Rolls-royce Corporation

Ian Graham Martindale

Sivasubramaniam K Sathianathan

Julian Mark Reed

David Geary

Cedric Brett Harper

Stephen John Booth

Paul Hodgson

Kenneth Franklin Udall

David S Knott

Ewan Fergus Thompson

Michael R Lawson

Neil Humphries

Robert Daniel Anthony

Caroline McLachlan

Peter E Farrington

Duncan Auterson

David S Yazdani

Michael Creagh

Sivasubramaniam Kathirgamathamby Sathinathan

Michael Rayner Lawson

Sivasubramaniam Kathirgamathamby Sathianathan

An instrumentation arrangement for a component includes a number of measurement devices mounted on a baseplate. The baseplate is shaped to correspond to the surface of the component in use, and has attachment features engageable with features of the component, so that the rake can be easily installed and removed without modification of the component.

Instrumentation arrangement

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 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 ().

Rotor blade containment assembly for a gas turbine engine

A spacer arrangementis provided in which wedgesare arranged to have an interfacebetween them such that a thermally variable membercan cause relative motion between the wedgesto adjust an arrangement lateral dimension dependent upon temperature. In such circumstances with the arrangementpositioned within a gapbetween a casingand unison ring, retention of position of that unison ringcan be maintained. The unison ring is arranged to adjust position of variable vanes.

Spacer arrangement

A gas turbine engine rotor blade containment assembly () comprises a containment casing () and the containment casing () has a plurality of axially spaced ribs (). The ribs () extend circumferentially and radially inwardly from the containment casing () to define a plurality of circumferentially extending grooves () and a perforate sheet () is secured to the radially inner ends () of the ribs (). In the arrangement of the present invention the blade containment function and the acoustic treatment function are combined.

Gas turbine engine blade containment assembly

A joint assembly for limiting an extension of the joint in the direction of a load path derived from an impact comprising a first member having a portion and a second member having a portion, the portions overlapping one another and arranged generally parallel to one another and secured together via securing means disposed through corresponding holes defined therein. One of the overlapping portions further defines, sequentially in the direction of extension, a shear neck, a pocket and a catcher portion. In the event of a worst-case impact load the securing means shears through the shear neck and the pocket and is arrested by the catcher portion, thereby the extension of the joint assembly is limited and the joint assembly remains integral.

Turbo fan gas turbine engine having a rotor containment assembly

A gas turbine engine fan blade containment assembly ( ) comprising a generally cylindrical, or frustoconical, metal casing ( ) has an upstream portion ( ), a transition portion ( ) and a blade containment portion ( ) and a downstream portion ( ). The upstream portion ( ) has a flange ( ) connecting the metal casing ( ) to a flange ( ) on axially adjacent casing ( ). The blade containment portion ( ) has a greater thickness (T ) than the thickness (T ) of the upstream portion ( ) and the downstream portion ( ). The downstream portion ( ) has impact protection means ( ) located on its inner surface ( ) to protect the downstream portion ( ) of the containment casing ( ). The impact protection means ( ) comprises a plurality of radially inwardly and circumferentially extending ribs ( ) on the inner surface ( ) of the downstream portion ( ) to act as spacer between an inner portion of a detached fan blade ( ) and the downstream portion ( ).

A gas turbine engine fan blade containment assembly ( ) comprising a generally cylindrical, or frustoconical, metal casing ( ) which has an inner surface ( ), an outer surface ( ), an upstream flange ( ) and a downstream flange ( ). The outer surface ( ) of the metal casing ( ) is provided with a pattern of blind apertures ( ) which extend radially inwardly from the outer surface ( ) of the metal casing ( ) between the flanges ( ). The fan blade containment has reduced weight of the metal casing ( ) of the fan blade containment assembly ( ) for a large diameter turbofan gas turbine engine ( ) but has unimpaired stiffness and penetration resistance.

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 annular, or frustoconical, cross-section casing ( ). At least one corrugated sheet metal ring surrounds the casing ( ) wherein the corrugations extend with axial and/or circumferential components.

A gas turbine engine rotor blade containment assembly ( ) comprising a generally cylindrical, or frustoconical, first metal casing ( ) and a plurality of generally cylindrical, or frustoconical axially spaced second metal casing is ( & ). The second metal casings ( ) surrounded and abut the first metal casing ( ). The first metal casing ( ) is relatively hard and tough to contain a fan blade ( ). The second metal casings ( are relatively soft and lightweight to stiffen the first metal casing ( ) and fan blade containment regions (A, B & C). The second metal casing ( ) are arranged coaxially with the first metal casing ( ). One of the second metal casing means ( ) is in a plane (Y) containing the fan blades ( ) of the gas turbine engine ( ). The first metal casing ( ) comprises steel and the second metal casing is ( ) comprise aluminum. The fan blade containment assembly ( ) is lighter for large diameter turbofan gas turbine engine ( ).

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 hook ( ) positioned axially upstream of the tip ( ) of the fan blade ( ). The annular hook ( ) extends in a radially inwardly and axially downstream direction from the metal casing ( ) towards the tip ( ) of the fan blade ( ). The metal casing ( ) has a containment portion (A) downstream of the annular hook ( ) and substantially in the plane of the leading edge of the tip ( ) of the fan blade ( ). The containment portion (A) of the casing ( ) has a greater diameter than the diameter of the casing ( ) at the annular hook ( ) to restrain upstream movement of a detached fan blade ( ).

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Derby, United Kingdom

Ian Graham Martindale