Abstract: A method of calibrating laser alignment for a direct laser deposition machine having a powder dispensing nozzle aligned with a laser source, comprises the steps of: (i) providing a test coupon; (ii) firing a powder pulse at the test coupon to create a first circular imprint; (iii) firing a laser beam pulse at the test coupon to create a second circular imprint; (iv) aligning a first template, comprising a first outline, with the second circular imprint; (v) positioning a second template, comprising a second outline, concentrically with the first template; (vi) imaging the test coupon to generate a first image; (vii) cropping the first image to the second outline to create a second image; (viii) determining an overlap area between the first circular imprint and the second outline; and (ix) generating an alert if the overlap area is less than a predetermined value.

Abstract: There is disclosed an access port for a casing of a gas turbine engine and a plug for plugging the access port. The access port and plug each include first and second baulking formations which are configured to engage with one another. The first and second baulking formations are spaced from one another by a unique angular separation which allows only the correct plug to be inserted into the correct access port.

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: A system includes a turbine engine having a fuel injector. The fuel injector includes fluid ducts, each having a fuel inlet coupled to a distinct fuel source. The system includes a compressed air source that provides compressed air simultaneously to the fluid ducts, and a convergence point where combined fuel and air streams from the ducts are mixed. The fuel inlets are in a parallel flow arrangement such that no fuel from one fuel injector is present at another fuel injector.

Abstract: A system includes an electric motor including a housing enclosing a substantially-sealed internal environment, a pump including an inlet connected to the substantially-sealed internal environment of the electric motor via a first conduit, and a fluid supply storing a makeup fluid, the fluid supply including an outlet connected to the substantially-sealed internal environment of the electric motor via a second conduit. The pump is configured to create a negative pressure within the substantially-sealed internal environment of the electric motor to mitigate potential contamination of an external environment of the electric motor with the makeup fluid.

Abstract: A gas turbine engine fan stand (40) comprising a base frame (42) and a fan case frame (44) coupled together at one edge by a hinge (46). The fan case frame (44) is arranged to: rotate about the hinge (46) between abutting the base frame (42) and substantially perpendicular thereto; and tilt about a yaw axis (52) perpendicular to the hinge (46) and in the plane of the fan case frame (44). The fan case frame (44) further comprising a coupling arrangement (56) arranged to rotate about a roll axis (60) and to couple a fan case (36) to the fan case frame (44). A gas turbine engine stand assembly (68) comprising a fan stand (40) and a core stand (38). A method of splitting a gas turbine engine (10) and a method of reassembling a gas turbine engine (10).

Abstract: A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.

Abstract: There is disclosed a method for spatiotemporal registration between a first image stream and a second image stream. A first registration frame set derived from the first image stream and a second registration frame set derived from the second image stream are defined. A spatial correlation analysis is conducted based on the first registration frame set and the second registration frame set to determine a spatial registration offset. The first registration frame set and the second registration frame set are spatially registered based on the spatial registration offset. A temporal correlation analysis is conducted based on the first registration frame set and the second registration frame set after spatial registration to determine a temporal registration offset. The first image stream and the second image stream are spatially and temporally registered based on the spatial registration offset and the temporal registration offset.

Abstract: An electrical fault detector is shown for installation in electrical network (101) of the type comprising a first voltage source (104) and a second voltage source (107), each of which have a respective positive rail (105,108) connected by a positive concentrator (110) and a respective negative rail (106,109) connected by a negative concentrator (111). The detector comprises an inductor (112) for location in one of: the positive concentrator between the connections of the positive rails thereto, and the negative concentrator between the connections of the negative rails to thereto. The detector also comprises a fault identification device (113) configured to monitor the voltage across the inductor, and generate a fault signal in response to the voltage across the inductor exceeding a threshold.

Abstract: A gas turbine engine comprises a plurality of variable guide vanes, a unison ring, and a lever arrangement connecting the unison ring to the variable guide vanes. The lever arrangement comprises a lever pin received by the unison ring, and a bush provided between the lever pin and the unison ring. The bush comprises a sprung region biased outwardly away from the lever pin towards the unison ring.

Abstract: An aircraft propulsion system (10) comprises at least first and second electrical generators (15a, 15b), each being configured to provide electrical power to a respective first and second AC electrical network (16a, 16b). The system (10) further comprises at least first and second AC electrical motors (19a, 19b) directly electrically coupled to a respective AC network (16a, 16b) and coupled to a respective propulsor (4), and a DC electrical network electrically coupled to the first and second AC networks (16a, 16b) via respective first and second AC to DC converters (17a, 17b), and to a further electrical motor 19c), the further electrical motor (19c) being coupled to a propulsor (4).

Abstract: A distributor device for distributing cooling air within a gas turbine engine, the device including a base mountable adjacent an inlet for air to be distributed; and a deflector supported by the base and in fluid communication with the air inlet, the deflector being configured to direct air from the air inlet in a plurality of directions within the engine; wherein the deflector includes one or more deflecting surfaces curvilinearly configured to direct the air differentially in a plurality of desired directions within the engine. In embodiments the deflecting surface(s) is/are curved and are so configured such that air from the air inlet is directable either: (i) in directions of travel in each of a plurality of desired different, non-parallel directions within the engine; or (ii) in each of a plurality of desired different directions within the engine with different flow rates.

Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.

Abstract: The invention is a method that combines the following components: a high pass filter designed to have sufficiently small phase delay and roll-off value in transition band as well as sufficiently good attenuation; a distortion detection and reconstruction introduced by the application of the high pass filter by extraction the significant frequency components in relevant frequency band; a signal compensation that reshapes the output of the high pass filter by matching the filter's phase delay and attenuation characteristics so as to approximate low frequency component extraction that would be produced by an ideal filter (very sharp frequency transition and no delay); a time-domain detection and correction method that addresses special circumstances under which the compensation would be inaccurate to achieve real-time estimate in normal circumstances, and a time-domain correction method during and immediately after sudden changes in composite signal (spike) is detected.

Abstract: A variable speed drive arrangement including: a load; a gearbox to supply mechanical drive to the load; a converter electrically coupled with a power grid. Also a primary electrical machine to supply mechanical power to the gearbox and to receive electrical power; and a secondary electrical machine mechanically coupled to the gearbox and electrically coupled to the converter. An electrical circuit breaker to selectively electrically couple the primary electrical machine to the secondary electrical machine or to the power grid; wherein the secondary electrical machine is adapted to supply or extract mechanical energy from the gearbox and to receive or deliver electrical energy to the converter. Also a control method for the arrangement including a starting mode and a running mode.

Abstract: A method of manufacturing a component from a nickel-based superalloy comprises the steps of: providing a vacuum induction casting furnace; positioning a component mould onto a chill plate within the furnace; casting a component blank; peening the surface of the component blank; applying a surface modification technique to the surface of the component blank; solution heat treating the component blank at or above the ??-solvus temperature for the superalloy; and precipitation heat treating the component blank.

Abstract: An articulating coupling assembly for coupling a pipe end to a support structure, the assembly including: a pipe end fitting configured for fitting onto a free end of a pipe; a spherical bearing which is part of said pipe end fitting, the spherical bearing having a maximum diameter not greater than that of the pipe end fitting; a flanged collar configured to receive the pipe end fitting in a snug fit; a radially outer wall of the spherical bearing having one or more slots extending along the bearing in a direction parallel to the axial direction of said pipe; and a radially inner wall of the flanged collar having one or more radially inwardly protruding dogs proportioned to be received snugly in the one or more slots of the radially outer wall of the spherical bearing.

Abstract: A method of controlling a rotor tip clearance in a gas turbine engine (10). The method comprises determining an engine or component remaining useful life Tr, and controlling a tip clearance control arrangement (38) to maintain a rotor tip clearance (36) at a target tip clearance Dtarget. The target tip clearance Dtarget is determined in accordance with a function of remaining engine life Tr.

Abstract: A method for designing a baffle including using patterns to produce an array of shell moulds, generating a 3-D image of the outer surface of each shell mould in the array of shell moulds, stacking the individual 3-D images for a plurality of the shell moulds to produce a conglomerate shell mould profile, determining a maximum cross sectional area of the conglomerate shell mould profile in a plane orthogonal to a direction along which the shell moulds are to be drawn through the baffle, defining a baffle profile segment which is consistent with a substantial portion of the conglomerate shell mould profile at the maximum cross sectional area, scaling the baffle profile segment to provide an offset clearance between the baffle profile segment and the maximum cross sectional area of the conglomerate shell mould profile, and reproducing the baffle profile segment to provide an array of baffle profile segments.

Abstract: Air-riding seal arrangement between two components are rotatable relative to each other about a rotation axis. The seal arrangement includes an axially slidable carrier module mounted to one component and runner provided by other components. The carrier module and runner have respective and opposing annular sealing faces in a seal arrangement normal operation are axially spaced to form an air-seal therebetween separating a high-pressure region at one side of the air-seal from low-pressure region at the other side. The carrier module has a front and rear portions, and carrier module sealing face is provided by the front portion. The front portion has first and second rotation positions relative to the rear portion, the first rotation position being in normal operation, and second rotation position being in event of high speed touchdown of the annular sealing faces when contact between sealing faces rotates the front portion to the second rotation position.