Abstract: A fault-accommodating flow scheduling valve has a first inlet, outlet, and orifice therebetween. The valve has a shuttle valve member on the orifice inlet side, a primary valve member on the orifice outlet side, a compression-loaded primary spring, and first and second compression-loaded balance springs. Below a threshold differential pressure, the primary valve member engages with the outlet-side sealing face to close the valve while the shuttle valve member is spaced from the inlet-side sealing face, and on failure of the primary spring, the primary valve member moves from the outlet-side sealing face but the shuttle valve member closes the valve. Above the threshold differential pressure, the primary valve member opens the valve while the shuttle valve member remains spaced, and on failure of the primary spring, the primary valve member moves further from the outlet-side sealing face but the shuttle valve member closes the valve.

Abstract: An aircraft gas turbine engine (10) comprises a main engine shaft (22) arranged to couple a turbine (17) and a compressor (13), the main engine shaft (22) defining an axial direction (9). The gas turbine engine (10) further comprises at least one radially extending offtake shaft (27) coupled to the main engine shaft (22), and a radially extending electric machine (25a, 25b) coupled to the radially extending offtake shaft (22).

Abstract: A gas turbine engine for an aircraft. The gas turbine engine comprises a rotatable shaft defining a rotational axis extending between rearward and forward ends of the gas turbine engine and a compressor drum surrounding, and coupled to, the shaft so as to define an annular gap therebetween. The gas turbine engine further comprises an intermediate case arranged axially rearward of the compressor drum and comprising a bearing support element extending into the annular gap, and a forward bearing mounted between the bearing support element and the shaft proximate a forward end of the compressor drum.

Abstract: An aircraft gas turbine engine (10) comprises a main engine spool (22) and a bearing arrangement (36) configured to rotatably support the main engine spool (22). The bearing arrangement (36) includes a damper (41) comprising a static element (42) and a moveable element (39). The gas turbine engine further comprises an electric machine (30) comprising a rotor (34) and a stator (32). The rotor (34) is mounted to the main engine spool (22), and the stator (32) is mounted to the moveable element (39) of the damper to be moveable with the moveable element (39).

Abstract: Battery assemblies and methods of fabricating battery assemblies are provided. One such battery assembly comprises: an array of battery cells comprising plural rows, each row comprising plural cells, each cell extending between opposed first and second ends and having first and second terminals both at the first end; a carrier frame housing the array of cells and comprising an array of apertures corresponding to the array of cells, the first end of each cell is at least partially exposed by one of the apertures; and bus bars attached to the carrier frame between adjacent rows of the array such that each of the rows is adjacent two bus bars.

Abstract: A battery assembly and a method of assembling a battery assembly are provided. The battery assembly comprises: an array of battery cells, the array comprising plural rows, each row comprising plural cells; a flexible printed circuit board (PCB) provided between two adjacent rows, of the plurality of rows of cells; and at least one temperature sensor provided adjacent to and electrically connected to the flexible PCB, each temperature sensor being operable to sense a temperature of one or more cells of the two adjacent rows.

Abstract: A method of assembling a battery pack from a plurality of battery cells of a same type is provided. The method may account for normal variation in the DC internal resistance of the cells and thereby improve the battery pack's performance. The method comprises: identifying a design for at least a portion of a battery pack, wherein the portion includes a plurality of battery cells and the design defines, for each of the plurality of cells, a cell position within the portion of the battery pack; obtaining a thermal model for the portion of the battery pack.

Abstract: A computer-implemented method of creating a database of characterising codes, each characterising code being indicative of character of a respective example of a physical system. The method comprises the steps of performing for each example: (a) receiving data including respective values of a plurality of parameters associated with the system; (b) identifying, from a plurality of data clusters, a data cluster for each value, said data clusters each defining a range of possible values of the respective parameter; (c) assigning each parameter to its identified data cluster; (d) generating, from the assigned data clusters, a characterising code for that example including a unique label for each of the identified data clusters; and (e) storing the characterising code in a database of characterising codes.

Abstract: A vane assembly includes an aerofoil having a leading edge, a trailing edge, and a pressure surface and a suction surface defined between the leading edge and the trailing edge. The aerofoil includes a blade member forming the trailing edge, at least a portion of the pressure surface and at least a portion of the suction surface. The blade member is formed of a first material. The aerofoil further includes a spar at least partly enclosed by the blade member and forming at least a portion of the leading edge. The spar further forms at least one cooling channel and supports at least a portion of an interior surface of the blade member. The spar is formed of a second material different from the first material. The second material has a greater impact resistance than the first material.

Abstract: A device is provided for inserting coil inserts into threaded holes. The device includes an insertion tool having a manipulator end which is configured to receive and hold a coil insert, and which is operable to apply a torque to the coil insert to screw the coil insert into a threaded hole when presented thereto, the manipulator end having an insertion axis which is coincident with the axis of the coil insert when held by the manipulator end. The device further includes a tool support to which the insertion tool is mounted, the tool support being fixable to an end of a robot arm whereby the manipulator end is presentable by the robot arm to the threaded hole for insertion therein of the coil insert.

Abstract: A controller assembly comprises an electromechanical actuator and a single-stage pneumatic flow switch configured to thermally protect the electromechanical actuator by a supply of cooling fluid. The single-stage pneumatic flow switch is movable between a first mode in which the switch is configured to open a cooling fluid flow passage and a second mode in which the switch is configured to close the cooling fluid flow passage. The electromechanical actuator is coupled to a valve movable between an open and a closed configuration.

Abstract: There is disclosed bagging apparatus (20) for bagging a pre-form (12) for a composite component on a tool (10), the apparatus (20) comprising: a bag dispenser (22) having a store (28) for a tubular vacuum bag (30); and a bag guide (36). In use, a length of tubular vacuum bag material (30) can be drawn from the store (28) radially outwardly over the bag guide (36) and over the tool (10) to form a tube around the pre-form. There is also disclosed a method of bagging a pre-form (12) for a composite component on a tool using the bagging apparatus (20).

Abstract: A fuel spray nozzle for a gas turbine engine, the fuel spray nozzle arranged to mix fuel and air and provide the mixture to a combustor of the engine and including: a first fuel supply conduit arranged to provide fuel to be mixed with air in a first ratio; a second fuel supply conduit arranged to provide fuel to be mixed with air in a second ratio, having a lower proportion of fuel than the first ratio; and a staging valve arranged to control the relative proportions of fuel provided through the first fuel supply conduit and the second fuel supply conduit, such that an increase or decrease in the flow in the first fuel supply conduit is accompanied by a corresponding decrease or increase in the flow in the second fuel supply conduit.

Abstract: The present disclosure concerns apparatus and methods for reinforcing composite materials by insertion of reinforcement pins. Example embodiments include an apparatus for reinforcing a composite preform, comprising: a carriage for introducing reinforcement pins into the composite preform, the carriage comprising a drill module, a pin feeder module and a tamper module, the assembly being translatable relative to the composite preform, wherein the drill module and pin feeder module are exchangeable between a common actuation position on the carriage.

Abstract: A gas turbine engine for an aircraft including a unit supplied with oil from a first oil circuit and a second oil circuit. The first oil circuit and the second oil circuit each are fluidly coupled with at least one inlet and with at least one outlet of the unit and with at least one inlet and with at least one outlet of an oil tank. The first oil circuit and the second oil circuit are configured to receive oil from the oil tank and to direct the received oil to the unit. The oil tank is incorporating offset outlets to each of the oil circuits. The offset outlet of the second oil circuit is positioned higher in the oil tank than the offset outlet of the first oil circuit.

Abstract: A fan blade for a gas turbine engine has a covered passage. A cross section through the fan blade at a point along the blade span is defined as having particular change in angle (?3??1) of the camber line between the leading edge and the trailing edge and/or between the leading edge and the point on the camber line that corresponds to the start of the covered passage.

Abstract: A 3D printed metal coil for an electrical machine. The 3D printed coil has a plurality of turns and is configured to fit within a slot in an electrical machine. A cross-sectional shape of successive turns of the plurality of turns varies such that a portion of each turn forms a part of an external surface of the metal coil, the external surface forming an interface with a side of the slot.

Abstract: Gas turbine engine for aircraft includes: an engine core including a turbine, compressor, and core shaft connecting the turbine to the compressor; a fan located upstream of the core; a gearbox; and a gearbox support arranged to at least partially support the gearbox. A moment of inertia of the fan is greater than or equal to 7.40×107 kgm2. A radial bending stiffness to moment of inertia ratio of: the ? ? radial ? ? ? bending ? ? stiffness ? ? of ? ? at ? ? least ? ? one ? ? of ? ? the ? ? fan ? ? shaft ? ? at ? ? the ? ? output ? ? of ? ? the ? ? gearbox ? ? and ? ? the ? ? gearbox ? ? support the ? ? moment ? ? of ? ? inertia ? ? of ? ? the ? ? fan may be greater than or equal to 2.5×10?2 Nkg?1m?3.

Abstract: A 3D printed metal coil for an electrical machine. The 3D printed coil has a plurality of turns and is configured to fit within a slot in an electrical machine. A portion of each turn forming an end winding of the coil has a flat plate-like shape for dissipating heat from the end winding.

Abstract: The present disclosure relates to gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox comprising: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.