Abstract: An apparatus for supporting a tool in an assembled apparatus. The apparatus includes a support structure, the support structure having a central member and a plurality of support members pivotally mounted on the central member. The support members are movable between a non-deployed position in which the support members extend a minimum distance from the central member and a deployed position in which the support members extend a maximum distance from the central member.

Abstract: A forging apparatus and method is disclosed in which a die has two separate cavities, each having a first cavity portion and a second cavity portion. A billet of material is received in a first cavity portion and struck by a striking portion of an extrusion punch so as to be forced into the corresponding second cavity portion to form a shaped component. The billet of material can be placed into either of the two cavities for extrusion. This may increase the number of extrusion operations that can be performed by a single die.

Abstract: A fuel manifold and fuel injector arrangement for a gas turbine engine combustion chamber comprises an annular combustion chamber casing arranged around the combustion chamber. A plurality of circumferentially spaced fuel injectors supply fuel into the combustion chamber and a fuel manifold supplies fuel to each of the fuel injectors. The fuel manifold comprises a plurality of flexible fuel pipes and a plurality of T piece connectors. The stem of each connector is mounted on an outer end of a respective one of the fuel feed arms and each flexible fuel pipe interconnects an arm of one connector with an arm of an adjacent connector. Each connector is arranged such that the arms are arranged at angles to the planes containing the axis of the casing and perpendicular to the axis of the casing respectively.

Abstract: This invention concerns a fuel delivery system for an aircraft engine, including a fuel delivery regulator arranged to receive fuel from a plurality of fuel sources for supply to the engine. An engine operating condition sensor reading is received by a control unit arranged to control operation of the regulator. The control unit actuates the regulator based on a received signal from the engine operating condition sensor in order to vary the volume of fuels from the plurality of fuel sources supplied to the engine during at least a portion of the landing/take-off (LTO) cycle relative to a further portion of the aircraft flight. The different fuels may include kerosene and an alternative fuel, such as a biofuel.

Abstract: A chamber fluid removal system including a pump and an ejector is disclosed. The system is arranged in use to pump fluid from a chamber using the pump and deliver it to the ejector as a motive fluid and the system being further arranged to draw fluid from the chamber or from a second chamber as an entrained fluid by entraining it using the ejector and the motive fluid.

Abstract: An electrical machine including a rotor and a stator, at least one of the rotor and stator being provided with superconducting first electrical windings; and a set of one or more screen electrical windings, provided in the form of one or more further superconducting electrical windings, arranged around and radially outward of the first electrical windings; wherein the set of screen electrical windings is arranged to be supplied with an electrical current for generating a magnetic field of suitable magnitude and phase to reduce the magnitude of the magnetic field, generated at least by the first electrical windings during operation of the electrical machine, radially outwards of the screen electrical windings.

Abstract: A gas turbine auxiliary power unit system for an aircraft comprises an aircraft cabin provided with a pressurised air supply, a gas turbine engine comprising a compressor assembly, and a controller. The pressurised air supply is provided to the aircraft cabin through an aircraft cabin air inlet, and exhausted from the aircraft cabin through an aircraft cabin air exhaust, while the gas turbine engine is provided with an inlet air flow from the aircraft cabin air exhaust. The controller is operable to control a flow rate of a fuel supplied to the gas turbine engine responsive to a power demand on the auxiliary power unit, and also to restrict an inlet air flow into the gas turbine engine, so as to maintain an air pressure inside the aircraft cabin within a pre-determined range.

Abstract: An airblast fuel injector is provided for a fuel spray nozzle of a gas turbine engine. The injector has an annular air passage for the passage of a swirling air flow therethrough. The swirling air flow is used by the injector to produce an atomized fuel spray. The air passage contains a swirler for producing the swirling air flow, the swirler comprising a circumferential row of vanes which span inner and outer side walls of the air passage. Viewed on a longitudinal section through the injector, the air passage has a bend downstream of the swirler, the bend changing the direction of the air passage. The vanes are configured to introduce a radial component to the air flow exiting the swirler, the radial component guiding the air flow around the bend.

Abstract: 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.

Abstract: A gas turbine engine combustion chamber heat shield and seal assembly comprises a heat shield and a seal. The heat shield has an aperture and the seal is located in the aperture in the heat shield. The seal comprises an annular member having an upstream end, a middle and a downstream end. The upstream end of the seal has a diameter greater than the diameter of the aperture in the heat shield, the middle has a diameter less than the diameter of the aperture in the heat shield and the downstream end of the seal has a diameter greater than the diameter of the aperture in the heat shield.

Abstract: A vehicle is provided that has a rigid dressing raft 200. The rigid dressing raft 200 provides a part of a fluid and/or electrical system to the vehicle. The rigid dressing raft comprises elongate fibers 232, which may provide strength to the raft. The fibers 232 are electrically conductive, and a voltage source may be applied to at least one of the fibers. The fiber 232 may form a part of an electrical measurement circuit 400, such as a wheatstone bridge, which may be used to determine the electrical resistance of the fiber 232. The electrical resistance of the fiber 232 may then be used to determine the temperature and/or stress/strain of the raft 200.

Abstract: A powder deposition apparatus for producing a component comprises a base plate, an annular stack of heating elements, accommodating the base plate, one or more insulating elements, being interleaved between adjoining heating elements, a mechanism operable to deposit a plurality of layers of a powder material onto the base plate, and a laser energy source operable to selectively fuse a portion of the deposited layer. The annular stack of heating elements is sized such that a predetermined clearance is defined between the component and the annular stack of heating elements. As successive layers of the powder material are deposited onto the base plate, the base plate is lowered into the stack of heating elements, the heating elements being actuated sequentially to maintain a pre-determined temperature profile in the deposited layers.

Abstract: A combustor for a gas turbine engine which includes a flame tube made of a ceramic material and a metal casing which surrounds the flame tube. The combustor further includes a thermal insulation layer between the flame tube and the casing which protects the casing from the high temperatures produced by combustion in the combustor and a loading structure which holds the flame tube in a state of axial and radial compression at all engine operating conditions.

Abstract: Apparatus to control transmission of data, the apparatus comprising: a controller configured to: receive data from at least a first sensor within an azimuth thruster; control storage of the received data in memory; determine whether at least one criterion is satisfied, the at least one criterion varying with the relative positioning of a first antenna mounted on a lower housing of the azimuth thruster and a second antenna mounted on an upper housing of the azimuth thruster, the lower housing being configured to rotate relative to the upper housing; and control transmission of the stored data from the first antenna in response to determining that the at least one criterion is satisfied.

Abstract: A method of providing a threaded fastener with a multi-layered coating comprises the step of using a vapour deposition process to apply a multi-layered coating to a threaded portion of the threaded fastener, each layer of the multi-layered coating being formed from a coating material selected from the group comprising titanium, chromium, nickel, platinum, tantalum, and combinations thereof.

Abstract: Described is a nozzle guide vane assembly may comprise: a plurality of nozzle guide vane passages arranged in an annular array, each nozzle guide passage comprising inner and outer radial platforms, a suction surface of a first vane, and a pressure surface of a second vane, wherein the nozzle guide passages are made from a plurality of layers of ceramic fibres held in a ceramic matrix, wherein a first nozzle guide passage includes at least one attachment lug attaching the nozzle guide passage to either or both of an engine casing and an adjacent second nozzle guide passage, the attachment lug being integral with the first nozzle guide passage.

Abstract: A honeycomb structure comprising a core and at least one face sheet. The core having a honeycomb configuration comprising an array of hollow cells formed between a network of walls. The or each face sheet having a plurality of outwardly directed protrusions. The or each face sheet being affixed to the core to cover the hollow cells with each said protrusion being received within a respective region of the core and bonded to the core.

Abstract: An aerofoil component (32) defining an in use leading edge (38) and a trailing edge (40). At least one of the leading edge and the trailing edge (38, 40) comprises a plurality of first and second recesses (52, 56) projecting in a direction corresponding with an in use flow direction, the first and second recesses being spaced apart normal to the in use flow direction and having a different chordal extent.

Abstract: A turbine blade having labyrinth of internal channels for circulation of coolant, the novel labyrinth geometry includes; inlet arranged on axially upstream face of terminal portion leading to an upstream duct portion having first section adjacent the inlet and a second section, the second section having reduced cross section compared to first section; a first passage intersecting first section and extending through the blade body towards tip of the blade, a proximal end of leading edge passage arranged to capture incoming air flow; a main blade passage intersecting a downstream duct portion, the downstream duct portion arranged in axial alignment with the upstream duct portion but separate from upstream duct portion; and a restrictor passage intersecting with the mid-blade passage and extending towards a mid-blade duct portion, the mid-blade duct portion in axial alignment with the upstream and downstream duct portions and in fluid communication with the upstream duct portion.

Abstract: A blade or a vane for a gas turbine engine. The blade or vane comprising an aerofoil and a leading edge member attached to the aerofoil. The leading edge comprises an electrically conductive support member and a nano-coating formed on the support member.