Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Daniel Molnar

Matthew Jordan

Jared J Schneider

Jared Schneider

Christopher D Hall

Jonathan M Rivers

Roy David Fulayter

Ewan Fergus Thompson

Eric William Engebretsen

Matthew J Kappes

Graham Burkholder

Dennes Kyle Burney

Justin McKendry

Daniel Stratton

Michael Buckley

Matt Kappes

An airfoil includes a base, a tip, a suction side face, and a pressure side face. The pressure side face includes an outer surface, an inner surface located between the outer surface and the suction side face, and a transition surface that extends between and interconnects the outer surface and the inner surface so as to form a pocket in the airfoil.

Airfoil with shaped mass reduction pocket

According to one aspect, an airfoil assembly for a gas turbine engine comprises a first end wall, a second end wall, an airfoil and a sheath. The first end wall has surfaces defining a first recess, and the second end wall has surfaces defining a second recess. The airfoil includes a first portion disposed in the first recess, a second portion disposed in the second recess, and a leading edge disposed between the first and second portions. The sheath is in contact with the first and second portions of the airfoil covering the leading edge between the surfaces defining the first and second recesses.

Apparatus for airfoil leading edge protection

A method of replacing a fan case liner panel in an engine fan case is provided. In one illustrative form, the method may include applying heat to an engine fan case to debond an adhesive layer, removing the first fan case liner panel, and bonding a second fan case liner panel.

Fan case liner removal with external heat mat

A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor.

Rotor for a gas turbine engine

A shaft balancing assembly comprising a nose cone and a plurality of balance weights. The nose cone is mounted to a rotatable shaft of a turbine machine via a plurality of elongated fasteners such that a central axis of the nose cone is alighted with the rotatable shaft. The nose cone comprises a flange extending axially from a leading tip to a trailing edge and a plurality of apertures each adapted to receive a balancing weight and an elongated fastener. The nose cone flange is formed from a filament wound composite material and has a uniform thickness.

Nose cone and shaft balancing assembly

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Lebanon, IN, United States of America

Daniel Molnar