Abstract: An aerofoil body for a gas turbine engine is provided. The aerofoil body has leading and trailing edge portions, wherein one of the leading and trailing edge portions is a morphable edge portion having a composite layer structure. The aerofoil body further has a non-morphing central portion which forms pressure and suction surfaces of the aerofoil body between the leading and trailing edge portions. The composite layer structure includes a return spring, one or more shape memory alloy layers, and a flexible cover for the return spring and the one or more shape memory alloy layers. The flexible cover defines pressure and suction surfaces of the aerofoil body at the morphable edge portion. The one or more shape memory alloy layers are electrically heatable to deform the layers against the resistance of the return spring, and thereby alter the pitch of the aerofoil body at the morphable edge portion.

Abstract: A cooled gas turbine engine component includes a wall having a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. Each aperture has an inlet in the first surface and an outlet in the second surface. Each aperture includes an inlet portion, a collection chamber, a metering portion, a U-shaped bend portion and a diffusing portion arranged in flow series from the inlet to the outlet. The inlet portion of each aperture is arranged substantially perpendicularly to a surface of the collection chamber. The metering portion of each aperture is arranged to extend longitudinally from a first lateral side of the collection chamber and the diffusing portion of each aperture is arranged at an angle to the second surface. Each outlet has a quadrilateral shape in the second surface of the wall and each outlet is displaced laterally from the metering portion.

Abstract: A power electronics module is provided having one or more power converter semiconductor components. The power electronics module further has a substrate having a first surface to which the one or more components are mounted, and having an opposing second surface from which project a plurality of heat transfer formations for enhancing heat transfer from the substrate. The power electronics module further has a coolant housing which sealingly connects to the substrate to form a void over the heat transfer formations of the second surface. The coolant housing has an inlet for directing a flow of an electrically insulating coolant into the void and an outlet for removing the coolant flow from the void, whereby heat generated during operation of the one or more components is transferred into the coolant flow via the substrate.

Abstract: Methods are provided for: (i) measuring the position of the blade stagger angle axis for one or more blades of a row of blades attached to a rotor, (ii) measuring the blade tip stagger angle for one or more such blades, and (iii) measuring the blade tip axial displacement for one or more such blades. The methods use forward and rearward blade tip timing datasets for successive rotations of the blades from two axially spaced blade tip timing probes. The forward probe is forward of the rearward probe along the axial direction of the rotor. The blade tip timing datasets allow the times of arrival of the blades at the respective probes to be measured. The methods also use a once per revolution dataset for the successive rotations of the blades. The once per revolution dataset allows the angular velocity of the blades to be measured.

Abstract: Fixture Apparatus and methods of manufacturing fixture apparatus. Fixture apparatus comprising: a first body to at least partially support an object, the first body including a structure having variable stiffness along at least a first axis of the first body.

Abstract: A method is provided of processing one or more blades of a row of blades which forms part of a rotor for a gas turbine engine. The method includes: providing a rotor disc having a slot for mounting one or more blades; applying tape at one or both sides of the slot such that when the blades are loaded in the slot the tape reduces a range of tilt angles which can be adopted by the blades; loading the blades in the slot; and performing a processing operation on the loaded blades.

Abstract: There is proposed a method of forming an inflated aerofoil (1), the method comprising the steps of: forming a layered, planar pre-form (30); providing at least one stress-relieving opening (44, 45, 46, 47) through the pre-form; hot creep forming and inflating the pre-form (30) to form an intermediate aerofoil; and subsequently removing material from the intermediate aerofoil, including at least a region containing the or each stress-relieving opening (44, 45, 46, 47), to form a finished aerofoil.

Abstract: A method providing a first tubular workpiece having a first weld surface at an end thereof, and a second tubular workpiece having a second weld surface at an end thereof; aligning the workpieces on a common axis with the weld surfaces facing each other, rotating one workpiece about the axis relative to the other workpiece, and engaging the first and second weld surfaces such that the rotation raises the temperature at the weld surfaces to create a weld interface; and ceasing the rotation and allowing the weld interface to cool to weld the workpieces together at the interface. The first weld surface is an apex region of an annular projection at the end of the first workpiece, on a longitudinal section through the aligned workpieces the annular projection having a profile in which radially inner and outer side surfaces of the annular projection taper towards the apex region.

Abstract: Each fuel injector has a main nozzle and pilot nozzle. A main fuel manifold to supply fuel to the main nozzle of each fuel injector and pilot fuel manifold to supply fuel to the pilot nozzle of each fuel injector. The main fuel manifold includes plurality of flexible main fuel pipes. Also, plurality of cross-piece connectors including a stem and four arms. The stem of each connector mounted on one fuel injector. The first and third arms extend in opposite directions from the stem and second and fourth arms extend in opposite directions from the stem. Each fuel pipe interconnects the first arm of one connector with a third arm of an adjacent connector and each connector so the first and third arms are at an angle relative perpendicular to the axis of the annular combustion chamber casing so the main fuel manifold extends around the combustion chamber casing sinusoidally.

Abstract: A marine cathodic protection system configured to protect a metal structure exposed to seawater from corrosion. The system includes a first anode provided on or adjacent the protected metal structure at a first position. The first anode is exposed to seawater, is electrically insulated from the protected metal structure, and is formed of a metal having a greater negative potential than the protected metal. The system further includes a second anode provided on or adjacent the protected metal structure at a second position. The second anode is electrically connected to the first anode. The first position is preferably substantially submerged in said seawater such that the protected metal and the first anode cooperate to define a seawater battery configured to apply an electrical current to the second anode, the second anode thus being an impressed current anode.

Abstract: A blade for an axial flow machine having a pressure surface, suction surface and trailing edge. The blade has a cross-sectional aerofoil profile including: a region of maximum curvature corresponding to the trailing edge of the blade and defining a trailing edge radius of curvature r; a trailing edge region extending from the trailing edge and having a chordwise extent equal to curvature r?s trailing edge radius; a taper region adjacent the trailing edge region, the taper region having a chordwise extent greater than the curvature r?s trailing edge radius and no more than 15% of the blade's chord; a body region adjacent the taper region; a pressure surface boundary corresponding to the blade's pressure surface; and a suction surface boundary corresponding to the blade's suction surface. A thickness between the pressure and suction surface boundaries reduces within the taper region towards the trailing edge by at least 50%.

Abstract: An aircraft gas turbine engine nacelle comprises a thrust reversal arrangement. The thrust reversal arrangement comprises at least first and second circumferentially spaced fixed thrust reverser cascade boxes each comprising a plurality of thrust reverser vanes configured to direct air forwardly and circumferentially and at least one inter-leaved translating circumferential turning vane configured to direct air in a direction having a circumferential component. The circumferential turning vane is moveable from a stowed position provided between the first and second circumferentially spaced thrust reverser cascade boxes, and a deployed position axially rearwardly of the thrust reverser cascade boxes.

Abstract: A system for countering the rolling motion of a marine vessel, includes one or more sensors adapted to characterize a sea condition approaching the vessel, one or more control systems, a computer, and one or more active stabilizers. The computer is adapted to receive the characterized sea condition data, is further adapted to generate one or more control signals in dependence on the characterized sea condition data, and is still further adapted to transmit the or each control signal to the or each control system. The or each control system is in turn adapted to actuate the or each active stabilizer in response to receipt of the or each control signal, to counter the rolling motion of the marine vessel.

Abstract: A fixture for stiffening a thin-walled component comprises linking elements which support respective biasing parts and pressure parts. The biasing parts are arranged to urge the pressure parts to press on a thin-walled component, and the linking elements are rigidly connected to one another to resist a reaction force exerted on the pressure parts by the thin-walled component.

Abstract: Described is a brush seal for sealing between a first component and a second component which relatively rotate during normal use, comprising: an annular housing which is attached to a first component in use; a plurality of bristles each having a fixed end attached to the housing and a free end, wherein the free ends of at least some of the plurality of bristles contact the second component during normal use to provide a sealing surface, wherein the sealing surface includes a plurality of discontinuities around the circumference of the brush seal for providing hydrodynamic lifting force in use.

Abstract: A rigid electrical raft is provided to a gas turbine engine via a fusible mount arrangement. The rigid electrical raft may be a part of an electrical system of the gas turbine engine, for example a part of the electrical harness. The fusible mount is arranged to break when a predetermined load is applied. The rigid electrical raft may be attached to a fan case of the engine, and the predetermined load may be that which results from a fan blade being released from the hub. This ensures that the rigid electrical raft is protected from the load.

Abstract: A fuel and oil system comprising a fuel pump; an oil pump. A first electric motor controller configured to supply a variable electrical drive. A second electric motor controller configured to supply a variable electrical drive. A fixed electrical drive. The fuel pump is selectively connected to and driven by the first electric motor controller or the second electric motor controller. The oil pump is selectively connected to and driven by the second electric motor controller or the fixed electrical drive.

Abstract: A method for the manufacture of a component having a defined geometry and dimensions is described. In sequence, the steps of the method involve; a) using an additive layer manufacturing process, budding a three-dimensional net shape of the component; b) applying a subtractive surface finishing operation to the product of step a); c) applying a heat treatment to the product of step b) whereby to provide a component to the defined geometry and dimensions.

Abstract: A fan assembly for a gas turbine engine. The assembly includes a hub and a plurality of blades projecting from the hub. The hub includes an inlet aperture located adjacent a blade root. The inlet aperture is in fluid communication with a passage extending along at least part of a span of the blade, and communicates with an outlet provided on an exterior of the blade, radially outwardly of the inlet.

Abstract: A method and apparatus for vibro-treating an object. The method includes the steps of controlling a relative displacement between a vibro-treating media and a surface area of the object to provide a vibro-treating effect; and, controlling movement of the object relative to a surface of the vibro-treating media whilst controlling relative displacement between the vibro-treating media and the surface area of the object, according to one or more pre-determined conditions, to provide a substantially even vibro-treating condition over the surface area of the object.