Rolls-royce Corporation

Cedric Brett Harper

Ian Colin Deuchar Care

Julian Mark Reed

Ian Graham Martindale

Neil Humphries

Ian C D Care

Dale Edward Evans

Clare L Pool

Geoffrey R Attewell

Michael Creagh

Geoffrey Roger Attewell

Clare Louise Pool

A fan containment system arranged to be fitted around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. Each fan blade has a respective tip. The system includes: a cylindrical fan case including a hook projecting in a radially inward direction and positioned axially forward of the radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a damaging tool which projects radially inwards from the fan case towards the tips. The damaging tool has a tip radially outward of the fan blade tips. The damaging tool is configured that in the event that one of the fan blades is released from the hub, the tip of the damaging tool damages the fan blade tip of the released fan blade to promote penetration of the fan blade into the fan track liner.

Fan containment system

A fan containment system includes an annular casing element and a hook projecting in a generally radially inward direction from the annular casing element. A fan track liner is connected to the hook via a fastener. The fan track liner has a forward end proximal to the hook and a rearward end distal to the hook. A pivot member protrudes radially inward from the annular casing element and is arranged and positioned between the forward and rearward end of the fan track liner such that a forward portion of the fan track liner is pivotable about the pivot member, so that upon release of a fan blade the forward portion of the fan track liner pivots about the pivot member into a voidal region provided between the annular casing element and the forward portion of the fan track liner to encourage engagement of the hook with a released fan blade.

Pivoting fan track liner for blade retainment

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 a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element. The fan containment system further includes an annular fan track liner comprising a plurality of adjacent arcuate fan track liner panels. Each of the plurality of fan track liner panels is connected to the fan case at the hook via one or more fasteners configured to permit movement of the fan track liner panel relative to the hook such that the fan track liner panel can pivot towards the annular casing element when a released fan blade impacts the fan track liner panel.

Gas turbine engine

A turbomaehine casing assembly includes a first casing element, located radially outward of one or more rotating aerofoil elements of a turbomachine, and a second casing element, located radially distal to the first element. A void is provided at a first end of the first element, between radially proximal faces of the first and second elements. The first end of the first element is located against a corresponding first end of the second element by an energy absorbing element. The first element includes a cantilever, arranged in a region extending along the first element from the first end with a pivot axis at its mid-portion. Release of one of the rotating aerofoil elements, resulting in impact with the first element, further results in the cantilever bending into the void between the first and second elements, enabling the rotating aerofoil element to be trapped within the casing assembly.

Turbomachine casing assembly

A turbomachine casing assembly including: a first casing element arrangeable adjacent to one or more rotating aerofoil structures of a turbomachine; a second casing element provided at a radially outer position with respect to the first casing element; and an infill member disposed between the first and second casing elements, wherein an end of the infill member is set back from an end of the first casing element such that a void is provided between the first and second casing elements.

A turbomachine casing assembly comprises a first casing portion for at least partially encasing one or more rotating aerofoil structures of a turbomachine and a second casing portion; the first casing portion being movable with respect to the second casing portion. One or more resilient elements are arranged so as to resist movement of the first casing portion with respect to the second casing portion.

A turbomachine casing assembly including 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 is provided. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. The cantilever is arranged in a region extending along the first casing element from the first end; and having a pivot axis at a mid portion thereof.

A stator vane assembly includes: inner and outer vane supports, and vanes extending radially between the supports. The supports have openings for receiving the ends of the vanes, and each vane is connected to the supports by a vane boot. Each vane boot has: a rim portion shaped to locate the boot within the corresponding opening in the vane support, the rim portion engaging with the inner surface defining the opening, an abutting portion for abutting against the vane support in the region surrounding the opening, and a vane pocket for accommodating the end of the vane. The vane pockets of the vane boots are shaped so as to position the vane with a predetermined stagger angle.

Stator vane assembly

A composite component such as a fan casing liner panel for a gas turbine engine comprises an abradable layer and a layer. The layer is provided with a septum layer, to which the abradable layer is bonded. The septum layer is perforated by holes, which enable air to be extracted from the region between the septum layer and the abradable layer during the process of bonding the components together, for example by a vacuum bonding process.

Fan section

A sealing assembly () for at least partially sealing a gap () leading to a void () between first and second members (), the first and second members forming part of a gas-washed surface of a jet engine, wherein the sealing assembly comprises: a bridging portion () couplable to one of the first and second members and movable to engage the other of the first and second members so as to block off the void between the first and second members from the gas-washed surface.

Sealing assembly

An acoustic assembly for a fan casing of a turbofan engine is made up from acoustic liner panel components which each comprise a body and a backing sheet. The body is an integral injection moulding that generally includes an acoustic structure, a perforated sheet and fastening portions. Adjacent panel components engage each other at non-linear circumferential edges which generally includes lugs on one of the components which are received in recesses of the other component. The lugs are defined by following cell walls over a convoluted path along the circumferential edge.

Acoustic liners

A liner panel for a fan casing of a gas turbine engine includes a honeycomb layer, a septum layer and an abradable layer. The fan casing is provided with a containment system in case of fan blade failure. In use, ice may be released from a fan blade in a first direction, and (in the case of a blade-off event) a fan blade or part of a fan blade may be released in a second direction. The panel has a compressive strength greater in the first direction than in the second direction such that the released ice will be deflected by the panel but the released fan blade or part of a fan blade will pass through the panel.

Liner panel

A turbofan gas turbine engine () comprises a fan rotor () carrying a plurality of radially extending fan blades (). A fan blade containment assembly () surrounds the fan blades () and the fan blade containment assembly () comprises a generally cylindrical, or frustoconical, metal casing (). The casing () comprises an annular member () positioned axially upstream of the tip () of the fan blade (). The annular member () extends in a radially inwardly and axially downstream direction from the metal casing () towards the tip () of the fan blade. A set of cassettes () carries fan blade track panels (B,C,D). The cassettes () are secured to the metal casing () by axially extending members () on the upstream and downstream ends () of the cassettes () which locate on the annular member () and are secured to inserts () on the inner face of the casing ().

Liner for a gas turbine engine casing

A clip used to attach an acoustic panel to a fan casing of a gas turbine engine is 'U' shaped. One arm of the clip is provided with a spacing portion cut into the material of the arm and which may be bent to define the spacing between the outer face of the arm and a support. An engagement portion, which may also be cut into the material of the clip, may be bent to engage a recess in a tenon inserted into the receiving portion.

Clip

A gas turbine engine rotor blade containment assembly () comprising a generally cylindrical, or frustoconical, casing (). The casing () having at least one member () and the member () has a first portion () extending radially from the casing () and a second portion () extending axially from the first portion () of the member (). At least one cassette () being provided and one or more liner panels () being arranged in each cassette (). A first end () of each cassette () being locatable on the second portion () of the member () and the first end () of each cassette () being shaped to correspond to the shape of the first and second portions () of the at least one member () to protect the first and second portions () of the at least one member (). The second end () of each cassette () having at least one axially extending member () removably securable to the casing ().

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Derby, United Kingdom

Cedric Brett Harper