Rolls-royce Corporation

Dale Edward Evans

Ian C D Care

Ian Colin Deuchar Care

Steven Aleksy Radomski

Clive Grafton-Reed

Matthew Ashley Charles Hoyland

David Laker Christmas

Mathew Ashley Charles Hoyland

Alison Jane McMillan

Ewan Fergus Thompson

Cedric Brett Harper

Stephen John Booth

James Alex Finlayson

Bijoysri Khan

Michael R Lawson

Matthew John Willshee

Matthew A C Hoyland

Mickael Drozdz

Alfonso Villanueva

Ben Williams

John P Barton

Steven Radomski

Cedric Harper

Ian Care

Matthew Hoyland

Ian Deucher Care

A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

Vane arrangement for a gas turbine engine

A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub with a through hole extending therethrough. The method comprises welding the aerofoil to the stub such that the open end of the hollow cavity of the aerofoil is aligned with the through hole of the stub so as to define a hollow region extending through the support member and stub to the cavity of the aerofoil. During welding a tool is positioned within the through hole and cavity and is aligned with an interface between the stub and aerofoil, the tool being configured to prevent weld splatter onto a surface of the cavity or through hole.

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

The present invention provides a retention device for applying a radial force to a component (e.g. a rotor blade) within a slot (e.g. on a rotor disc). The device comprises a body having an outer surface for facing the component. The outer surface comprises a recess having a recess base with a first ramped surface extending from a lower end proximal a first lateral end of the body to an upper end. The device further comprises a spring element having a contact surface for contacting the component and a first mounting portion for mounting the spring element on the first ramped surface such that the first mounting portion is slidable along the first ramped surface towards the upper end to increase the spacing of the contact surface above the outer surface of the body.

Retention device

A fan casing assembly comprising an annular casing member for circumferentially surrounding a fan, and an annular fan track liner comprising a plurality of circumferentially adjacent liner panels. The annular fan track liner is positioned radially inward of the annular casing member. A tilting arrangement is provided and configured to selectively circumferentially tilt one or more of the liner panels, such that, in the event of a fan blade being released from a fan, the tilting arrangement can initiate tilting of one or more liner panels so that the liner panels can trim one or more of the remaining fan blades.

Fan casing assembly

A fan track liner assembly for ducted fan engine which provides for reduced strain and deformation of front of fan case in the event of a fan blade off event. Various assemblies are proposed. In one aspect, assembly includes fan track liner panel and plurality of fasteners which are arranged to secure panel to fan case of engine, wherein: a forward portion of panel includes hinged portion which operates as trapdoor to permit blade or blade fragment to pass through, and fasteners are arranged to fail in the event of blade or blade fragment passing through trapdoor causing panel to be displaced rearwards in fan case. Other aspects provide for reduced height of support on fan case for attaching fan track liner and for collapsible comb box.

Fan track liner assembly

A fan track liner assembly for a ducted fan engine which provides for ease of installation and replacement. The assembly includes a plurality of panels; and a plurality of fastening members which are arranged to secure the panels to the fan case of the engine, wherein: each fastening member has a base portion and an elongate arm member, and further wherein: the base portion has an attachment portion which is used to secure the fastening member to the fan case; and the arm member extends from the base portion, and each panel has slotted edge portions on opposing edges at one end of the panel which are each arranged to engage with respective arm members of fastening members on either side of the panel when the panel is assembled with the fastening members by sliding the panel onto the fastening members or vice-versa.

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

The present invention relates to a fire resistant fan casing for a gas turbine engine. The casing has a projection such as a reinforcing rib or a mounting pad. The projection comprises at least one shell portion formed of a fiber/plastic composite material encasing a core of fire resistant material such as a metallic material or a ceramic matrix composite material.

Fan casing for a gas turbine engine

A turbomachine casing assembly including an inner casing element for arrangement radially outward of a turbomachine fan; an outer casing element for arrangement radially further outward of the turbomachine fan; a retaining lip arranged radially inward of a portion of the inner casing element; and a separator extending between the inner and outer casing elements and arranged to urge a portion of the inner casing element against the lip. The separator is arranged in compression between the inner and outer casing elements to urge the portion of the inner casing element against the lip. The separator is arranged to engage a frangible region of the inner casing element such that the frangible region is configured to break in response to an impact satisfying predetermined conditions, allowing the inner casing element to displace radially outwards exposing features to improve retention of a released fan blade.

Turbomachine fan casing assembly

Fan containment system fitting around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system includes a fan case having an annular casing element for encircling the array of fan blades and a hook projecting in a radially inward direction from the annular casing element and positioned axially forward of the array of fan blades when the fan containment system fitted around fan blades. An annular fan track liner positioned substantially coaxial to the annular casing element. Clamping arrangement connects fan track liner to the hook. Clamping arrangement is configured under the condition that a fan blade impacts the fan track liner, the clamping arrangement releases connection between the hook and a portion of fan track liner so that a portion of the fan track liner can move towards the annular casing element to encourage the fan blade to impact the hook.

A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element and one or more arcuate fence elements positioned between the first and second casing elements. Following impact of a detached fan blade, a radially outward movement of the first casing element causes the or each fence element to project into the air flow passing through the turbomachine.

Turbomachine casing assembly

A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibers extending in a generally radial direction and a plurality of second reinforcing fibers extending in generally axial and circumferential directions. The second fibers are interlaced with the first fibers so as to form a more unified and integrated structure, and to prevent the first reinforcing fibers from moving relative to one another.

Composite aerofoil vane

A fan containment system having a generally cylindrical fan case including a hook projecting in a generally radially inward direction and positioned axially forward of a radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a panel which is positioned axially rearward of the hook and positioned axially forward of the radial array of fan blades and forms a substantially continuous air washed surface with the fan track liner. The panel is temporarily deformable so as to absorb the impacts of any foreign bodies, which enter the gas turbine engine, without compromising the structural integrity of the panel while being weak enough so that in the event that one of the fan blades is released from the hub, the fan blade tip of the detached fan blade is not inhibited from moving radially outward of the hub.

Fan containment system

This invention relates to a stator aerofoil for a gas turbine engine, comprising: a body portion; at least one panel which forms at least part of one of either the pressure or section surface of the aerofoil; at least one internal chamber which is bounded by the body portion and panel; and, at least one elastomeric component within the at least one internal chamber, wherein the elastomeric component at least partially defines a cell within the internal chamber, wherein the cell is in fluid communication with the exterior of the aerofoil.

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Derby, United Kingdom

Dale Edward Evans