Abstract: Control systems and methods for controlling injection of water into a turbine engine are described. In an exemplary embodiment, the water injection system includes a plurality of nozzles for injecting water into a gas flow through the engine, a water source, a water manifold, a water supply line extending from the water source to the water manifold, a water metering valve for controlling flow through the water supply line, an air manifold, an air flow pipe coupled to the high pressure compressor and to the air manifold, a plurality of air feeder tubes extending from the air manifold to the nozzles, and a plurality of water feeder tubes extending from the water manifold to the nozzles.

Abstract: Methods and apparatus for injecting water into a turbine engine are described. In one embodiment, water injection apparatus is provided for injecting water into the gas flow through the engine, e.g., at a high pressure and/or low pressure compressor inlet. The water injection apparatus includes a plurality of nozzles arranged so that water injected into the gas flow by the nozzles results in substantially uniformly reducing the temperature of the gas flow at the high pressure compressor outlet.

Abstract: Methods and apparatus for injecting water into a turbine engine are described. In one embodiment, water injection apparatus is provided for injecting water into the gas flow through the engine, e.g., at a high pressure and/or low pressure compressor inlet. The water injection apparatus includes a plurality of nozzles arranged so that water injected into the gas flow by the nozzles results in substantially uniformly reducing the temperature of the gas flow at the high pressure compressor outlet.

Abstract: Precompressor and pre-booster water spray injection apparatus and methods are described. In an exemplary embodiment, a plurality of nozzles are configured so that water injected into the gas flow to the high pressure compressor provides substantially uniform radial and circumferential temperature reductions at the outlet of the high pressure compressor.

Abstract: Methods and apparatus for injecting water into a turbine engine are described. In one embodiment, water injection apparatus is provided for injecting water into the gas flow through the engine, e.g., at a high pressure and/or low pressure compressor inlet. The water injection apparatus includes a plurality of nozzles arranged so that water injected into the gas flow by the nozzles results in substantially uniformly reducing the temperature of the gas flow at the high pressure compressor outlet.

Abstract: A variable stator vane assembly which substantially eliminates leakage paths by utilizing a cantilevered finger spring seal and an o-ring is described. In one form, the stator vane assembly includes a spacer configured to form, with an upper, or outer, surface of the vane trunnion bushing, an annulus. The ring shaped cantilevered finger spring seal is positioned in the annulus and forms a seal between the spacer and trunnion bushing. The stator vane assembly also includes, in one form, an o-ring located at an interface between the stator case and the stator vane metal jacket.

Abstract: A variable stator vane assembly which substantially eliminates leakage paths by utilizing a cantilevered finger spring seal and an o-ring is described. In one form, the stator vane assembly includes a spacer configured to form, with an upper, or outer, surface of the vane trunnion bushing, an annulus. The ring shaped cantilevered finger spring seal is positioned in the annulus and forms a seal between the spacer and trunnion bushing. The stator vane assembly also includes, in one form, an o-ring located at an interface between the stator case and the stator vane metal jacket.

Abstract: An assembly for housing an inboard end of a stator vane in an axial flow compressor includes a shroud having a plurality of openings formed about the periphery of an outboard surface thereof, where the shroud includes at least one circumferential groove adjacent an inboard surface of the openings, and a bushing fitted into each of the openings, with the bushing including a slot in an outboard surface thereof for receiving the inboard end of the stator vane and at least one tang extending from a sidewall of the bushing, wherein the tang is positively retained within the shroud groove and radial displacement of the bushing is prevented.

Abstract: A variable angle stator vane assembly for an axial flow gas turbine engine compressor. The compressor casing has a bore surrounded by a boss at the position of each assembly. A housing having a central bore and a bushing assembly is located in the casing bore and is bolted to the boss. The stator vane spindle extends through the housing bore and busing assembly. The housing and bushing assembly can be removed from the casing bore, to be rotated 180.degree. or replaced, without removing the casing from the compressor or the stator vane spindle from the casing bore.