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 continuum robot comprising: a first segment defining a first end and a second end, the first segment including a first actuator coupled to the second end and configured to control movement of the second end relative to the first end; and a first elastic strain sensor coupled to the first segment and positioned between the first end and the second end, the first elastic strain sensor being configured to provide a first output signal associated with the movement of the second end relative to the first end.

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 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 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.

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 gas turbine engine. The engine includes a first compressor coupled to a first turbine by a first shaft, the first turbine having first and second turbine stages. A first combustor is provided downstream of the first compressor and upstream of the first stage of the first turbine. A second combustor is provided downstream of the first stage of the first turbine, and upstream of the second stage of the first turbine. A further turbine is provided downstream of the first turbine, and is coupled to a further compressor by a further shaft.

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 mounting bracket for mounting an accessory to a gas turbine engine, the mounting bracket including a space frame structure. The space frame structure including a plurality of struts joined to one another at nodes.

Abstract: An abradable liner suitable for a gas turbine engine fan stage, comprising a plurality of abradable layers that are bonded together, wherein at least one visual indicator is embedded in the plurality of abradable layers, the visual indicators can be coloured strips of material and may be at a given depth, and may be in an independent element or layer located in between other layers.

Abstract: A gas turbine engine comprising a casing, a bonding patch (10, 22) bonded to a surface of the casing, and a liner attached to the bonding patch. The bonding patch (10, 22) comprising a bonding region (12) configured to receive an adhesive for bonding the patch (10, 22) to a surface. A plurality of de-bonding elements (16) is configured to be movable relative to the bonding region (12) in response to an energizing signal.

Abstract: A bolt which extends into the first casing part, into the hole in the barrel nut, and into the second casing part, wherein the bolt engages with the barrel nut so as to join the first casing part to the second casing part; wherein the barrel nut includes a first portion and a second portion, wherein the first portion of the barrel nut is structurally weaker than the second portion of the barrel nut such that, if a predetermined load between the first casing part and the second casing part is exceeded, the first portion of the barrel nut becomes crushed while the second portion of the barrel nut remains engaged with the bolt. The casing assembly may be included in a gas turbine engine.

Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The space to chord ratio of the aerodynamic vanes that are closest to the suction surface of a strut-vane is higher than the space to chord ratio of aerodynamic vanes that are closest to a pressure surface of the strut-vane. The arrangement allows the duct 100 to be axially short.

Abstract: A gas turbine engine (10) comprising: a low pressure turbine (19); a fan (13) drivable by the low pressure turbine. A high pressure turbine (18) and a high pressure compressor (16) coupled by a high pressure shaft (24). An epicyclic gearbox (14) in planetary configuration coupled between a low pressure shaft (23) and the fan. The engine having a bypass ratio greater than or equal to 13. Or the fan having a diameter greater than or equal to 85 inches and less than or equal to 170 inches. Or the engine arranged to generate thrust in the range 35,000 lbf to 130,000 lbf.

Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The arrangement allows the duct 100 to be axially short.

Abstract: An electrical connector arrangement comprises a metal mounting bracket for securing the arrangement to a structure; an electrically insulating mounting block abutting the mounting bracket; a clamp to secure an electrical cable to the mounting block, the electrical cable comprising a plurality of electrical conductors; and a plurality of spaced-apart terminals to accommodate the respective electrical conductors.

Abstract: A turbine blade includes a labyrinth of internal channels for the circulation of coolant received through an inlet formed in a terminal portion of the blade root and leading to a duct- defined wall. A first passage intersects the duct and extends through the blade towards a tip. An end of the first passage is arranged to capture incoming coolant flow. A second passage intersects the duct at a position downstream of the first passage intersection. The duct and/or the passage intersections are configured to create a pressure drop in the duct in the direction from the inlet to the second passage intersection. In an axial direction, a duct wall terminates at a position between the inlet and the second passage intersection to balance the pressure of coolant in the duct with the pressure of coolant in a leakage path thereby reducing the mass flow of coolant entering the leakage path.

Abstract: An ice thickness measurement sensor 100 is provided to measure the thickness of ice extending from a circuit. The ice thickness measurement sensor comprises at least one capacitive sensor 150. The capacitance of the sensor 150 depends on the thickness of ice covering the sensor, because the presence of the ice changes the permittivity. The ice thickness measurement sensor may be used in a fluid pipe, for example to measure the thickness of ice extending from the inner surface of the pipe.

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.