Abstract: A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials.

Abstract: A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials.

Abstract: A gas turbine engine having turbine discs includes a low diameter turbine rotor clamp for securing the turbine discs together. The rotor clamp includes a clamp sleeve, a clamp cylinder adapted to be threadably engaged to the clamp sleeve to apply an axial force on the turbine discs being coupled together. The rotor clamp includes an anti-score ring positioned between the bore of a turbine disc and the clamp cylinder and a lock tube used to prevent unwanted rotation of the clamp cylinder with respect to the clamp sleeve.

Abstract: A gas turbine engine is provided. The engine has an axis and a plurality of coaxial turbine discs, including a first disc and a second disc. A face of the first disc is disposed opposite to a face of the second disc. The engine also has a cover plate coaxial with the axis covering the second disc. The second disc includes an arrangement of turbine blade inserts positioned around its periphery. This arrangement is concentric with the plurality of turbine discs. Turbine blade inserts are retained on the second disc at least in part by the cover plate. The engine further comprises a coaxial tie bolt extending through the plurality of coaxial turbine discs, a spanner nut on the end of the tie bold, an arm coaxial with the axis extending from the face of the second disc having a distal end an axial stop extending from the face of the first disc. The distal end is in contact with the axial stop. The axial stop retains the axial movement of the second disc.

Abstract: A gas turbine engine is provided. The engine has an axis and a plurality of coaxial turbine discs, including a first disc and a second disc. A face of the first disc is disposed opposite to a face of the second disc. The engine also has a cover plate coaxial with the axis covering the second disc. The second disc includes an arrangement of turbine blade inserts positioned around its periphery. This arrangement is concentric with the plurality of turbine discs. Turbine blade inserts are retained on the second disc at least in part by the cover plate. The engine further comprises a coaxial tie bolt extending through the plurality of coaxial turbine discs, a spanner nut on the end of the tie bold, an arm coaxial with the axis extending from the face of the second disc having a distal end an axial stop extending from the face of the first disc. The distal end is in contact with the axial stop. The axial stop retains the axial movement of the second disc.

Abstract: A gas turbine engine having turbine discs includes a low diameter turbine rotor clamp for securing the turbine discs together. The rotor clamp includes a clamp sleeve, a clamp cylinder adapted to be threadably engaged to the clamp sleeve to apply an axial force on the turbine discs being coupled together. The rotor clamp includes an anti-score ring positioned between the bore of a turbine disc and the clamp cylinder and a lock tube used to prevent unwanted rotation of the clamp cylinder with respect to the clamp sleeve.

Abstract: A turbomachinery blade for a gas turbine engine is provided and includes an airfoil extending between a leading edge and a trailing edge. In one embodiment the turbomachinery blade is a compressor blade. The blade can include a platform attached to the airfoil on one side, the other side being attached to a stalk having a lower attachment portion useful for being received in a compressor disk. The blade includes an undercut beneath a portion of the airfoil, preferably beneath the leading edge and/or trailing edge of the airfoil. In one form the undercut is located in a corner of the platform and extends partially along two sides of the platform.

Abstract: A turbomachinery blade for a gas turbine engine is provided and includes an airfoil extending between a leading edge and a trailing edge. In one embodiment the turbomachinery blade is a compressor blade. The blade can include a platform attached to the airfoil on one side, the other side being attached to a stalk having a lower attachment portion useful for being received in a compressor disk. The blade includes an undercut beneath a portion of the airfoil, preferably beneath the leading edge and/or trailing edge of the airfoil. In one form the undercut is located in a corner of the platform and extends partially along two sides of the platform.

Abstract: One embodiment is an apparatus comprising a first rotational gas turbine engine component including first threads; a second rotational gas turbine engine component including second threads; the first threads and the second threads being mated; and the first rotational engine component being fastened to the second rotational engine component substantially only by the first threads and the second threads being mated. Other embodiments include unique apparatuses, systems, devices, and methods relating to gas turbine engine interconnection. Further exemplary embodiments, forms, objects, features, advantages, aspects, and benefits of the present invention are included in the following description, drawings, and claims.