Abstract: Bayonet connection key includes upper and lower blocks shaped to be inserted one at a time into a key space, having laterally spaced apart upper and lower flat first and second side contact surfaces, and means for retaining blocks against each other. Bolt or screw may be disposed through an aperture in retaining plate and screwed into threaded hole in upper block pressing retaining plate against lower block. Upper block may include axially spaced apart upwardly extending forward and aft lugs, aft lug shorter than forward lug, and inwardly extending upper stop lug at aft end of upper block. Alternatively bendable tab extending axially forward from a front end of the lower block may be bent up contacting upper block for retaining blocks in key space. Upper block may include forward and aft lugs of same radial length and inwardly extending stop lug at aft end of lower block.

Abstract: Bayonet connection key includes upper and lower blocks shaped to be inserted one at a time into a key space, having laterally spaced apart upper and lower flat first and second side contact surfaces, and means for retaining blocks against each other. Bolt or screw may be disposed through an aperture in retaining plate and screwed into threaded hole in upper block pressing retaining plate against lower block. Upper block may include axially spaced apart upwardly extending forward and aft lugs, aft lug shorter than forward lug, and inwardly extending upper stop lug at aft end of upper block. Alternatively bendable tab extending axially forward from a front end of the lower block may be bent up contacting upper block for retaining blocks in key space. Upper block may include forward and aft lugs of same radial length and inwardly extending stop lug at aft end of lower block.

Abstract: A process of fabricating a rotating component and a rotating component formed thereby. The rotating component has a rotational axis, at least one rim member, at least one disk member, and at least one airfoil member. The rim and disk members are welded together to define a first solid-state weld joint lying in a first plane that is not parallel to the rotational axis of the rotating component. The airfoil member is welded to the rim member to define a second solid-state weld joint lying in a second plane that is not parallel to the rotational axis of the rotating component. The rim member is located in a radially outward direction from the disk member, and the airfoil member is located in a radially outward direction from the rim member.

Abstract: A connection between an annular sleeve on a gas turbine engine first rotor component includes an annular tapered conical slot extending axially inwardly into the sleeve from an annular opening and tapers axially into the sleeve from the opening. An annular rim of a second rotor component is received within the conical slot and includes a rim inner conical surface mating with and contacting a sleeve inner conical surface in part bounding the conical slot. A sleeve cylindrical outer surface in part bounds the conical slot in the sleeve and a rim outer cylindrical surface on the annular rim contacts the sleeve cylindrical outer surface. An annular lip may extend radially inwardly from the sleeve and sleeve inner conical surface at the annular opening to the conical slot. The connection may be used between a first stage disk and an interstage seal.

Abstract: A connection between an annular sleeve on a gas turbine engine first rotor component includes an annular tapered conical slot extending axially inwardly into the sleeve from an annular opening and tapers axially into the sleeve from the opening. An annular rim of a second rotor component is received within the conical slot and includes a rim inner conical surface mating with and contacting a sleeve inner conical surface in part bounding the conical slot. A sleeve cylindrical outer surface in part bounds the conical slot in the sleeve and a rim outer cylindrical surface on the annular rim contacts the sleeve cylindrical outer surface. An annular lip may extend radially inwardly from the sleeve and sleeve inner conical surface at the annular opening to the conical slot. The connection may be used between a first stage disk and an interstage seal.

Abstract: A process of fabricating a rotating component and a rotating component formed thereby. The rotating component has a rotational axis, at least one rim member, at least one disk member, and at least one airfoil member. The rim and disk members are welded together to define a first solid-state weld joint lying in a first plane that is not parallel to the rotational axis of the rotating component. The airfoil member is welded to the rim member to define a second solid-state weld joint lying in a second plane that is not parallel to the rotational axis of the rotating component. The rim member is located in a radially outward direction from the disk member, and the airfoil member is located in a radially outward direction from the rim member.

Abstract: A method for fabricating a rotor assembly for a turbine, the turbine including a central rotational axis is provided. The method includes forging a first rotor component from a first material, separately forging a second rotor component from a second material, and coupling the second rotor component to the first rotor component at a location radially inward of the first rotor component. The second rotor component is coupled to the first rotor component in at least one axial-circumferential plane that is at least one of substantially parallel and obliquely oriented with respect to the central rotational axis.

Abstract: A method and apparatus for fabricating a workpiece is provided. The method includes applying a predetermined axial force to a tool, translating the axial force into a radial force in the workpiece using the tool, and generating a hoop stress in the work piece sufficient to relieve residual stress in the workpiece.

Abstract: A method for fabricating a rotor assembly for a turbine, the turbine including a central rotational axis is provided. The method includes forging a first rotor component from a first material, separately forging a second rotor component from a second material, and coupling the second rotor component to the first rotor component at a location radially inward of the first rotor component. The second rotor component is coupled to the first rotor component in at least one axial-circumferential plane that is at least one of substantially parallel and obliquely oriented with respect to the central rotational axis.

Abstract: A method of assembling a gas turbine engine that includes providing a rotor assembly including a rotor shaft, an air duct, and a rotor disk that includes a mounting arm, wherein the mounting arm extends radially inward from the rotor disk towards the rotor shaft and coupling a rotor impeller assembly to the mounting arm, wherein the rotor impeller assembly includes a carrier and a plurality of bleed tubes that each extend outwardly from the carrier and are configured to receive bleed air.

Abstract: A method facilitates assembling a seal assembly for a gas turbine engine rotor assembly. The method comprises coupling a disk retainer to a first stage disk, and coupling an interstage seal assembly including an outer shell within the rotor assembly such that a downstream arm extending from the outer shell engages a second stage disk while an upstream arm extending from the outer shell engages the disk retainer.

Abstract: A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000° F.

Abstract: A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000° F.