Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Matthew Peter Basiletti

Richard Christopher Uskert

David John Thomas

Daniel K Morrison

Michelle Lynn Tucker

Ted Joseph Freeman

Adam Lee Chamberlain

Brandon R Snyder

Matthew I Jackson

Michelle L Tucker

A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion and a second surface coupled to the second end of the blade portion, the first and second surfaces arranged to extend divergently away from one another. The engagement portion is adapted for coupling to a wheel included in a gas turbine engine wheel.

Gas turbine engine component including a compliant layer

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

The present disclosure provides for a turbine wheel having a blade platform disposed to compliantly secure ceramic turbine blades to a rotatable disk. The platform includes opposing ends to engage a portion of an airfoil of each turbine blade and radial extensions to engage a portion of a root of each turbine blade.

Platform for ceramic matrix composite turbine blades

A bladed disk assembly includes a disk, a blade, and a retaining clip. The disk is centered on an axis. The disk has at least one groove extending along the axis. The blade is received in the groove. The retaining clip contacts the blade and limits movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit.

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Lafayette, IN, United States of America

Matthew Peter Basiletti