Abstract: A secondary combustion system for a stage one turbine nozzle. The secondary combustion system may include a supply tube extending into the stage one nozzle, a number of injectors extending from the supply tube to an outer surface of the stage one nozzle, and an air gap surrounding each of the number of injectors.

Abstract: A method of operating a gas turbine engine includes providing an inlet flow conditioner (IFC). The IFC has an annular chamber defined therein by at least one wall wherein the wall includes a plurality of perforations extending therethrough. The perforations are spaced in at least two axially-spaced rows that extend circumferentially about the wall. The method also includes channeling a fluid into the IFC and discharging the fluid from the IFC with a substantially uniform flow profile.

Abstract: A combustor includes a center nozzle surrounded by a plurality of outer nozzles, the center nozzle and each of the outer nozzles having a fuel passage and an air passage, with a swirler surrounding the fuel passage and having a plurality of vanes projecting radially within the air passage, each vane having a trailing edge arranged at a swirl angle relative to a longitudinal axis of the nozzle, wherein the swirl angle for the swirler in the center nozzle is different than the swirl angle for the swirlers in the plurality of outer nozzles.

Abstract: A can combustor for an industrial turbine includes a transition piece transitioning directly from a combustor head-end to a turbine inlet using a single piece transition piece. In an exemplary embodiment, the transition piece is jointless.

Abstract: A gas-air premixing burner for gas turbines includes an air swirler and an annular burner tube surrounding a bluff centerbody. The bluff body serves to stabilize the flame by defining a recirculating vortex. Cooling air is directed to impinge against the bluff face of the centerbody and the spent impingement cooling air flows in a reverse direction towards the air swirler within the centerbody and is discharged through holes at the outer diameter of the centerbody, where it mixes with the fuel/air mixture prior to reaching the flame zone.

Abstract: A hybrid structure that combines characteristics of the DACRS and Swozzle burners to provide the high mixing ability of an axial flowing counter rotating vane swirler with good dynamic flame stability characteristics of a bluff center body.

Abstract: A valve system for an engine is provided. The valve system includes a cylinder head that defines an intake passageway, an exhaust passageway, and an auxiliary passageway. The auxiliary passageway includes a first connection with the intake passageway and a second connection with the exhaust passageway. A control valve is disposed in the auxiliary passageway. The control valve is moveable between a first position where the control valve blocks the first connection between the auxiliary passageway and the intake passageway and a second position where control valve blocks the second connection between the auxiliary passageway and the exhaust passageway.

Abstract: A valve system for an engine is provided. The valve system includes a cylinder head that defines an intake passageway, an exhaust passageway, and an auxiliary passageway. The auxiliary passageway includes a first connection with the intake passageway and a second connection with the exhaust passageway. A control valve is disposed in the auxiliary passageway. The control valve is moveable between a first position where the control valve blocks the first connection between the auxiliary passageway and the intake passageway and a second position where control valve blocks the second connection between the auxiliary passageway and the exhaust passageway.