Abstract: A rotor assembly for a gas turbine engine, the rotor assembly comprises a plurality of cooling air deflectors mounted on the rotor assembly to redirect air to a manifold at a bottom side of a corresponding blade retention slot on the periphery of the rotor disk.

Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.

Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.

Abstract: An internally-cooled airfoil for a gas turbine engine, wherein the airfoil comprises at least one substantially chordwise-extending and internally-projecting stiffener located on an internal surface of one of the sidewalls and adjacent to the insert.

Abstract: A rotor assembly for a gas turbine engine, the rotor assembly comprises a plurality of cooling air deflectors mounted on the rotor assembly to redirect air to a manifold at a bottom side of a corresponding blade retention slot on the periphery of the rotor disk.

Abstract: A dimple for use on a heat transfer surface exposed to a flowing gas, for use for example in a gas turbine engine, the dimple having an aspherical shape.

Abstract: A stator blade assembly for a gas turbine engine has a leading edge portion with a passage communicating between a plenum and an air supply port of the outer shroud and an internal blade cooling channel communicating between passages and apertures adjacent the trailing edge of the blade. The plenum includes an impingement plate disposed a distance from the inner surface of blade platform to define an impingement cooling chamber within the plenum, and the plate includes impingement cooling apertures to direct cooling jets of air at the inner blade platform. An air flow restriction plate covers the inner end of the passage and controls the pressure and quantity of air delivered to the plenum via a compressed air metering aperture.

Abstract: A stator blade assembly for a gas turbine engine having; an outer shroud with an air supply port in communication with compressed air from a high pressure stage of a compressor of the engine; an inner shroud including a blade platform and a plenum enclosure defining a plenum bounded by an inner surface of the blade platform; and a blade spanning between the outer and inner shrouds. The blade has a leading edge portion with a passage communicating between the plenum and the air supply port of the outer shroud and an internal blade cooling channel communicating between the passage and apertures adjacent the trailing edge of the blade. The plenum includes an impingement plate disposed a distance from the inner surface of blade platform to define an impingement cooling chamber within the plenum, and the plate includes impingement cooling apertures to direct cooling jets of air at the inner blade platform.