Abstract: There is disclosed a method of monitoring abrasion of a component during abrasive machining. The method comprises generating an acceleration signal corresponding to movement of the component or of an abrasive tool in response to abrasive machining of the component by the tool; generating an acoustic emission signal corresponding to acoustic waves emitted from within the component; and determining an abrasion parameter relating to the removal of material from the component based on a set of input variables including the acceleration signal and the acoustic emission signal. There is also disclosed an apparatus for abrasion monitoring and optionally abrasive machining, and a non-transitory machine readable storage medium comprising instructions for abrasion monitoring.

Abstract: A variable vane mechanism for adjusting the angle of stator vanes in a gas turbine engine is provided. The mechanism includes a circumferentially extending unison ring that is driven circumferentially around a casing by an actuator. The unison ring is connected to the stator vanes via levers such that the angle of the vanes changes with circumferential movement of the unison ring. The unison ring and the casing are each provided with at least one rigging hole in order to set the initial angle of the vanes. At least one of the unison ring and the casing are each provided with at least two rigging holes, so that the initial angle of the vanes can be adjusted by selecting different combinations of rigging holes. This may allow accumulations in tolerances to be compensated for and/or may allow the engine to be tested at different initial vane angles.

Abstract: Described is a planet carrier rotatable about a carrier axis, comprising: a planet pin for receiving a planet gear, the planet pin having a body with an external surface for receiving a planet gear bearing or planet gear; a carrier having a first axial wall and a second axial wall with the planet pin extending there between along a planet pin axis, wherein each carrier wall includes a planet pin retention feature located on radially inwards of the planet pin axis and engaged with a portion of the planet pin.

Abstract: Apparatus for insertion into a cavity of an object, the apparatus comprising: a first tube comprising a first end, a second end, a first cavity extending between the first end and the second end, and an aperture at the second end; a member positioned within the first cavity of the first tube and adjacent the aperture of the first tube, the member being configured to enable an action to be performed; a plug coupled to the second end of the first tube; and an actuator configured to move the first tube relative to the object between a first position in which the plug seals the member from the cavity of the object, and a second position in which the member is exposed to the cavity of the object.

Abstract: A method of processing data from a sensor, the method comprising: receiving first data; identifying an object by comparing the received first data with stored second data for a plurality of objects; determining a first processing strategy for one or more portions of the object in third data using the identification of the object, the third data being received from a sensor; and processing the determined one or more portions of the object in the third data using the determined first processing strategy.

Abstract: There is disclosed an axial flow machine (10) comprising an annular flow path (23); a stator ring (38) comprising a plurality of stators mounted at their radially outer ends and extending into the annular flow path (23); a non-rotating body (24) axially adjacent the stator ring (38); and an annular shroud (42) disposed between the radially inner end of the stator ring (38) and the body (24). The shroud (42) is supported on the stator ring (38) and moveable relative the body (24); and the shroud (42) cooperates with the body (24) to inhibit a flow through a clearance pathway (78) therebetween.

Abstract: An aircraft comprises at least first and second gas turbine engines arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine comprising at least one compressor or turbine rotor disc defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors of at least one of the engines is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine is nonintersecting with another engine.

Abstract: A joint assembly has first to third end portions of first to third components and an elongate resilient connection member. The first end portion interconnects with the second in a castellated arrangement. The first and second end portions have repeating arrays of first and second, and third and fourth connection portions. The first connection portion is received inward the third, and its first location feature being aligned with a third location feature of the third forming a first cavity portion, and the second connection portion axially distal surface abutting against that of the fourth, with a second location feature of the second connection portion being aligned with a fourth location feature of the fourth connection portion forming a second cavity portion. The first and second cavity portions are aligned forming an annular cavity, with the connection member being receivable within the annular cavity interlocking the first component to the second.

Abstract: A tile for attaching to a wall of a gas turbine engine. The tile has a main body. The tile also has a bridging structure that projects outwardly from the main body and has a hole configured to receive an elongate fastener so that the tile can be attached to the wall of the gas turbine engine by passing the elongate fastener through a hole in the wall of the gas turbine engine and the hole in the bridging structure.

Abstract: A sealing element for positioning radially outwardly of aerofoil blades of a gas turbine engine is provided. A radially inner surface region of the sealing element includes a seal structure having one or more inwardly projecting walls formed by additive layer, powder fed, laser weld deposition. The walls form a plurality of curved profile shapes which are arranged in a repeating pattern across the radially inner surface region. None of the walls intersects with any other wall. The curved profile shapes have no radii of curvature less than 0.5 mm.

Abstract: A double wall structured combustor having an outer wall having an inner surface and an outer surface and an inner wall comprising a plurality of tiles. Each tile has at least one interlocking member at a first wall and at least one interengaging member at a second wall. The interlocking member extending through an aperture in the outer wall, and the interengaging member at the second wall engaging with a cutaway section in the first wall of an adjacent tile. On assembly of the combustion chamber, the interlocking members and interengaging members of the tiles ensure lower profile fixings and an overall reduction in number of conventional fasteners used.

Abstract: A method of producing cooling apertures in a combustion chamber head includes mechanically drilling a plurality of cooling apertures through the combustion chamber head from the downstream side of the combustion chamber head. A tool is inserted through at least one aperture for a fuel injector from the downstream side of the combustion chamber head and the tool is rotated about its axis while within the aperture for a fuel injector. Fluid is supplied from the drilling machine through the tool and jets of fluid are directed from nozzles in the tool with at least a radial component towards the cooling apertures on the upstream side of the combustion chamber head to remove burrs and/or caps adjacent the cooling apertures. The present disclosure enables cooling apertures to be drilled through a combustion chamber head using conventional mechanical drilling in a viable and cost effective manner.

Abstract: There is provided a wireless communication system for a marine propulsor, comprising: a transmitter; a receiver; and a waveguide, arranged to convey an electromagnetic data signal between the transmitter and the receiver; wherein the waveguide comprises an electrically non-conductive solid or liquid medium for propagating the electromagnetic data signal.

Abstract: The present invention provides a method of manufacturing an abradable section to be formed on the interior of the casing of a gas turbine engine. The abradable section is formed by an additive manufacturing process to be of a lower density than the surrounding portions of the casing, but integrally formed with those portions. The abradable section thus formed can result in reduced blade fin tip wear, and may also have an improved performance. It may also have lower manufacturing costs. Formation of cooling passages in the abradable section is also easier and a wider range of designs of cooling passages can be provided. A gas turbine engine included such a casing is also provided.

Abstract: The valve includes a casing arrangeable so the fluid in the passage flows over an outer side. The valve includes a piston axially slidably positionable within the casing, and the axial position regulates the fluid pressure in the poppet valve passage downstream, an annular clearance between the piston and casing. The valve includes a dynamic seal between the piston and casing to seal the annular clearance end. The valve includes a piston chamber located on the dynamic seal opposing side of the annular clearance so a leakage flow may cross the dynamic seal between the annular clearance and piston chamber. The fluid pressure in the piston chamber varies the axial position within the casing. A diversion path formed in the casing diverts fluid for the leakage flow into the annular clearance from the fluid flow in the passage, the diversion path having filter to filter debris from the diverted fluid.

Abstract: Invention provides gear pump bearing block and method of manufacturing gear pump bearing block. Bearing block includes a bush formed of antifriction alloy, bush having cylindrical portion providing bore adapted to receive bearing shaft of gear of pump, and further having flange portion extending radially outwardly at end of cylindrical portion to provide thrust face adapted to slidingly engage with side surface of gear. Bearing block also has backing layer covering radially outer surface of cylindrical portion and rear face of flange portion, backing layer being formed of less dense alloy compared to antifriction alloy. Furthermore, there is an annular gallery embedded in flange portion such that gallery is spaced from surface of bore and from thrust face, gallery surrounding bore, with inlet to and outlet from annular gallery such that, in use, fluid flows from inlet, through annular gallery to provide cooling of thrust face, and then to outlet.

Abstract: The invention provides a gear pump bearing block and method of manufacturing gear pump bearing block. Bearing block includes bush formed of antifriction alloy, having a cylindrical portion providing bore adapted to receive bearing shaft of a gear of pump, and further having a flange portion extending radially outwardly at end of cylindrical portion to provide thrust face adapted to slidingly engage with side surface of gear. Bearing block also has backing layer covering radially outer surface of cylindrical portion and rear face of flange portion, backing layer being formed of relatively less dense alloy compared to antifriction alloy. Furthermore, there is an annular formation of one or more stiffening members, formation surrounding bore, the, or each, stiffening member being embedded in flange portion, and the, or each, stiffening member being formed of material having higher elastic modulus than antifriction alloy.

Abstract: Described is an oil distributor comprising: an oil distribution conduit having an inlet end and an outlet; an oil delivery arrangement at the outlet of the oil distribution conduit, the oil delivery arrangement including a circumferential channel having a base, an upstream wall and a downstream delivery wall, wherein the delivery wall includes a plurality of circumferentially distributed delivery apertures extending therethrough.

Abstract: The invention concerns an aircraft propulsion control system in which multiple gas turbine engines (10) are under the control of a controller (30). One or more sensor is arranged to sense a condition indicative of vapor trail formation by an exhaust flow from one or more of the engines. The controller (30) is arranged to be responsive to a thrust demand (51) for the aircraft and to control the thrust produced by each of the engines (10) concurrently so as to alter the efficiency of the engines upon sensing of the vapor trail formation condition, while satisfying the aircraft thrust demand. The controller (30) may output a separate throttle control signal (35) to each engine (10).

Abstract: An edge detector is provided for determining the axial position of the leading or trailing edge of a rotating blade within rotating machinery. The edge detector includes a set of axially spaced tip detection probes locatable within a casing of the machinery. Each probe is arranged to detect whether or not the blade tip passes over that probe. The edge detector determines the axial position of the edge of the blade as the position of the boundary between those tip detection probes which detect passage of the blade tip thereover and those tip detection probes which detect no passage of the blade tip thereover.