Abstract: A gas turbine engine includes a fan, a fan shaft that rotationally support the fan, a first bearing that rotationally support the fan shaft and a support arrangement configured to support the first bearing. The support arrangement includes a first support member coupled to first bearing and to a mechanical ground to define a first load path, and a second support member coupled to the mechanical ground and first bearing to define a second load path. The second support member is coupled to one of the first bearing and mechanical ground by a first frangible link. A load extends between the bearing and mechanical ground through the first and second loads paths, and in the event of a predetermined radial load being applied to first bearing, the frangible link breaks such that the load extends between the first bearing and the mechanical ground through first but not second load path.

Abstract: There is described an inspection device for inspecting a slot of a gas turbine engine. The inspection device comprises: an insert for insertion into the slot; a plurality of imaging devices coupled to the insert; and a processor. The insert is movable along a longitudinal axis of the slot. Each of the plurality of imaging devices is positioned adjacent an external surface of the insert and is configured to capture an image of a portion of the slot adjacent the imaging device. The processor is configured to receive data corresponding to the images captured by the plurality of imaging devices. There is also described a method of inspecting a slot using the inspection device.

Abstract: A method of manufacture of an article or component comprising: providing an intermediate article or component comprising, or consisting essentially of, a precipitation strengthened alloy; and treating the intermediate article or component in accordance with a predetermined heat treatment schedule comprising: a solution treatment step (2), wherein the intermediate article is held at a solution temperature for a first predetermined period of time, the solution temperature being above a ?? solvus temperature (7) and below a solidus temperature (6) for the precipitation strengthened alloy; and a first cooling step (3), wherein the intermediate article is cooled at a first cooling rate of up to 20° C. per minute from the solution temperature to an aging temperature, the aging temperature being below the ?? solvus temperature (7) for the precipitation strengthened alloy.

Abstract: An apparatus for machining an object includes a wheel having a first circular surface, a second circular surface oriented parallel to the first circular surface, a first rim surface extending from the first circular surface at a first edge, and a second rim surface extending from the second circular surface at a second edge and towards the first rim surface. A gradient of the first rim surface has a radial component, and a gradient of the second rim surface has a radial component. The first edge defines a curved surface between the first circular surface and the first rim surface, and the second edge defines a curved surface between the second circular surface and the second rim surface.

Abstract: A variable geometry exhaust nozzle arrangement includes a plurality of hingable exhaust petals defining a perimeter of an exhaust duct and an annular ring slidably engagable against a radially outer surface of each petal. The annular ring is coupled to a plurality of circumferentially spaced actuator arrangements, each including first and second circumferentially spaced parallel actuator arms pivotably coupled to the annular ring at a first end and to a slide arrangement at a second end. Each slide arrangement is mounted for linear sliding movement relative to the annular ring, such that sliding movement of each slide arrangement causes pivoting of the first and second actuator arms to thereby translate the annular ring in one or both of a longitudinal direction and a lateral direction.

Abstract: A rotor stage (100) of a gas turbine engine (10) comprises a platform (120) from which rotor blades extend. The platform is provided with a circumferentially extending damper ring (200), the damper ring having an engagement surface (210) that engages with a platform engagement surface (110) of the platform (120). The platform engagement surface (110) and the damper engagement surface (210) can move relative to each other in the radial direction. In use, the damper engagement surface (210) moves less in the radial direction than the platform engagement surface (110) in response to diametral mode excitation. This causes friction between the two surfaces, thereby dissipating energy and damping the excitation.

Abstract: A workpiece for use with a flash producing welding process comprises a revolute body, a plurality of first attachment portions, a plurality of second attachment portions. The revolute body has an axis of rotation. Each of the first attachment portions has a first radially outer weld joint surface, and each of the second attachment portions has a second radially outer weld joint surface. The revolute body comprises a plurality of first and second stub portions, with each of the first stub portions having a first radially inner weld joint surface, and each of the second stub portions having a second radially inner weld joint surface.

Abstract: A composite component comprising a plurality of plies. A first set of pins extend in a direction transverse to the plies and a second set of pins extend in a direction transverse to the plies. The pins of the first set are made of a different material to the pins of the second set.

Abstract: A turbofan engine driveshaft comprises, in axial sequence along an axial centreline, a driving portion, and a driven portion. The driving portion has a first end and a second end. The second end of driving portion is connected to the driven portion. The driven portion comprises an annular drum having a radially inwardly facing surface, with the annular drum having a stiffener attached to the radially inwardly facing surface. The driveshaft is supported radially by a bearing assembly at the connection between the driving portion and the driven portion. The driving portion is configured to accommodate a predetermined range of movement of the outer end relative to the inner end.

Abstract: A method of manufacturing a cable harness may comprise the steps of providing a plurality of cables, wherein each cable comprises a cable inner and a coating, wherein each cable inner comprises at least one conductor, locating at least a portion of each of the plurality of cables within a mould tool, heating the portions of each of the plurality of cables such that the coating of each cable consolidates to form a common harness with a solid cross section, wherein the cable inners are arranged within the common harness.

Abstract: A coated substrate comprising a metal or metal alloy such as a high speed steel, TiAl based alloy or Ni based alloy or an electrically conductive ceramic material, wherein the coating comprises a hard material protective coating comprising alternating layers of different compositions, wherein a first composition of the alternating layers comprises silicon, Si, and/or a second composition of the alternating layers comprises boron, B.

Abstract: An air swirler arrangement comprises a coaxial arrangement of an inner and an outer air swirler passage. Each air swirler passage comprises a radial flow swirler. Air swirler arrangement comprises a coaxial arrangement of first, second and third members. Second member has radially extending upstream portion spaced axially from first member and a convergent portion. Third member has a radially extending upstream portion spaced axially from the upstream portion of second member and a radially inner surface having convergent and divergent downstream portions and a radially outer surface having a divergent downstream portion. First, second and third members the vanes of the radial flow swirlers is a monolithic structure. Plurality of circumferentially spaced passages are provided within the third member and each passage has an inlet in the surface and an outlet arranged to direct fluid onto the divergent portion of the surface or the surface of the third member.

Abstract: A method of manufacturing a valve or an element used to form a valve, the method comprising forming a first part of a first component using additive manufacturing, adding a second component to the first part of the first component and forming a second part of the first component using additive manufacturing.

Abstract: A nozzle for a fuel injector of a gas turbine engine, the nozzle having an insulating air gap adjacent a conduit for carrying fuel, the air gap formed between a pair of concentrically arranged annular walls, wherein the pair of annular walls are arranged to move independently to accommodate differential thermal expansion, the nozzle further including: a channel extending circumferentially around a surface a first of the pair of annular walls, facing a second of the pair of annular walls; and a sealing member received in the channel, to close the insulating gap.

Abstract: A method to determine a fatigue limit for a material. Form a test component including the material. Identify a resonant frequency of the component and an excitation frequency which causes the component to vibrate. Measure a response parameter of the component when excited at the excitation frequency. Test the component to determine its fatigue limit by sub-steps to: apply an excitation force to the component at the excitation frequency to cause vibration of the component; alter the applied excitation force at constant excitation frequency to maintain the response parameter constant; measure at least one of an input parameter and an output parameter; iterate the sub-steps to alter and measure until the first order, second order, or first and second order derivatives of the input parameter and/or output parameter exhibit a discontinuity. Repeat the steps for a different excitation frequency. The fatigue limit for the material includes all the identified discontinuities.

Abstract: The present application discloses a fuel system for a gas turbine engine. The engine includes a main alternating current electrical generator driven by an engine shaft such that the electrical output frequency of the electrical generator varies in dependence on shaft rotational speed. The fuel system includes a variable flow fuel pump for providing a fuel flow to the engine, a frequency and/or voltage controller configured to provide electrical power having at least one of a predetermined output frequency and a predetermined voltage, and a variable speed electric motor configured to drive the fuel pump. The electric motor includes an induction motor having a stator and at least a first rotor, the stator having first and second sets of stator windings. Each set of stator windings is configured to impart a torque on the rotor in use.

Abstract: A method of manufacturing a gas turbine engine including designing a row of vanes provided upstream of an asymmetric gas flow volume. The method includes two dimensionally optimizing camberline and stagger angle of each vane, including using orthogonal polynomials to modify the camberline and stagger angle of each vane.

Abstract: Methods of cleaning internal portions of additively manufactured components are provided, together with an apparatus for carrying out the cleaning. The methods use an impacting element which is contained within the internal portion and the component is vibrated to clean material from the component and leave one or more hollow portions. Various embodiments for retaining the impacting element are set out, which preferably use a grid which allows loosened powder to fall out of the component and, optionally, be recycled for use in further manufacturing processes. The methods are described in relation to components for gas turbine engines but have wider application in relation to any additively manufactured component in which it is desired to have a hollow internal portion.

Abstract: A ring gear arrangement, including: a ring gear mount including: a ring gear having at least one internal gear for interaction with one or more gear wheels; a ring gear stator; and, a plurality of couplings which locate the ring gear within the gear stator, each coupling having a drive arm connected to the ring gear and a resiliently deformable connection, wherein the drive arm is movable between a first position in which the ring gear is in a rest position and a second position in which the ring gear has undergone some radial or rotational movement relative to the ring gear stator, wherein movement of the drive arm from a the first position to the second position loads the resiliently deformable connection against the ring gear, wherein the resiliently deformable connection biases the drive arm to return to the first position when in the second position.

Abstract: There is disclosed a method of manufacturing a component. The method comprises generating, by additive manufacture, an intermediate structure comprising a core corresponding to the component, and one or more excess portions to be removed and comprises machining the intermediate structure to remove the excess portions. The core is generated by a first additive manufacturing procedure and the one or more excess portions are generated by a second additive manufacturing procedure. The second additive manufacturing procedure differs from the first additive manufacture so that the excess portions are fused at a higher rate than the core.