Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Daniel K Morrison

Matthew Peter Basiletti

Ted Joseph Freeman

Brandon R Snyder

Matthew I Jackson

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

Turbine wheel assembly with circumferential blade attachment

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.

Low diameter turbine rotor clamping arrangement

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. The cover plate extends axially between the axial stop and the second disc and radially between the arm and the periphery of the second disc.

System and method to retain a turbine cover plate between nested turbines with a tie bolt and spanner nut

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.

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Carmel, IN, United States of America

Daniel K Morrison