Rolls-royce Corporation

Stephen John Booth

Alison Jane McMillan

Sivasubramaniam K Sathianathan

Ian Graham Martindale

Dale Edward Evans

Peter Rowland Beckford

David S Yazdani

David V Roberts

Caroline McLachlan

Peter E Farrington

Duncan Auterson

Alison J Mcmillan

Sivasubramaniam Kathirgamathamby Sathianathan

David Vaughan Roberts

Alison Jane Mcmillan

A component, for example an aerofoil vane or other gas path structure in a gas turbine machine such as a gas turbine engine, in which an insulated electrical conductor path is embedded structurally integrally, and in which electromagnetic shielding, for the embedded electrical conductor path is provided structurally integrally.

Electrical conductor paths

A fan blade containment assembly () for a turbofan gas turbine engine () comprises a cylindrical, or frustoconical, casing () arranged to surround an arrangement of fan blades (). At least one hollow tubular member () is arranged radially within and secured to the casing () and the at least one hollow tubular member () contains a filler material (). The at least one hollow tubular member () extends circumferentially. The hollow tubular member () is helical and the axial spacing between the adjacent turns of the tubular member () varies and the density of the filler material () varies in order to match the severity of the impact expected at each axial location along the casingof the fan blade containment assembly ().

Rotor blade containment assembly for a gas turbine engine

A guide vane arrangementfor a gas turbine engine (, FIG.) includes a vane memberextending between inner and outer platformswhich are respectively mounted on inner and outer mounting members. One of the inner and outer platformsincludes a resilient that abuts the respective inner or outer platformto permit relative movement between the inner or outer platformand the respective inner or outer mounting member

Guide vane arrangements for gas turbine engines

Appropriate location of components such as vanes in gas turbine engines is important. These components are located between tangs held in interference engagement. There are four relatively rigid mounting points constituted by the tangs engaging respective opposed slots in a casing or a mounting ring. Only three point limitation with respect to displacement and rotation is adequate so provision of a fourth locator causes unnecessary constraint. A relatively resilient or compliant locator means it is possible to reduce the amount of constraint upon the component mounting whilst the other locators are adequate for positioning of the component.

Mounting arrangement

A platform arrangement for components such as aerofoil vanesis provided whereby the necessary rigidity provided by the platform does not create excess problems with respect to stress and strain fatigue failure at thinner sections of the component. The leading edgeand trailing edgeof a vane generally have a thinner section and so when subject to greater flex deformation such flex deformation may lead to premature failure through stress and strain. Structural configurations are now provided which comprise cut out windowsin the platformbeneath the edgesor alternatively differential material types at these locations with a less stiff nature. Generally, a backing memberis provided below an integral platform layerto create generally greater stiffness in the platform unit formed by the combination but in accordance with the present invention this backing membermay include the cut out windowsor have the necessary differential material types for variable flexibility compliance at portions of reduced component cross-section.

Platform mounted components

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 ( ).

Gas turbine engine blade 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 ( ). 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 ( ). The transition portion ( ) connects the blade containment portion ( ) and the upstream portion ( ) to transmit loads from the blade containment portion ( ) to the flange ( ) on the upstream portion ( ). The ratio of the thickness (T ) of the flange ( ) on the upstream portion ( ) to the thickness (T ) of the upstream portion ( ) is between 3 to 1 and 6 to 1. The flange ( ) on the upstream portion ( ) is radially scalloped ( ) between adjacent fasteners ( ) and the upstream portion ( ) is relatively thin such that the flange ( ) and upstream portion ( ) are allowed to deform to reduce impact loads transmitted to the flange ( ) on the casing ( ).

A gas turbine engine fan blade containment assembly ( ) comprising a generally cylindrical, or frustoconical, metal casing ( ) has an upstream portion ( ), a blade containment portion ( ) and a transition portion ( ). The upstream portion ( ) has a flange ( ) connecting the metal containment casing ( ) to an axially adjacent casing. The upstream portion ( ) of the casing ( ) has a greater diameter (D ) than the diameter (D ) of the blade containment portion ( ) and the blade containment portion ( ) has a greater thickness (T ) than the thickness (T ) of the upstream portion ( ). The transition portion ( ) connects the blade containment portion ( ) and the upstream portion ( ) to transmit loads from the blade containment portion ( ) to the upstream flange ( ). The transition portion ( ) has a smoothly curved increase in diameter between the blade containment portion ( ) and the upstream portion ( ) whereby the transition portion ( ) is allowed to flex to reduce impact loads transmitted to the upstream flange ( ).

Growing community of inventors

Derby, United Kingdom

Stephen John Booth