Abstract: The disclosed overboard extractor provides overboard extraction of compressor fluid at multiple extraction points. The overboard extractor includes multiple extraction manifolds and a delivery manifold for extracting the compressor fluid from the multiple extraction points. The overboard extractor also includes extraction valves and a delivery valve to control the extraction flow through each extraction manifold. The overboard extractor can operate in a delivery mode, a closed loop mode, or a mixed mode.

Abstract: A fuel nozzle for turbine engine includes a cooling shroud located at the downstream end of the fuel nozzle to help cool the downstream end of the fuel nozzle. The cooling shroud surrounds the exterior circumference of the downstream end of the fuel nozzle. A flow of air is admitted into the cooling shroud and the flow of air travels in the downstream direction through a first passageway which covers the exterior of the fuel nozzle. The cooling air flow then turns 180° and travels in the upstream direction through a second passageway which is located concentrically outside the first passageway. The airflow then leaves the upstream end of the cooling shroud and enters the interior of the fuel nozzle.

Abstract: A venturi device for a turbine combustor includes a substantially annular outer liner; a substantially annular inner liner; a venturi channel located between the substantially annular outer and inner liners; the substantially annular outer and inner liners being substantially V-shaped in axial cross-section, thereby defining a throat region; the substantially annular outer liner formed with an array of impingement holes and the substantially annular inner liner formed with a plurality of vortex generators facing the substantially annular outer liner.

Abstract: An air bypass band assembly includes a transition piece of a gas turbine, the transition piece having at least one opening therein to allow a flow of air to pass through the at least one opening. The air bypass band assembly also includes a band that is movable between at least two positions, a first one of the at least two positions being a closed position where the at least one opening is closed to prevent the flow of air from flowing through the at least one opening, a second one of the at least two positions being an open where the at least one opening is opened to allow the flow of air to flow through the at least one opening. The air bypass band assembly further includes a mechanism that moves the band between the at least two positions.

Abstract: A bucket for use on a steam turbine rotor wheel, the bucket comprising a shank portion and an airfoil portion, the airfoil portion having a radially outer tip with a tip cover adapted to be engaged, in use, by a similar tip cover on an adjacent bucket, wherein a radial step is formed in the tip cover and the airfoil portion along a leading edge of the airfoil portion.