Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Facc Ag

Ewan Fergus Thompson

Paul J Mason

Simon Read

Kristofer John Bottome

James Andrew Lee

Richard Geoffrey Stretton

Daniel E Molnar, Jr

Kenneth Franklin Udall

Ian C D Care

Dale Edward Evans

David S Knott

Julian Mark Reed

Sivasubramaniam K Sathianathan

Eric William Engebretsen

Ian Graham Martindale

Daniel Molnar

David Geary

Mark J Hicklin

Timothy J Summers

Stephen O Osiyemi

Konstantin Horejsi

Christopher M Whitehead

Jeremy Nicholas Turner

Michael Buckley

Martin Fleischmann

Christof Obertscheider

Elliot Carty

Thomas Keusch

Ning Wang

Christopher S Brown

Daniel J Blair

Gion Barandun

Markus Henne

Eric W Engebretsen

James Lee

Jeremy N Turner

Christopher Shelton Brown

An annulus filler for mounting to a rotor disc in a gas turbine engine includes a body portion having a top wall arranged to bridge the gap between two adjacent blades extending from the rotor disc and to define an air flow surface for air passing between the blades; and a separately formed rear interface portion, fixed to the body portion adjacent to a down-flow end of the top wall. The rear interface portion forms a lip projecting below the top wall.

Annulus filler

A method of forming a protective sheath for an aerofoil component includes: providing a first sheath portion and a second sheath portion, the first sheath portion and the second sheath portion each comprising an inner surface, an outer surface and an end surface between the inner and outer surfaces and having a sacrificial flange at its distal end; positioning the first sheath portion and second sheath portion so that the inner surface of the first sheath portion abuts against the inner surface of the second sheath portion with the end surfaces of the first and second sheath portions aligned to form a mating edge; and joining the first sheath portion to the second sheath portion by welding along the mating edge, wherein the sacrificial flanges are completely consumed and a curved outer profile is formed.

Method of forming a protective sheath for an aerofoil component

A rotary device, comprises a central hub; and at least one blade extending from the hub; wherein the blade comprises a blade body and a blade cap, the blade body having a blade body tip, the blade cap being arranged to cover the blade body tip; and wherein the blade cap comprises a mesh.

Rotary device

A method is provided of bonding a first component to a second component. The method includes: locating the first component against the second component to form an interface between the components, a curable adhesive being provided at the interface; locating a pressurizable, fluid-filled bladder against the first component such that the first component is sandwiched between the second component and the bladder; locating a backing member against the bladder such that the bladder is sandwiched between the backing member and the first component; pressurizing the bladder such that a consolidating pressure is exerted by the bladder on the first component to conform the first component to the second component; and curing the adhesive while the first component is conformed to the second component by the consolidating pressure.

Bonding method

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

The present invention provides a mounting arrangement for mounting a variable stator vane within a gas turbine engine. The mounting arrangement comprises an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot. The or each insert has at least one bore for receiving a spindle portion of the variable stator vane. The at least one insert is formed of a plastics material and/or the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is greater than and radially inwards from a respective second width, the first width of the at least one insert being greater than the second width of the slot and there being a smooth transition between the respective first and second widths.

Mounting arrangement for variable stator vane

A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element. A hook projects in a generally radially inward direction from the annular casing element and is positioned axially forward of an array of fan blades when the fan containment system is fitted around said fan blades. Tabs protrude from the hook in a generally rearward direction and are spaced circumferentially along the hook. Fasteners connect the fan track liner to the tabs. The fasteners are configured so as to permit movement of the fan track liner towards the annular casing element when the fan track liner is impacted by a released fan blade.

Gas turbine engine

A test blade for use in a blade-release test in which the blade is mounted on a rotatable hub and at least a portion of the blade is released therefrom by the action of a controlled explosion. The blade has a root portion for mounting on said rotatable hub and the root portion comprises a radially inner surface having a channel extending at least partly along or proximal the camber line. The channel is for receiving at least one explosive charge and at least one detonator which may be contained within a charge carrier.

Test blade

An annulus filler, mounted to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, is disclosed. The annulus filler, formed from a polymer matrix composite material, includes an outer lid, defining an airflow surface for air drawn through the engine in an axial airflow direction, and a support structure, connectable to the rotor disc, to support the rear of the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. Under centrifugal loads, the opposing support walls resiliently deform. Each support wall has a concave rear edge. Each rear edge has a first curved section, a second curved section and a substantially straight section therebetween.

An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler is substantially entirely formed from a polymer matrix composite material. It has an outer lid which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and a support structure which is connectable to the rotor disc to support the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. In use, under centrifugal loads, the opposing support walls resiliently deform to allow outward radial movement of the lid. Each support wall is thickened in a region neighboring the attachment strap.

A component for use in a gas turbine engine comprises an indicator operable to provide a visual indication when strain over a threshold value has been experienced by the component by transitioning from a rest state to an indication state on occurrence of strain above the threshold value. Also disclosed is a method of detecting foreign object damage in a component of a gas turbine engine, comprising: identifying at least one of a component or a region of a component that is subject to increased strain during a foreign object impact; and mounting an indicator on the identified component or region of a component, the indicator providing a visual indication when increased strain has been experienced.

Strain indicator for a gas turbine engine component

An annulus filler () is provided for mounting to a rotor disc () of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc (). The annulus filler () has an outer part () which defines an airflow surface for air being drawn through the engine, and a separate, support part () which is connectable to the outer part () and to the rotor disc () to support the outer part () on the rotor disc (). The outer () and support parts () are configured to allow a procedure for mounting the annulus filler () to the rotor disc (). In a first step the support part () is connected to the rotor disc () without the outer part (), and in a subsequent second step the outer part () is connected to the support part ().

A method of manufacturing a hollow article () comprising the steps of cold pressing two members () to form at least one depression () in the members (). Arranging the two members () in abutting relationship such that the at least one depression () defines at least one chamber between the two members (). Sealing () the edges () of the two members () together to form a core structure (). Positioning the core structure () in a mold () to define a cavity () between the external surface () of the core structure () and the internal surface () of the mold (), the internal surface () of the mold () substantially defining the external shape of the hollow article (). Filling the cavity () between the core structure () and the mold () with a powder material (), sealing the open edge of the core structure () to the mold (). Removing gases from the cavity () containing the powder material (), applying heat and pressures to consolidate the power material to form the hollow article () in the cavity () and removing the mold () from the hollow article ().

Method of manufacturing a hollow article

Powder metallurgy techniques are utilised to form components and in particular titanium components in moulds. By the nature of the powder forming process, closed surfaces are created in the powder formed component, particularly when hot iso-static pressing techniques are utilised. In order to create surface texturing, and in particular entrant features, a mould lining is associated such that it reciprocates the shape of an underlying mould. The mould lining incorporates surface discontinuities such as holes, slots, spots or folds which result, once the moulded material is formed, in entrant features which can be utilised to enhance bonding through adhesives or other surface features beneficial to a component.

Mould lining

An aerofoil blade for a gas turbine engine, the blade having a metallic core defining a number of cavities that contain a foamed material. The cavities are shaped such that the force of an impact on one surface of the blade is dissipated through the foam and transmitted to the metallic core. A fibrous internal containment device allows the blade to fragment progressively thereby spreading the load imparted by the blade to a casing should the blade fragment upon impact.

Growing community of inventors

Derby, United Kingdom

Ewan Fergus Thompson