through evaporator.

Abstract: An aft frame for a transition duct of a gas turbine combustor includes a main body having an outer rail, an inner rail, a first side rail circumferentially separated from an opposing second side rail, a forward portion, an aft portion and an outer surface. An inlet port extends through the outer surface and an exhaust port extends through the forward portion. A serpentine cooling passage is defined within the main body beneath the outer surface. The serpentine cooling passage is in fluid communication with the inlet port and the exhaust port. A conduit may be connected to the exhaust port for routing a compressed working fluid away from aft frame.

Abstract: The present application provides a combustor with a radial penetration. The combustor may include a combustion chamber, a liner surrounding the combustion chamber, a flow sleeve surrounding the liner, a penetration tube extending through the liner and the flow sleeve with the radial penetration positioned within the penetration tube, a flange extending from the penetration tube about the flow sleeve, and a ferrule positioned about the flange and the radial penetration so as to limit leakage about the radial penetration.

Abstract: A system includes a heat recovery steam generator (HRSG) having a plurality of evaporator sections. At least one evaporator section includes a forced circulation evaporator configured to generate a saturated steam, a once-through evaporator configured to generate a first superheated steam, and a first superheater configured to receive the saturated steam and the first superheated steam.

Abstract: A system includes a heat recovery steam generator (HRSG) including a plurality of evaporator sections. At least one evaporator section includes a natural circulation evaporator configured to generate a saturated steam, a once-through evaporator configured to generate a first superheated steam, a first superheater configured to receive the saturated steam from the natural circulation evaporator, and a second superheater configured to receive the first superheated steam from the once-through evaporator.

Abstract: A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, a mixing region configured to mix an exhaust flow with an oxidant flow to provide an oxidant-exhaust mixture, and a flow distributor configured to distribute the oxidant-exhaust mixture circumferentially around the head end chamber. The flow distributor includes at least one oxidant-exhaust mixture path.

Abstract: A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and a flow distributor configured to distribute an oxidant flow circumferentially around the head end chamber. The flow distributor includes at least one oxidant flow path.

Abstract: A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and a flow distributor configured to distribute at least one of an exhaust flow, an oxidant flow, an oxidant-exhaust mixture, or any combination thereof circumferentially around the head end chamber.

Abstract: A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and a flow distributor configured to distribute an exhaust flow circumferentially around the head end chamber. The flow distributor includes at least one exhaust gas flow path.

Abstract: A system includes a turbine combustor that includes a head end portion having a head end chamber, a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and a flow separator configured to separate a first exhaust flow from an oxidant flow. The flow separator is configured to direct the first exhaust flow into the head end chamber. The turbine combustor also includes a mixing region configured to mix the first exhaust flow with the oxidant flow to provide an oxidant-exhaust mixture.

Abstract: A cross fire retention system for a gas turbine engine includes a retention system housing operably coupled to a radially outer surface of a flow sleeve surrounding a combustion chamber, wherein the retention system housing includes a central aperture relatively aligned with a flow sleeve channel and is configured to receive a cross fire tube. Also included is a locking element extending through a side aperture of the retention system housing and having a first end configured to fittingly engage a first portion of an outer surface of the cross fire tube. Further included is a resilient member disposed within the retention system housing and configured to engage a second portion of the outer surface of the cross fire tube.