Abstract: A transfer coupling includes a static component and a rotatable component arranged concentrically, the static component including a first number of radially extending ports and the rotatable component having a second number of radially extending ports the radially extending ports arranged in a common circumferential plane wherein the ports are configured and arranged, in use, to homogenize a flow area for a fluid being transferred through the ports and thereby create a homogenous volume flow.

Abstract: A pressure relief arrangement for a gas turbine engine comprises a hinged door and a mount spaced from the door. An expandable structure is connected to the door and to the mount such that when the door hinges open the expandable structure expands.

Abstract: A permanent magnet electrical machine (30) comprising a first shaft having a rotational axis (34). A second shaft spaced from the first shaft and rotating about the rotational axis. The second shaft comprises magnetic material. A first magnet mounted to the first shaft or aligned with the first shaft to selectively magnetise at least a portion of the first shaft. A second magnet aligned with the second shaft to selectively magnetise at least a portion of the second shaft and thereby to couple the second shaft to the first shaft.

Abstract: A method of manufacturing a component comprising forming an identifier internally within the component in a predetermined manner, wherein the identifier can be used to subsequently identify or authenticate the component.

Abstract: A method of manufacturing a component comprises forming a body of the component using additive layer manufacturing. During formation of the body, layers of the material are arranged so that the body has a surface roughness greater than or equal to 100 ?m. The method further comprises coating the body with a coating.

Abstract: An aircraft gas turbine engine comprises a high pressure compressor coupled to a high pressure turbine by a high pressure shaft, and a low pressure compressor coupled to a low pressure turbine by a low pressure shaft. The engine includes a first shaft bearing configured to support a forward end of the low pressure shaft, the first shaft bearing being mounted to a static structure forward of the high pressure turbine. The engine also includes a second shaft bearing configured to support a rearward end of the low pressure shaft, the second shaft bearing being mounted to a static structure rearward of the high pressure turbine, and forward of the low pressure turbine. The engine further includes a third shaft bearing configured to support the low pressure shaft, the third shaft bearing being mounted to a static structure rearward of the low pressure turbine.

Abstract: An additive layer manufacturing apparatus comprising a doctor blade (57) having a tip (51) which, in use, is arranged proximal to a material layer (59) to be recoated during an additive layer manufacturing method, the doctor blade (57) having a cavity (50) with an inlet and an outlet, the outlet located at the tip (51) and the inlet connectable to an air supply (53) whereby air can be directed through the cavity (50) to the outlet and onto a surface (59a) of the material layer (59).

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: Investment casting of an engine part using a pair of core members having respective opposed faces spaced apart by a first distance, a face of a first core member of the pair being provided with one or more protrusions thereon and a face of the second core member of the pair being provided with one or more respective open recesses therein, each protrusion facing a respective open recess, wherein during a casting procedure the first and second core members are maintained positioned relative to each other so major portions of the opposed faces of the first and second core members assume mutual spacing equaling a corresponding predetermined thickness of a portion of a resulting cast wall of the first distance; and at least a head portion of the protrusion is located within the respective open recess to define a minor portion of the resulting cast wall.

Abstract: An electrical machine is disclosed comprising a stator cavity. The stator cavity is axially divided by a distribution plate into a winding chamber containing stator windings of the electrical machine and a handling chamber. The handling chamber has one of a fluid inlet and a fluid outlet and the winding chamber has the other of the fluid inlet and fluid outlet. In use fluid is passed from the fluid inlet to the fluid outlet via the handling chamber, the winding chamber and an array of fluid passages in the distribution plate providing fluid communication between the handling chamber and winding chamber. The array of fluid passages comprises passages of at least two different cross-sectional areas.

Abstract: A method is provided of forming a neural network for detecting surface defects in aircraft engine components. The method includes: providing (i) a pre-trained deep learning network and (ii) a learning machine network; providing a set of pixelated training images of aircraft engine components exhibiting examples of different classes of surface defect; training the trainable weights of the learning machine network on the set of training images.

Abstract: Apparatus for enabling determination of a shape of at least a portion of a continuum robot, the apparatus comprising: a flexible cover defining a first end, a second end opposite to the first end, and a cavity for receiving at least a portion of a continuum robot therein; and a first elastic strain sensor coupled to the flexible cover and being configured to provide a first output signal associated with movement of the flexible cover.

Abstract: Described is a shaft support system for a gas turbine engine comprising: a rotatable fan shaft; first and second support structures extending in parallel from the shaft to a load bearing structure to provide radial location of the shaft within an engine casing, wherein the first support and second support structures include first and second respective mechanical fusible joints; wherein the first fusible joint is a two-stage fuse which partially fails within a first predetermined load range, the second fusible joint fails within a second predetermined load range which is different to the first load range, and the first fusible joint fully fails only when the second fusible joint has failed.

Abstract: An axial flux electrical machine comprises a first flux generating assembly, a second flux generating assembly, a shaft and a speed controller. The shaft has an axis of rotation. Each of the first flux generating assembly and the second flux generating assembly is rotationally located on the shaft in axial juxtaposition to one another, with the first flux generating assembly being axially separated from the second flux generating assembly by a separation distance. The speed controller is configured to modify a magnetic field generated by either of the first flux generating assembly and the second flux generating assembly so as to control a rotational speed of the electrical machine.

Abstract: A fluid system comprising a surface that is fluid washed in use by a fluid flow travelling substantially parallel to the surface is disclosed. The system has a first port through the surface and a second port through the surface, the first and second ports having respective first and second port inlets that are substantially flush with the fluid washed surface. The first and second port inlets are stacked in a direction parallel to the normal flow of fluid over the fluid washed surface such that the first port is upstream of the second port and fluid travelling closer to the fluid-washed surface entering into the first port tends to entrain fluid travelling further from the fluid-washed surface for entry into the second port.

Abstract: A fuel injector for a lean direct injection fuel nozzle has a pilot air swirler which sits radially outboard of a pilot fuel swirler radially outer wall. The air swirler is bounded on its radially outer side by joined wall portions. One wall portion extends axially and another wall portion converges radially. On the radially inwardly facing surface, the wall portions meet to provide a continuing wall surface of the air swirler which transitions from axial extension to radial convergence over a smooth radius. The curvature of this surface broadly mirrors the radially outwardly facing profile of the pilot fuel swirler radially outer wall. The axially extending wall portion is extended axially to form a first part of a join interface. The radially converging portion is extended in a radial direction to provide a second part of the join interface.

Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).

Abstract: A controlled collapse stub shaft allows controlled axial-movement of a mainline shaft joining a fan or compressor to a turbine. A first end of the stub shaft is joined to the mainline shaft. A second end of the stub shaft is joined to an engine part axially stationary relative to the mainline shaft controlled axial-movement. The stub shaft has an annular-body between first and second ends. The body contains plurality of axially-spaced circumferential rows of circumferentially-extending slots, inter-slot ligaments formed between each row slots. Successive rows are offset. The ligaments of the axially forwardmost and rearwardmost rows excepted, each ligament sandwiched between forward and rearward slots of neighbouring rows. Each ligament joined to adjacent ligaments of neighbouring rows by circumferentially-extending bars having thickness in axial direction corresponding to axial spacing between rows.

Abstract: A decision aid system for a vessel belonging to a plurality of vessels in data communication with a remotely located control hub comprises: associated with each of the plurality of vessels, a sub-system comprising one or more sensors for monitoring the local environment of the vessel, a node processor for processing data collected by the one or more sensors and a data storage device; and a controller located remotely from the node processors and in two-way data communication with each of the node processors. Each data storage device maintains an historic record of vessel states recorded by the one or more sensors, corresponding control actions taken in response to those vessel states and the ensuing vessel states resulting from those control actions.

Abstract: A system for generating a map for use in the navigation of one or more vessels includes: one or more sensor sub-systems provided on a vessel and configured for sensing, in real-time, the presence of obstacles within a local environment of the vessel; a processor associated with the one or more sensor sub-systems for collecting the sensor data and configured for generating therefrom, in a serialised digital format, a real-time map of the local environment surrounding the vessel; data communication means between the processor and a remotely located hub in data communication with remote sensing systems located remotely from the vessel. The hub is configured to collect sensor data from a source remote from the vessel and communicate the sensor data to the processor. The processor is configured on receipt of additional sensor data to generate a real-time map from the sensor data.