Abstract: An automated welding apparatus and computer-implemented method are described which generally perform the steps of: scanning a joint interface of a workpiece using a three-dimensional scanner (S4); determining a volume to be filled by a welding process (S6); determining a specification for the welding process based on the volume to be filled using an algorithm (S8, S10); and controlling a welding device so as to execute the specification by moving the welding device relative to the workpiece (S12).

Abstract: A fan casing assembly comprising an annular casing member for circumferentially surrounding a fan, and an annular fan track liner comprising a plurality of circumferentially adjacent liner panels. The annular fan track liner is positioned radially inward of the annular casing member. A tilting arrangement is provided and configured to selectively circumferentially tilt one or more of the liner panels, such that, in the event of a fan blade being released from a fan, the tilting arrangement can initiate tilting of one or more liner panels so that the liner panels can trim one or more of the remaining fan blades.

Abstract: A gas turbine engine includes a gearbox including a sun gear, annulus gear, plurality of planet gears and a planet gear carrier. Each planet gear is rotatably mounted in the planet gear carrier by a planet gear bearing. A lubrication system is arranged to supply lubricant to the planet gear bearings and at least one of the sun gear, the planet gears and the annulus gears. The planet gear carrier includes an annular extension. The lubrication system includes an annular member arranged around annular extension to define an annular chamber which is sealed at its ends to the planet gear carrier and which contains a reserve of lubricant. The annular member has an inlet to supply lubricant into the annular chamber and the planet carrier has a first passage to supply lubricant to the sun, planet or annulus gear and a second passage to supply lubricant to planet gear bearings.

Abstract: A component for the turbine of a gas turbine engine is provided. The component two facing walls interconnected by one or more generally elongate divider members to partially define side-by-side, generally elongate, cooling fluid passage portions which form a multi-pass cooling passage within the component. The passage portions are connected in series fluid flow relationship by respective bends formed by joined ends of neighbouring of the passage portions. The component further includes one or more core tie linking passages formed in the divider members. One or more differential pressure reducing arrangements are formed in the multi-pass cooling passage adjacent respective of the core tie linking passages.

Abstract: A rigid electrical panel has both a flexible printed circuit and an electrically conductive grounding layer embedded therein. The electrically conductive grounding layer is electrically connected to a grounding insert which is also embedded in the rigid material. The grounding insert has a base portion and an exposed portion. The electrically conductive grounding layer is connected to the base portion, and the exposed portion allows the grounding insert, and thus the electrically conductive grounding layer, to be electrically connected to a grounding point, for example on a gas turbine engine.

Abstract: An internally cooled gas turbine engine component has a line of cooling air discharge holes, an internal cooling channel, an internal feed cavity for feeding cooling air from the channel to the discharge holes, and flow disrupting pedestals arranged in rows. A method of configuring the component includes: determining angles ? and ? of the directions of cooling air flow into the first and Nth rows, respectively; defining a change in angle ? of the direction of cooling air flow between rows as ?=(???)/N; and positioning the pedestals such that a line extending forward from the center of each pedestal in the ith row at an angle {?+?(i?1)} intersects the (i?1)th row at a location which is midway between two neighboring pedestals of the (i?1)th row, i being an integer from 2 to N.

Abstract: A fuel system (12) comprising a vapor trail detection sensor (20) configured to generate a first signal (28) which indicates the optical depth of a vapor trail (35). A control unit (40) is provided responsive to the first signal (28) and configured to generate a second signal (80) in dependence upon the first signal (28). The second signal (80) defines a percentage of at least one of a first fuel composition and second fuel composition required to produce a resultant fuel composition. At least one regulator (42) is provided configured to receive and be responsive to the second signal (80) and regulate the percentage of first and second fuel composition required to produce the resultant fuel composition.

Abstract: A combustion chamber comprises an outer wall and an inner wall spaced from the outer wall. The outer wall has at least one mounting aperture extending there-through and the inner wall has threaded studs extending there-from. The threaded studs extend through the mounting apertures in the outer wall. Cooperating nuts locate on the studs and washers are positioned between the outer wall and the cooperating nuts. Each washer has a rim and a bore. The washers have one or more passages extending there-through from the rim to the bore of the washer to provide a flow of coolant through the passages in the washers, the mounting apertures in the outer wall and around the threaded studs to cool the threaded studs to increase the working life of the inner wall. Other cooling arrangements for the threaded studs are disclosed.

Abstract: An aircraft propulsion system includes at least first and second propulsor arrangements. Each propulsor arrangement includes an internal combustion engine configured to mechanically drive a plurality of propulsors. At least one of the propulsors of each propulsor arrangement is driveable via a shaft and at least one reduction gearbox. Each internal combustion engine is coupled to a motor generator arrangement configured to drive at least one of the mechanically driven propulsors when in a motor mode, and to generate electrical power when in a generating mode. The system further includes an electrical interconnector configured to transfer electrical power between the first and second propulsor arrangements.

Abstract: A method for the manufacture of a component having an internal cavity is described. The method comprises; defining an external geometry of the component, defining a core geometry of the component; and using an additive layer manufacturing (ALM) method, building the component from a plurality of layers laid on a first plane. The core geometry is advantageously designed to suit manufacture of the component using an ALM method which involves local melting of powder in a powder bed to form the layers, permitting easy removal of excess powder from the internal cavity.

Abstract: The present invention provides a gas turbine engine comprising a tubular containment casing surrounding a rotary fan blade assembly. The radially outer perimeter (and optionally the radially inner perimeter) of the radial cross-sectional profile of the containment casing is non-circular e.g. polygonal, corrugated, fluted or wavy.

Abstract: A control system for a machine comprising a plurality of independently replaceable machine modules comprises a controller operable to control operation of the machine. Memory stores machine data for use by the controller. Communication means are operable to provide communication for data transfer between the controller and the memory. The memory includes a plurality of memory modules associated with respective machine modules. Each of the memory modules is replaceable with the respective associated machine module and independently of other memory modules. The communication means is operable to provide communication for data transfer between the controller and a replacement memory module associated with a replacement machine module.

Abstract: An example system includes at least one acoustic sensor configured to generate at least one acoustic data signal indicative of an acoustic signal generated by a thermal spray system comprising a flowstream, a computing device, and an acoustic data signal processing module operable by the computing device to determine an ignition attribute of the thermal spray system by analyzing at least a pre-ignition window of the acoustic data signal received by the computing device.

Abstract: An actuation arrangement for effecting actuation of pivotable vane, for example, variable inlet guide vane in gas turbine engine. The actuation arrangement includes an actuator having a support plate and pivotable plate. The pivotable plate is fixedly connected to pivotable vane and pivotable plate and pivotable vane are pivotable about a pivot axis. The actuator further includes at least one actuation element having a length extending from support plate to proximal a transverse edge portion of pivotable plate substantially perpendicular to pivot axis. The or each actuation element is fixedly connected to each of the support and pivotable plates and formed of a material that changes dimension upon application of external energy. Thus, upon application of external energy, for example, heat, a change in length of the or each actuation element occurs such that change in length effects pivoting of pivotable plate and pivotable vane about the pivot axis.

Abstract: A method for electrical discharge machining a workpiece includes the steps of: presenting an elongate electrode to the workpiece with a spark gap therebetween; flowing a dielectric fluid in the gap; eroding the workpiece by electrical discharge between the tip of the electrode and the workpiece; displacing the electrode in a direction aligned with the long axis of the electrode to maintain the gap as the electrode wears and the workpiece is eroded; and simultaneously with the displacement, producing vibratory movement of the electrode, the vibratory movement being aligned with the long axis of the electrode.

Abstract: A fuel nozzle for a gas turbine engine is disclosed which includes a nozzle body having a longitudinal axis, an elongated annular air passage defined within the nozzle body, and a plurality of circumferentially spaced apart axially extending swirl vanes disposed within the annular air passage, wherein each swirl vane has multiple joined leads and a variable thickness along the axial extent thereof.

Abstract: A handheld tool facilitates the removal of an aerofoil from an array of aerofoils for an axial flow machine includes a body portion, and first and second jaw members depending from the body portion. The first jaw member is shaped to be insertable between a first aerofoil and an adjacent aerofoil in the array so as to contact a first surface of the first aerofoil. The position of the first and/or second jaw member is adjustable to selectively grip the aerofoil in use. The second jaw member is adapted to contact a further portion as a trailing edge of the first aerofoil. The tool may allow for manual levering and/or impact forces to be applied to the aerofoil. A method of removal of aerofoils is also provided, involving a sequence of manual operations using the tool. The aerofoil array may be a stator vane array for a gas turbine engine.

Abstract: An end-wall component of the mainstream gas annulus of a gas turbine engine has a cooling arrangement including one or more circumferentially extending rows of ballistic cooling holes through which, in use, dilution cooling air is jetted into the mainstream gas to reduce the mainstream gas temperature adjacent the end-wall. A portion of the cooling holes are first cooling holes angled such that the direction of the dilution cooling air jetted therethrough has, on entry into the mainstream gas annulus, a component in one tangential direction. A portion of the cooling holes are second cooling holes angled such that the direction of the dilution cooling air jetted therethrough has, on entry into the mainstream gas annulus, a component in the opposite tangential direction. The first and second cooling holes are arranged such that the cooling air from jets having entry components in opposing tangential directions collide and coalesce.

Abstract: Vibratory finishing apparatus comprising: a receptacle to receive media; a first fixture to: support an object within the receptacle; and move the object relative to the receptacle in at least a first direction; and a first guide to move relative to the receptacle to direct movement of the media within the receptacle to a predetermined part of the object.

Abstract: A method of forming a component includes defining an identification pattern, defining one or more scanning parameters and/or one or more heating parameters, depositing a sinterable material on a substrate and scanning a heat source of the deposited sinterable material to thereby selectively sinter the material to the substrate to produce a sintered layer having the identification pattern. The sintered layer includes first and second regions, and the method includes sintering the first region using one or more scanning parameters and/or one or more heating parameters having a first value, and sintering the second region using one or more scanning parameters and/or one or more heating parameters having a second value to thereby produce the identification pattern including a contrast between the first and second regions.