Abstract: A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element. The fan containment system further includes an annular fan track liner comprising a plurality of adjacent arcuate fan track liner panels. Each of the plurality of fan track liner panels is connected to the fan case at the hook via one or more fasteners configured to permit movement of the fan track liner panel relative to the hook such that the fan track liner panel can pivot towards the annular casing element when a released fan blade impacts the fan track liner panel.

Abstract: A fan containment system has a fan case having an annular casing element for encircling an array of fan blades and a hook projecting generally radially inwardly from the annular casing element. An annular fan track liner is positioned substantially coaxial to the annular casing element, and positioned such that a forward end of the fan track liner is axially spaced from the hook so that there is a gap between the hook and the fan track liner. A bridge member spans the gap between the hook and the fan track liner, wherein the bridge member is connected to the hook and contacts a radially inner surface of the forward end of the fan track liner. The bridge member fails when impacted by a fan blade released from a hub so that the released fan blade can impact the hook and be contained by the fan containment system.

Abstract: A gas turbine engine fan blade apparatus is disclosed comprising a reverse pitch rotatable mounting and an aerofoil part. The aerofoil part comprises radially inner and radially outer portions that are separated by an interface extending from a leading edge of the aerofoil part to a trailing edge of the aerofoil part. The reverse pitch rotatable mounting locates the radially inner and radially outer portions with respect to one another. The reverse pitch rotatable mounting and separation at the interface permit relative pitch change rotation between the radially inner and radially outer portions such that one of the radially inner and radially outer portions is rotatable to a reverse pitch configuration by comparison with the other portion.

Abstract: A method of manufacturing an induction motor rotor assembly, the method includes the steps of: providing a rotor; machining a plurality of re-entrant slots axially along an outer surface of the rotor; positioning a sleeve concentrically over the outer surface of the rotor; applying a friction stir welding process to the sleeve along each re-entrant slot axially along the outer surface of the rotor to cause the sleeve material to plasticise and flow into the axial re-entrant slot to form an axial re-entrant slot bar; and providing an electrical connection at each of the opposing axial ends of the rotor between respective ones of opposing ends of each of the axial re-entrant slot bars to thereby form the induction motor rotor.

Abstract: A rectifier diode failure detection apparatus for an electrical machine (10), the electrical machine (10) comprising an exciter armature winding (28a-c), a rotor main field winding (24) and first and second rectifiers (34a, 34b) arranged in parallel, each rectifier (34a, 34b) comprising at least first and second diodes (38a, 38b), each rectifier being configured to independently supply the rotor main field winding (24) with DC electrical current, the failure detection apparatus comprising: a controller (40) comprising at least two current sensors (42a, 42b), each current sensor (42a, 42b) being configured to measure output current (If1, If2) of a respective one of the rectifiers (34a, 34b), and the controller (40) being configured to determine a harmonic of the measured rectifier output currents; the controller (40) being further configured to determine a ratio of the magnitude of the first rectifier (34a) output current harmonic to the magnitude of the second rectifier (34b) output current harmonic, wherein

Abstract: A method of machining an object, the method comprising: receiving a signal from an ultrasonic transducer; determining at least a first external surface of the object and a second internal surface of the object in the received signal; determining a thickness between the first external surface and the second internal surface of the object, the object comprising a first material between the first external surface and the second internal surface, and a second material between the second internal surface and a third surface, the determination of the thickness using a database including a plurality of materials and a plurality of associated acoustic wave velocities; and controlling machining of the first external surface using the determined thickness.

Abstract: A method of manufacturing a gas turbine engine, the method including providing a fan having a plurality of fan blades circumscribed by a fan track liner and attaching a cutter to the fan track liner, the cutter is arranged towards the blades of the fan. The fan blades are rotated so that one or more of the fan blades are trimmed by the cutter. Once one or more of the fan blades have been trimmed by a desired amount, the cutter is removed from the fan track liner.

Abstract: A method for manufacturing a component having a defined geometry includes: a) defining a pre-component geometry including interim shape elements and additional, sacrificial elements for supporting interim elements; b) on a base plate, depositing multiple layers of a powder including a material from which the pre-component will be manufactured; c) sintering the powder to form the pre-component to the defined geometry; d) removing at least some of the sacrificial elements from the pre-component; e) subjecting the remaining pre-component from step d) to a HIP step; and f) removing remaining sacrificial elements from the pre-component product of step e) to provide a component to the defined component geometry. In the definition of the pre-component geometry, the interim elements differ from the corresponding final shape elements in the defined component geometry such that during the HIP step, the interim shape elements adjust to form final shape elements in the defined component geometry.

Abstract: A duct arrangement for an internal combustion engine comprises an exhaust duct, an inlet duct and a cooling air duct. The exhaust duct is contained within the cooling air duct for substantially its whole length and the cooling air duct is contained within the inlet duct for substantially its whole length, so that in use the cooling air duct provides a barrier to limit heat transfer between gas flowing in the exhaust duct and gas flowing in the inlet duct. The invention avoids the need for separate inlet and exhaust ducts with their attendant disadvantages. The separation of the inlet and exhaust ducts by the cooling air duct allows the inlet air to be kept as cool as possible, as is necessary for efficient engine operation.

Abstract: A rotary blade tip insert for incorporation into a rotary blade, for example, a rotary fan blade in a gas turbine engine. The tip insert comprises a sleeve for insertion into a recess provided in said rotary blade. The sleeve has a radially outer end defining an opening, a radially inner end and opposing wall portions extending between said ends. The tip insert further comprises a tip element having a crown portion and a root portion for insertion into the opening of said sleeve.

Abstract: A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibers extending in a generally radial direction and a plurality of second reinforcing fibers extending in generally axial and circumferential directions. The second fibers are interlaced with the first fibers so as to form a more unified and integrated structure, and to prevent the first reinforcing fibers from moving relative to one another.

Abstract: A robot for cleaning submersed marine structures is provided. The robot has a drive system for traversing the robot over the submersed structure. The robot further has an attachment system for attaching the robot to the submersed structure. The robot further has a cleaning arrangement for removing biofouling from the submersed structure as the robot is traversed thereover. The robot further has one or more flexible detector strips which contact the submersed structure as the robot is traversed thereover. The strips have a plurality of electrodes and are formed from electroactive polymer material which produces electrical signals in the electrodes on deflection of the strips. The signals are indicative of the surface roughness of the submersed structure.

Abstract: This invention concerns a support structure for releasably clamping onto a body relative to a central axis in use, wherein the support structure comprises a plurality of links connected at a plurality of pivots spaced about the axis and an array of contact members depending from the links at angularly spaced locations about the axis, whereby pivoting of the links causes actuation of the contact members in a substantially radial direction relative to the axis such that said contact members communicate an applied contact force about the body in use so as to clamp the support structure to the body via the array of contact members.

Abstract: Bearing apparatus comprising: an inner race; an outer race; a roller element positioned between the inner race and the outer race; a first sensor to sense displacement of one of: the inner race, the outer race, and the roller element, and to provide a first signal for the sensed displacement to enable a load on the bearing apparatus to be determined.

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 magnetizing 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: A gas turbine engine comprising a circumferential row of vanes directly upstream of an asymmetric gas flow path. At a given spanwise position the tangential and axial position of the vanes varies along the row of vanes.

Abstract: A friction welding apparatus has first and second clamps for respectively holding first and second parts to be welded by rotary friction welding, a device for producing relative rotation between the first and second clamps and a forge for applying an axial forging pressure to the parts to be welded when the parts are located in the clamps. The second clamp is mounted on a first half of a coupling. A second half of the coupling is movable axially between first and second positions. In the first position the second half of the coupling is engaged with the first half to prevent rotation of the second clamp and enable relative rotation between the first and second clamps. In the second position the second half of the coupling is disengaged from the first half to enable rotation of the second clamp and stop relative rotation between the first and second clamps.

Abstract: A gas turbine engine comprising in flow series: a fan; a series of outlet guide vanes; and a bifurcation. The outlet guide vanes are more densely distributed in a region circumferentially aligned with the bifurcation than in a region circumferentially offset from the bifurcation.

Abstract: A gas turbine engine comprising a fan, a bypass duct positioned downstream of the fan and defined by an inner casing and an outer casing, a series of outlet guide vanes arranged downstream of the fan, the outlet guide vanes extending between the inner casing and the outer casing of the bypass duct; and a bifurcation positioned downstream of the outlet guide vanes and extending between the inner casing and the outer casing. The bifurcation comprises a leading edge, and the leading edge of the bifurcation is shaped so as to protrude axially forward by a varying distance from the inner casing to the outer casing so as to improve uniformity of a static pressure field formed, in use, immediately upstream of the bifurcation.

Abstract: An apparatus for use in Ultrasonic testing, and a method of inspection or testing using the apparatus. The ultrasonic testing tool includes an elongate connector arranged between a transducer and a tip or contact head for contact with the component to be tested. The elongate connector carries soundwaves produced by the transducer between the transducer and the contact head.