Rolls-Royce Corporation

Christopher Alan Powell

David Stephen Williams

Nicholas Barrington Orchard

Ian Richard Gower

Hugo M P Lobato

Hugo Manuel Pinto Lobato

A method and system for accepting or rejecting a curved surface of a body under evaluation involves conducting a comparison between the curvature of a surface profile for the surface under evaluation and higher and lower curvature tolerance boundaries. The higher and lower curvature tolerance boundaries are determined from a desired surface profile. The curvature at a plurality of locations on the curve profile under evaluation may be defined with reference to a geometric variable for said curved surface and may be plotted on a graph. The higher and lower curvature tolerance boundaries may also be plotted on the graph so as to determine whether the plot of curvature for the surface under evaluation falls within the bounds of the higher and lower tolerance boundaries.

Surface profile evaluation

An integrally bladed rotor is constructed from a plurality of layers of organic matrix composite material wound together in a spiral fashion to form the disc portion of the rotor, and at each rotor blade position at least the outermost one of the layers is turned substantially radially outwards from the periphery of the rotor disc to form a blade. Each blade is finished with further pieces of organic matrix composite material bonded into position on the. An encircling blade tip shroud may be formed by further layers of material wound around the tips of the blades in conjunction with closed loop inserts in the spaces between blades.

Organic matrix composite integrally bladed rotor

A damped airfoil structure comprises an airfoil having a first wall and a second opposing wall, and vibration damping means for damping relative movement of the first and second wall. The damping means comprises at least two cooperating damping elements, a first damping element mounted to the first wall of the structure and a second damping element mounted to the second wall of the structure.

Damped aerofoil structure

A component such as a blade for use in a gas turbine engine comprises a bodyformed from outer panelsdefining an internal cavity. A damping elementis provided in the cavityand is secured at one end between the panelsat one end of the body, for example adjacent the root of the blade. Damping material fills the cavityand so extends between the damping elementand the panels. Vibration induced in the blade causes relative movement between the bodyof the blade and the damping element, causing energy loss in the damping material which damps the vibration. The componentsmay be secured by a diffusion bonding process.

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Cardiff, United Kingdom

Christopher Alan Powell