Abstract: Apparatus for manufacturing a component and a method of manufacturing a component. The method comprises the steps of directing a beam of energy to heat a working region of a substrate and adjusting the cross sectional shape of the beam to thereby generate a variety of predetermined cross sectional shapes of working region while the beam is being directed onto the substrate. Thus the distribution of energy delivered to the substrate is controlled during the manufacturing process. The cross sectional shape and area of the beam is repeatedly monitored and compared to a library of predetermined cross sectional shape(s) and area(s).

Abstract: A magnetic valve arrangement for controlling flow of fluid, the magnetic valve arrangement having at least one ferromagnetic element forming a portion of a magnetic circuit, a valve member and a valve seat; the valve member has a passage therethrough for the flow of fluid and is moveable between a first position, in which the valve member abuts the valve seat to restrict a fluid flow, and a second position, in which the valve member is spaced from the valve seat to allow a fluid flow into and through the passage in the valve member, wherein the position of the valve member is dependent on the temperature of the ferromagnetic element.

Abstract: A rolling-element bearing 1 comprising an inner race 3, an outer race 2 and an array of rolling elements 4 arranged within a bearing cage 5 situated between the two races 2, 3, the inner surface of the bearing cage 5 being piloted on the inner race 3 for limiting eccentric movement of the cage 5 within the bearing 1 and further having a reservoir 9 formed between a pair of circumferential weirs 6a, 7b on the cage 5, the outer surface of the inner race 3 comprising a raised land portion 3d for contacting oil 9a in the reservoir 9 thereby to control the relative speed of the cage 5 and the inner race 3, wherein the radial depth of each weir 6b, 7b is greater than the maximum radial clearance between the land portion 3d and the cage 5 for maintaining said controlling contact between the land portion 3d and the oil 9a during said eccentric movement of the cage 5.

Abstract: A bearing arrangement for supporting a rotatable shaft relative to a support structure. The bearing arrangement has a first bearing having radially inner and outer races, the inner race being rotatable relative to the outer race in use, and a second bearing arranged such that the first bearing is mounted to the support structure via the second bearing. The second bearing may allow for deflection of the shaft supported by the bearing arrangement.

Abstract: A composite article includes a composite member, a flexible member and at least one shape memory material member. The composite member has longitudinally extending fibers in a matrix material. The at least one shape memory material member extends substantially parallel to the composite member and the flexible member is positioned between the composite member and the at least one shape memory material member to bond the at least one shape memory material member to the composite member. The composite article is particularly suitable for use as a tab for an exhaust nozzle of a turbofan gas turbine engine.

Abstract: An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion which defines an airflow surface for air being drawn through the engine, and one or more hook portions which extend radially inwardly from the body portion. The hook portions are for connection to corresponding engagement portions on the radially outer face of the rotor disc. The or each hook portion is attached to the body portion by a joining arrangement in which a wedge part provided by one of the hook portion and the body portion is received in a complementary-shaped retention recess provided by the other of the hook portion and the body portion.

Abstract: A fan casing for a turbofan engine including an annular casing component of composite material including a body portion having an outwardly directed stiffening flange at one end, the stiffening flange being connected to the body portion by a radially outwardly stepped region, the fan casing also including a metallic ring which is coaxial with the annular casing component, the metallic ring being situated at least partially within the stepped region and being secured to the annular casing component.

Abstract: A fuel supply arrangement for supplying fuel to a turbine engine, the arrangement having a fuel injector in fluidical connection with a first manifold via a first conduit and a second fuel manifold via a second conduit, wherein the first conduit is in fluidical connection with a valve having two outlets, the first outlet fluidically connecting the valve with at least one pilot vent in the injector, and the second outlet fluidically connecting the valve with at least one main vent in the injector via a second valve, the second conduit in fluidical connection with at least one further main vent in the injector via a third valve.

Abstract: A method for inspecting the interior of a non-horizontal pipe includes (a) filling the pipe with a first fluid, (b) feeding a second fluid into a lower part of the pipe when the second fluid is more dense than the first fluid or into an upper part of the pipe when the second fluid is less dense than the second fluid the pipe, a meniscus forming between the first and the second fluid and moving along the pipe, (c) introducing an inspection device having an average density between the densities of the first and second fluids such that the device locates at and moves with the meniscus, (d) obtaining inspection data from the inspection device as the device moves along the pipe, (e) determining positions of the meniscus as it moves along the pipe, and (f) relating the meniscus positions to positions at which the inspection data is obtained.

Abstract: A method is provided of determining the internal cross-sectional area of a pipe along its length. The method includes the steps of: (a) filling the pipe with a first fluid; (b) feeding a second fluid into the pipe at a known flow rate, a meniscus being formed between the first and the second fluid, and the meniscus moving along the pipe as the second fluid displaces the first fluid in the pipe; (c) ultrasonically detecting the position of the meniscus as it moves along the pipe; and (d) determining from the second fluid flow rate and the meniscus position, the internal cross-sectional area of the pipe along its length.

Abstract: An annulus filler system bridges the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine. The system includes an annulus filler having a lid which extends between the adjacent blades and defines an airflow surface for air being drawn through the engine. The filler also has a support body extending beneath the lid and terminating in an elongate foot which, in use, extends along a groove provided in the rim of the disc. The groove has a neck which prevents withdrawal of the foot through the neck in a radially outward direction of the disc. The system further includes a sleeve which, after installation of the filler, is slidably locatable into a gap between the foot and sides of the groove.

Abstract: An annulus filler system bridges the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine. The system includes an annulus filler having a lid which extends between the adjacent blades and defines an airflow surface for air being drawn through the engine. The filler also has a support body extending beneath the lid and terminating in an elongate foot which, in use, extends along a groove provided in the rim of the disc. The groove has a neck which prevents withdrawal of the foot through the neck in a radially outward direction of the disc. The system further includes a sleeve which, after installation of the filler, is slidably locatable into a gap between the foot and sides of the groove.

Abstract: A rotational assembly comprises a first shaft having a plurality of circumferentially arranged axially extending outer splines on an outer surface thereof and a second shaft having a plurality of circumferentially arranged axially extending inner splines on an inner surface of an axially extending shaft recess. The first shaft is located with the shaft recess such that the outer splines are engaged with the inner splines. At least one biasing element is also provided which is arranged to rotationally bias the first and second shafts towards one another such that the driving faces of the inner and outer splines are forced together.

Abstract: An arrangement for a combustion chamber the arrangement comprising a combustion chamber, an injector for injecting fuel into the combustion chamber and an igniter for supplying a spark for igniting fuel so injected, wherein the injector has a passage through which air is supplied to the combustion chamber in use, the igniter being positioned upstream of the combustion chamber such that a spark generated by the igniter is conveyed along the passage by the injector air.

Abstract: An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler defines an airflow surface for air being drawn through the engine. The annulus filler has one or more primary connectors for connecting the annulus filler to the rotor disc, and for resisting, in use, centrifugal forces on the annulus filler. Each primary connector allows rotation of the annulus filler around the center line of the engine relative to the rotor disc at that primary connector. The annulus filler also has a secondary connector for connecting the annulus filler to the rotor disc and for resisting, in use, motion of the annulus filler relative to the rotor disc in a first axial direction. The secondary connector allows rotation of the annulus filler around the center line of the engine relative to the rotor disc at the secondary connector.

Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels and the web by applying internal pressure between the panels so as to form a series of internal cavities partitioned by the web. The method further includes the step of either cutting the web (30) across its entire width or causing the web to fail across its entire width so as to define an aerofoil having first and second panels with at least one protrusion extending from the first panel partially across the space between the first and second panels.

Abstract: A method of manufacturing a milling cutter having a cutting head and a coaxial integral shank including grinding, in a first grinding operation, a plurality of helical flutes into the outer periphery of a cutter blank from a lead end using a peripheral area of a first grinding wheel generally of frusto-conical profile and rotatable about an axis generally transversely of the milling cutter axis, which peripheral area produces, simultaneously, the following three features: a leading face of a trailing tooth; a rear face on an adjacent preceding tooth; and a swarf removal gullet having divergent sides, grinding, in a second grinding operation, and using a peripheral edge of a second grinding wheel, a relief face, which extends rearwardly from a leading end of a tooth tip, resulting in a minimum tooth wedge angle of approximately 60°, and grinding, in a third grinding operation, a radius on the end of each flute.

Abstract: A gas turbine engine combustion chamber includes a first wall and a second wall. The second wall is arranged within and spaced from the first wall to define a cavity between the first wall and the second wall. The first wall has a plurality of impingement apertures extending there-through and the second wall has a plurality of effusion apertures extending there-through. The impingement apertures have a first diameter, a first pitch, and a first area. The effusion apertures have a second diameter, a second pitch, and a second area. The ratio of the first diameter to the second diameter is at least 3, the ratio of the first pitch to the second pitch is at least 4 and the ratio of the first area to the second area is at least 9. This arrangement increases the cooling performance of the effusion apertures in the second wall.

Abstract: A method of determining the proportions of different powders in a powder comprises obtaining a sample of a powder, adding and mixing the sample into a molten material and freezing the mixture of powder and molten material to form a block. Computed tomography is performed on the block to produce a three-dimensional image of the block, the three-dimensional image of the block comprises a first shade, a second and a third shade corresponding to the material, a first powder particle and a sec and powder particle. The three-dimensional image of the block is analysed to count the number of regions exhibiting the second shade and the third shade corresponding to the number of first powder particles and second powder particles respectively. The fraction of second particles in the powder is determined by dividing the number of second powder particles by the sum of the number of first powder particles and the number of second powder particles.

Abstract: A composite component such as a blade or vane of a gas turbine engine includes a body and an erosion-resistant layer. The body includes a fibre reinforcement in a resin matrix, and the erosion-resistant layer includes a 3-D woven fabric element which is also resin-impregnated. The woven fabric element is made from a thermoplastics material such as PEEK, and may be thicker at the leading edge of the component than at pressure and suction surfaces. The component may be manufactured in a laying-up process in which the woven fabric element of the erosion-resistant layer is placed in a mould with the resin-impregnated fibre reinforcement of the body so that the resin of the body migrates into the woven fabric element of the erosion-resistant layer.