Abstract: A compressor rotor includes coaxially adjoining disks having corresponding rows of rotor blades. A forward shaft is affixed to a forward disk and includes an annular seat for being mounted in a bearing to support the rotor at its forward end. A blisk coaxially surrounds the shaft axially between the seat and forward disk, and is removably fixedly joined piggyback to the shaft. In a repair method, the blisk may be removed from the compressor rotor without requiring teardown of the compressor rotor itself.

Abstract: A rotor blade for a turbine engine including a blade root section and an airfoil section which extends radially outward along a radial line RAS from the blade root section, is described. The radial line RAS extends at an angle relative to a plane extending across a top surface of the platform, rather than normal, or perpendicular, to such plane. As a result, and during a blade out event, an over turning moment is generated in a root of the airfoil section. The overturning moment facilitates bending the airfoil section reducing damage to the stator.

Abstract: An article and a method for improving an article that results in a reduction or elimination of damage due to fretting from contact of similar metals. The invention specifically reduces wear-related fretting between titanium alloy parts by lowering the stresses between mating parts. An aluminum bronze coating is applied to one of the parts. The aluminum bronze coating provides an improvement over prior art coatings in reducing coefficient of friction between the parts. Additionally, the cumulative stresses at the surface of the parts is reduced by a dual intensity peening treatment. This involves a first peening operation using large peening media that provides a compressive stress to the required depth. This first peening operation is followed by a second peening operation that provides additional compressive stresses closer to the dovetail surface.

Abstract: A dovetail of a rotor blade is mounted in a complementary slot in a rotor disk. Life of the dovetail is simulated by providing a specimen dovetail mounted in a complementary slot in a fixture. Relative stiffness of the specimen dovetail and fixture are tailored to simulate the loading profile between the blade dovetail and rotor disk. Load is cycled between the specimen dovetail and fixture for determining life of the dovetail.

Abstract: A method and fixture assembly for assisting in the matching and assembly of components of a variable stator vane assembly of a gas turbine engine. The method generally entails a stator vane configured to be assembled to a casing with a spacer. The vane has a surface at a perimeter thereof and a seat offset from the surface. The spacer to which the vane is to be assembled has first and second surfaces offset relative to each other, the first surface being adapted to engage the seat of the vane and the second surface adapted to face the surface of the vane. The vane is installed within an opening in the casing so that a first sealing member is between the casing and the vane, the casing is between the first sealing member and a second sealing member, and the seat extends through the opening. A fixture is then mounted to the vane so that the casing and the first and second sealing members are clamped between the fixture and the vane under a load.

Abstract: A shaft assembly for movement of an array of adjustable members comprises a hollow shaft body including a shaft body wall with a wall outer surface. A plurality of spaced apart clevises, secured with the shaft body wall on the wall outer surface, each includes connection means disposed away from the wall outer surface for connection with an actuator for movement of the adjustable members.

Abstract: A seal and a washer for a variable vane assembly in a turbine engine are described. The seal includes a first portion and a second portion that are substantially perpendicular. The seal is positioned between a variable vane and a casing. The washer is substantially flat and is located between the casing and a spacer.

Abstract: A bushing assembly as a means to enable guided movement of a shaft in an opening of a housing comprises a stationary bushing support carried by a housing internal wall. The bushing support has a support internal wall defining a bushing support opening through the bushing support to receive a movable shaft. Carried by the shaft is a removable wear sleeve having a wear sleeve outer wall in juxtaposition with and spaced apart from the support internal wall to permit relative axial movement of the wear sleeve with the shaft within the bushing support opening. Disposed between and for contact with the support internal wall and with the wear sleeve outer wall is an anti-friction layer.

Abstract: A rotor blade includes an airfoil, an integral platform, and a dovetail integrally joined to the platform. The dovetail includes a neck extending between a pair of dovetail lobes configured to engage a complementary slot in a rotor disk. The dovetail includes an undercut extending between an outer face of the dovetail lobes and the neck for introducing a stress concentration thereat. The stress concentration relieves stress at the outer face at the expense of the neck for increasing the high cycle fatigue life of the blade.

Abstract: The present invention relieves the stress at a fillet of a blade shank using at least one axially extending pocket on the shank near an axially extending fillet of a shank to root interface or a shank to platform interface on a pressure or suction side of the blade and the pocket is axially shorter than the fillet. The stress relief pocket has a radially extending pocket width that is substantially wider than a fillet width between generally axially extending edges of the fillet wherein the pocket width may be several times wider than the fillet width. The wider pocket shields the fillet thereby reducing the stress concentration at the fillet.

Abstract: A rotor disk includes a rim with axially spaced apart forward and aft ends, with the aft end having a larger diameter than the forward end. The rim includes a plurality of straight dovetail slots defining dovetail posts therebetween. Each dovetail post includes a pair of lobes, a neck, and first and second pressure faces facing radially inwardly from the lobes. The first and second pressure faces vary in radial height therebetween from a first magnitude at the rim aft end to a second and smaller magnitude at the rim forward end to shift a portion of the bending loads from the dovetail post at the rim forward end to the dovetail post at the larger rim aft end.

Abstract: A sealing device for compressor axial dovetail rotor blades for a gas turbine engine comprising a sealing member having a finger portion extending from a main body portion which engages a disk hook located on each disk post and forms a first point of contact about which the sealing member rotates. The sealing member further comprises an extended skirt portion which engages the blade platform of the rotor blades forming a second point of contact. The main body has a center of gravity positioned such that during operation of the engine the main body pivots due to centrifugal force about the disk hook such that the skirt portion engages the blade platform. A split ring is located between the disk posts and a tail portion extending from the lower portion of the sealing member and engages the disk post and tail portion during operation of the engine thereby forming a third point of contact.

Abstract: A high pressure compressor flowpath bleed extraction slot is provided wherein an articulated portion of the outer band of the compressor forms a slot for providing efficient conversion of core air to diffuser air while retaining substantial pressure and velocity energies. The diffuser slot can be applied to an earlier compressor stage with improved performance.