Abstract: A termination unit for a superconductor network. Including a primary system that includes a first superconductor cable. Also a first superconducting coil and a first auxiliary magnetising coil, each coil wound around the first superconductor cable. Also a terminal including a first leg, the first leg including an aperture configured to receive the first superconductor cable. The first leg defining a clearance about the first superconductor cable at ambient temperature and arranged to firmly clamp onto the first superconductor cable at a cryogenic temperature. The termination unit including a cooling system arranged to enclose and cool the primary system to cryogenic temperatures.

Abstract: An ink jet ink that may be used to provide a stop-off layer on a metallic substrate, the ink including: Between 4.8% weight to 35.1% weight Yttria nanopowder; between 2.6% weight to 19.3% weight of a stabiliser; between 0.3% weight to 1.9% weight of a binder; between 0.01% weight to 5% weight of a surfactant and between 0% weight to 30% weight of a humectant and the balance water.

Abstract: A vane for an exhaust system duct in a gas turbine engine including a vane plate, a guide plate, and a baffle. The vane plate includes a leading edge, a first leg and a second leg, with the first and second legs respectively extending on opposing sides of the leading edge to form a substantially U-shaped profile. The baffle connects respective distal ends of the first and second legs. The guide plate is accommodated within the vane plate, and includes a first aperture extending along the guide plate and aligned with the leading edge. The vane further includes a fluid inlet arranged, in use, to direct a fluid flow from outside the duct into an interior of the vane.

Abstract: A lock plate of a bladed rotor arrangement is hollow. The bladed rotor arrangement comprises is a bladed turbine rotor of a gas turbine engine. The hollow lock plate has reduced weight compared to a solid lock plate and reduces the centrifugal load on the rim of the rotor and reduces the stresses in the lock plate groove on the rotor blade and hence increases the working life of the rotor and the working life of the rotor blade respectively. The lock plate may have radially extending chambers and openings to provide a flow of coolant onto the rotor posts of the rotor).

Abstract: Bearing structure including a first bearing, surrounded by a housing, having a first inner and outer race and first set of rolling elements between the inner and outer races and a second bearing having a second inner and outer race and second set of rolling elements between the second inner and outer races. A first compliant element is connected to the first outer race. A rigid diaphragm is connected to the first outer race between the compliant element and outer race, and is connected to the housing at its outer end. The first compliant element, outer race and rigid diaphragm at least partly define a pressure chamber. The first outer race is axially slidable relative to the second such that a pressure increase in the chamber changes the axial spacing between the first and second outer races, inducing additional axial load on the bearings which helps balance thrust load sharing.

Abstract: A propulsion engine for an aircraft includes a first fan having a set of first blades and a second fan having a set of second blades. There is provided a first angular pitch adjustment mechanism coupled to the first set of blades, a second angular pitch adjustment mechanism coupled to the second set of blades and an actuation device coupled to the first angular pitch adjustment mechanism. The first and second angular pitch adjustment mechanisms are coupled together such that when the actuation device generates an output, the angular pitch of each of the first blades and each of the second blades changes.

Abstract: A seal arrangement for effecting a seal between first and second components arranged for relative rotation about a common axis. Seal arrangement includes a first seal surface associated with the first component, and a second seal surface associated with the second component. First and second seal surfaces are presented for air-riding interaction with one another during relative rotation between components such that, in use, a pressure drop is maintained across seal arrangement. First seal surface incorporates a plurality of spaced-apart hydrodynamic lift-generating features and plurality of ventilation recesses, each ventilation recess being interposed between respective pair of lift-generating features, and wherein each ventilation recess has depth measured normal to first seal surface which is greater than maximum dimension of each lift-generating feature measured normal to first seal surface. Seal arrangement may be embodied in compliant filament seal such as a leaf seal or a brush seal.

Abstract: A sleeve for retaining magnets around a rotor of an electrical machine. The sleeve is cylindrical and hollow, having axial length and having radial thickness between its inner surface and outer surface. The sleeve defines a plurality of axially spaced, circumferentially extending grooves. Each groove has radial depth which is less than the radial thickness of the sleeve.

Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine comprises using a capping panel to cover a pocket in a pocketed aerofoil body. The pocketed aerofoil body has a ledge of substantially constant thickness that extends around its perimeter, and to which the capping panel is joined (e.g. welded) during manufacture. This ensures that the geometry of the join is consistent around the perimeter, meaning that the resulting join has improved properties, for example in terms of residual stress and/or distortion.

Abstract: A method of detecting rotor and/or stator side faults in an induction motor. Signals indicative of three-phase stator currents of the induction motor are acquired (10) and converted (16) into three-phase current phasors. The three-phase current phasors are combined (16) to obtain a quantity having a DC component and an AC component.

Abstract: A gas bleed arrangement for a gas turbine engine. The gas bleed arrangement includes an annular casing defining a main gas flow path. The annular casing has a plurality of bleed ducts each defining a respective bleed flow path. The arrangement further includes a blocking element having at least one aperture. The blocking element is moveable to align the at least one aperture at least partly between the main gas flow path and at least one of the bleed flow paths to control fluid communication between the main gas flow path and the at least one of the bleed flow paths through the aperture.

Abstract: A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc includes a retention body having a key portion receivable in a keyway formed in the base of the slot, and a mating portion for mating with a complementary mating portion of the root to prevent relative axial movement between the retention body and the root. The retention body has a lowered position in which the key portion is received sufficiently deeply in the keyway to allow the root to be positioned in the slot without interference from the retention body and also has a raised position in which, after the root is positioned in the slot, a part of the key portion is still received in the keyway while the mating portion mates with the complementary mating portion of the root.

Abstract: This invention concerns an engine fuel-oil heat exchange system for an engine (10) having a first fuel line (30) for delivery of fuel to an engine combustor (16) and a second fuel line (32) for delivery of fuel to ancillary engine equipment. The heat exchange system has a first heat exchanger (34) for transfer of heat from an engine oil system to the first fuel line (30) and a second heat exchanger (40) for transfer of heat from the engine oil system to the second fuel line (32). A control valve (46) is provided for selective control of the oil flow (48) from the engine oil system to the first (30) and second (32) heat exchangers. [FIG.

Abstract: A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc, the root being mounted in the slot by insertion of a leading end of the root into a proximal end of the slot and then sliding the root towards a distal end of the slot. The device includes a first wedging body having a key portion receivable in a keyway formed at the distal end of the slot. The keyway restrains the first wedging body against movement in the axial direction. The first wedging body further has a first angled surface over which a correspondingly angled leading end surface of the root slides when the root is inserted in the slot to urge the leading end of the root radially outwardly.

Abstract: A temperature and pressure probe (40) comprising an elongate outer tube (42) and elongate inner tube (56). Each tube having a peripheral wall (44, 58), a first open end (46, 60) and a second closed end (48, 62); the outer tube thereby defining an outer cavity (52) and the inner tube defining an inner cavity (66). The inner tube is located wholly within the outer cavity and is spaced from the outer peripheral wall (44) and second end (48). A temperature sensor (70) is located in the inner cavity. A pressure sensor (68) is located in the outer cavity. A vent pipe (76) is coupled between the inner peripheral wall and the outer peripheral wall, the vent pipe having a first end open to the inner cavity (66) and a second end open to vent outside the probe (40).

Abstract: An aircraft propulsion control system for an aircraft having a plurality of combustion engines is provided. The system has a plurality of sensors for sensing a condition indicative of properties and/or formation of vapor trails which may be formed by the plurality of engines. A controller is arranged to control one or more operational variable for each of the plurality of engines. The controller is arranged to undertake a search of trial values of the operational variable by instructing different concurrent values of said operational variable across the plurality of engines and determining the resulting impact on the vapor trail formation and/or properties as sensed by the sensors. A population-based search may be performed, for example in parallel over all the engines at once so as to reduce the time taken to achieve vapor trail mitigation.

Abstract: A rotor, for a compressor of a gas turbine, comprising a rotatable support for rotation about an axis of rotation and a plurality of blades. Each blade comprising a hub, a leading edge and a trailing edge and a chord is defined between the leading edge and the trailing edge. Each of the blades extends from its hub away from the rotatable support and at least one of the blades has a hub-thickness to chord ratio greater than 10 percent. The leading edge of the at least one of the blades at its hub is positioned at a leading-edge-hub-radius from a position of the axis of rotation and the trailing edge of the at least one of the blades is positioned at its hub at a trailing-edge-hub-radius from the position of the axis of rotation. The trailing-edge-hub-radius is greater than the leading-edge-hub-radius.

Abstract: A fixture having a foot clamp for clamping a foot of an aerofoil and a tip clamp for clamping a tip of the aerofoil is provided with an array of supports between the foot clamp and the tip clamp. Each support within the array is independently addressable to one of the aerofoil flanks when the aerofoil is secured to the fixture. The support is driven by pneumatics till it contacts the aerofoil when it is locked by an alternative mechanism.

Abstract: A joint assembly includes an end portion of a first component that is accommodated within an end portion of a second component, with each respective first and second end portion having a corresponding first and second location feature, and an elongate resilient helical connection member. When the joint is assembled, the first and second location features together define an annular cavity into which is accommodated the connection member to interlock the first and second components to one another.

Abstract: There is described a core for an investment casting process, comprising: a core passage which extends between a first point and a second point along a tortuous path having length L, wherein the first point and second point are separated by a direct line of sight distance, S, wherein L is greater than S; and, a core bridge which extends between the first and second points away from the core passage.