Rolls-royce Corporation

James Alex Finlayson

Julian Mark Reed

Lorenzo Mencattelli

Victor P A Medeau

MohammadErfan Kazemi

Emile S Greenhalgh

Soraia Pimenta

Silvestre T Pinho

Ian C D Care

Dale Edward Evans

Christopher Williams

Paul Robinson

A kinetic energy absorptive composite article comprising a plurality of plies, and a method of manufacturing the kinetic energy absorptive composite article. Each ply comprises a plurality of substantially parallel fibers encapsulated within a resin. A plurality of localised weaknesses are comprised within the fibers of the kinetic energy absorptive composite article, the locations of the plurality of localised weaknesses forming a pre-defined pattern. The pre-defined pattern comprises a first sub-pattern and a second sub-pattern superposed upon the first sub-pattern. The first sub-pattern is configured so that a crack formed by an impact event propagates substantially along a predetermined fracture path to separate the kinetic energy absorptive composite article into at least a first portion and a second portion and the second sub-pattern is configured to set a threshold below which the crack does not propagate.

Kinetic energy absorptive composite article

A containment structure for a propulsion device, comprising a plurality of laminates arranged in a stack for absorbing projectile impact from the propulsion device, each laminate comprising a multi-ply composite of fibre reinforcement material and matrix material. The plurality of laminates comprises a plurality of primary laminates and a plurality of secondary laminates provided in an alternating arrangement along a stacking direction S of the containment structure. The primary laminates comprise a first fibre reinforcement material and the secondary laminates comprises a second fibre reinforcement material. The first fibre reinforcement material has a higher elongation to failure than the second fibre reinforcement material.

Containment structure

A fan blade containment system is arranged to surround a fan including a plurality of fan blades in a gas turbine engine for an aircraft. The fan blade containment system includes a composite fan case arranged to surround the fan; and a metallic insert mounted on the composite fan case and including a metallic hook arranged to prevent forward debris release should all or part of a fan blade become detached from the fan.

Fan blade containment system for gas turbine engine

A fan blade containment system is arranged to surround a fan including a plurality of fan blades in a gas turbine engine for an aircraft. The fan blade containment system includes a fan case arranged to surround the fan; a debris retainer, such as a front hook, mounted on the fan case and arranged to prevent forward debris release should all or part of a fan blade become detached from the fan; and a front panel mounted on the fan case adjacent to and rearward of the front hook, and arranged to move or break when struck by a detached fan blade or fan blade part so as to allow the detached fan blade or fan blade part to engage the front hook.

The present invention provides a projectile for use in a simulated fan-blade-off ballistic test. The projectile has an ellipsoid body having a blind axial bore extending from a first axial end. The blind axial bore is for housing a weight adjustment body which can be used to modify the weight and/or centre of gravity of the projectile. A sealing plug may seal the weight adjustment body within the axial bore and an insert may be provided to fix the position of the weight adjustment body and/or to control the sliding of the weight adjustment body within the axial bore.

Projectile

The present invention provides a gas turbine engine comprising a tubular containment casing surrounding a rotary fan blade assembly. The radially outer perimeter (and optionally the radially inner perimeter) of the radial cross-sectional profile of the containment casing is non-circular e.g. polygonal, corrugated, fluted or wavy.

Containment casing

A containment case for a gas turbine including: a cylindrical outer casing extending about an axis and having a radially outer and a radially inner surface; a coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing; and an array of ribs extending radially from the inner skin towards the axis. The case for can have the coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing by a galvanic isolation layer.

Growing community of inventors

Ashby-de-la-Zouch, United Kingdom

James Alex Finlayson