Abstract: A method of manufacturing a ceramic matrix composite article comprising the steps of: — a) forming a slurry consisting of water, polyvinyl alcohol, nitric acid, polyethylene glycol and alumina particles only, b) providing a length of fabric, the fabric comprising a plurality of ceramic fibres, c) applying slurry to at least one of the sides of the length of fabric such that the slurry adheres and impregnates the length of fabric, d) drying the slurry impregnated length of fabric, e) cutting the slurry impregnated length of fabric into a plurality of pieces of slurry impregnated laminates of fabric, f) applying water to each of the pieces of slurry impregnated laminates of fabric to reactivate the slurry, g) stacking the plurality of pieces of slurry impregnated laminates of fabric on a first mould part, h) consolidating the plurality of pieces of slurry impregnated laminates of fabric on the mould part, and i) sintering the stack of the plurality of pieces of slurry impregnated laminates of fabric to form an

Abstract: Actuators utilising shape memory alloy materials are known with regard to gas turbine engines. Such shape memory alloys have been used with respect to deformation provided in vanes and blades as well as nozzle elements in order that variations can be made in engine configuration dependent upon thermal cycling. Unfortunately, pedestals in order to provide spacing between the shape memory alloy and an antagonistic bias has resulted in uneven stress distribution as well as a higher thermal mass for the shape memory alloy. An uneven stress distribution will limit operational life whilst a higher thermal mass will result in slower reaction times. By separation of the shape memory alloy or material from its antagonistic bias through use of a slide element, a reduction in thermal mass is achieved and, more importantly, stress differentiation across the actuator is reduced.

Abstract: A reformer module (10) comprises a hollow support member (12) having at least one passage (14) extending longitudinally therethrough. The hollow support member (14) has an external surface (20), a barrier layer (22) arranged on at least a portion of the external surface (20) of the hollow support member (12), a catalyst layer (24) arranged on the barrier layer (22) and a sealing layer (26) arranged on the catalyst layer (24) and the external surface (20) of the hollow support member (12) other than the at least a portion of the external surface of the hollow support member (12). By providing the barrier layer (22) and the catalyst layer (24) on the exterior surface (20) of the hollow support member (12), the distribution of the barrier layer (22) and/or the catalyst layer (24) may be more precisely controlled and thus a non-uniform distribution of barrier layer (22) and/or catalyst layer (24) may be achieved.

Abstract: Synchronous generators are driven by shafts to produce 3-phase AC power. The frequency and amplitude of power depends on the speed of the respective shaft. The outputs are rectified and connected in series to provide an output of varying voltage DC power to a load. Applications in aerospace and renewable energy supply are described.

Abstract: A powder and/or polyhedral grains of a solid material are produced by directing one or more jets of liquid at a body of the solid material, thereby causing the ablation of powder particles from the solid material. The jet or jets of liquid may be controlled to cut polyhedral grains from the solid material. The liquid within which the powder particles and/or grains are entrained is then collected and the powder particles and/or grains are separated from the liquid.

Abstract: A method of manufacturing a component. The method includes the steps of heating a working region of a substrate with a heating means; directing a material into the working region to bring the material into a temporary molten state, and depositing said material on the substrate such that when the material solidifies it forms at least part of the component. The heating means power output, stand off, orientation, speed and direction of travel relative to the substrate are adjustable and controlled throughout the material deposition process to control the shape and/or size of the working region to thereby control the distribution and rate of heat delivery to the substrate.

Abstract: A mounting arrangement for locating a stator (10) within a casing (16) of a rotating machine comprises at least one mounting plate (12) adapted to engage with the stator (10) and the casing (16). The mounting plate (12) has a series of discrete apertures (20) therein. The apertures (20) extend through the plate (12) and are arranged in an array to provide a convoluted path which impedes the transmission of the dynamic forces through the plate (12) and into the casing (16). The apertures (20) render the plate (12) more resilient to the dynamic forces that the stator (10) experiences in operation. Each aperture (20) divides the plate (12) into portions which provide anisotropic stiffness in the radial and tangential directions.

Abstract: Apparatus for applying a fluid to a target area of a component is provided, the apparatus comprising a fluid applicator 10 and means 12, 300, 400 for guiding the fluid applicator 10 along a predetermined path with respect to the component 26; the fluid applicator 10 comprising a body 14 and an application head 50, 100, 200 mounted on the body 14 and operable in use to be brought into physical contact with the component 26.

Abstract: The generator uses a permanent magnet electrical machine providing three phase, unregulated DC voltage, from three windings feeding a rectifier circuit. A capacitor across the DC voltage acts as a buffer between the DC supply and the load. Regulation of the DC supply seen by the load is achieved by a switch in parallel with the DC voltage and with the load. The switch allows current to be drawn by the capacitor or load from the windings, or shorts the windings. The inductance of the windings makes it safe to short them. A blocking diode prevents current returning from the capacitor when the switch is closed. The result is a regulated DC output of adequate quality for e.g. aerospace applications and with low component count and complexity.

Abstract: A rotor blade for a gas turbine engine has an aerofoil portion and a tip region. The tip region is at the radially outermost end of the blade. The radially outermost surface carries abrasive material (not shown) to interact with an abradable surface. The tip has a recess in which cooling air outlets are formed. The recess is open in a circumferential direction. This allows cooling air outlets to be formed without interference from the abrasive material, and inhibits any tendency for abrasion debris to collect in the recess and interfere with the flow of cooling air.

Abstract: A rotor blade 40 for a gas turbine engine has an aerofoil portion 42 from a root 48 to a tip 54. In use, combustion gas may leak over the tip 54 from the pressure face 52 to the suction face 50. A gutter 62 extends across the tip 54 to entrain any over tip leakage gap. The floor of the gutter defines an increased depth portion 72 at the exit end of the gutter 62.

Abstract: A turbine blade (40) for a gas turbine engine has an aerofoil portion (42) extending from a root (48) to a tip (54). The tip (54) carries winglets (56, 58). A gutter (62) extends across the tip (54) to entrain gas leaking around the tip (54) (over tip leakage). The aerofoil portion (42) has a mean camber line and the gutter (62) has a centre line. In the examples described, the conditions that (a) the mean camber line and the centre line coincide at the exit when viewed from the tip towards the root, and (b) the mean camber line and the centre line are parallel at the exit when viewed as aforesaid, are not both fulfilled.

Abstract: A magnetic gear arrangement is provided comprising a first gear member for generating a first magnetic field and a second gear member for generating a second magnetic field. A coupling element is disposed between the first and second gear members and provides arrangements of interpoles which couple the first and second magnetic fields. The coupling element comprises a plurality of magnetisable lamellae, each interpole in an arrangement of interpoles being formed from a group of neighbouring lamellae. Selected lamellae are deactivatable to provide boundaries between adjacent interpoles. This allows different numbers and arrangements of interpoles to be formed, so as to provide different gear ratios between the first and second gear members.

Abstract: A composite blade (26) comprises a three-dimensional arrangement of reinforcing fibres (58) and a matrix material (60) infiltrated around the three-dimensional arrangement of woven reinforcing fibres (60). The three-dimensional arrangement of woven reinforcing fibres (58) defines a plurality of cavities (56) within the aerofoil (28). The composite blade (26) comprises an aerofoil portion (38) and a root portion (36). The aerofoil portion (38) comprises a leading edge (44), a trailing edge (46), a concave pressure surface wall (50), a convex suction surface wall (52) and a tip (48). The aerofoil portion (36) comprises a plurality of webs (54) extending between, and being secured to, the concave pressure surface wall (50) and the convex suction surface wall (52) to produce a Warren girder structure. The three-dimensional arrangement of woven reinforcing fibres (58) are arranged to produce the concave pressure surface wall (50), the convex suction surface wall (52) and the plurality of webs (54).

Abstract: A fault current limiter comprising: an input node; an output node; a variable impedance element coupled between the input node and the output node; a closed loop cryocooler circuit, comprising a first cryocooler for cooling the variable impedance element and a second cryocooler, thermally coupled to the first cryocooler, for cooling the first coolant, wherein the variable impedance element comprises Magnesium Diboride.

Abstract: Aerofoils (22) of a gas turbine engine are provided with a coating (34) or filler (44) of viscoelastic material. As ice accretes on the aerofoils (22) during operation, the resulting aerodynamic stability imbalance induces vibration in the aerofoils (22). The viscoelastic material (34, 44) damps this vibration, and in so doing generates heat, which melts the ice away from the aerofoils (22). Heat-conducting members conduct the heat to regions of the component in which ice accretion is to be prevented. Alternative embodiments are described in which the pseudoelastic behaviour of a shape memory alloy (56), or eddy currents arising from the rotor blades' rotation in an axisymmetric magnetic field, are used as sources of heat.

Abstract: A frame for the support of a bladed array, such as a compressor rotor stage or turbine rotor stage for turbo machinery, comprises a collar configured to fit around a radially outer periphery of the array. The collar is provided with a closure mechanism. The closure mechanism is configured to, in use, close the collar around the bladed array such that at least part of at least some of the blades are engaged with and/or captured by the radially inner surface of the collar. The collar and bladed array are held in a fixed relationship relative to one another.

Abstract: A method of manufacturing a composite rotor disc (2) in which, following diffusion bonding of a ceramic core section (4) of the rotor disc (2) to a metallic outer section (6) of the rotor disc (2) at an elevated temperature, the rotor disc (2) is allowed to cool to a predetermined temperature and is held at this predetermined temperature for a predetermined period of time. Whilst the rotor disc (2) is held at this predetermined temperature it is loaded in a radially outward direction. The rotor disc (2) is then allowed to cool to a temperature below the predetermined temperature.

Abstract: A fan track liner within a rotor blade assembly for a gas turbine engine comprises a radially inner casing liner member and a radially outer casing liner member adjacent to the radially inner casing liner member. A septum is interposed between the radially inner and radially outer casing liner members and bonds together the radially inner and radially outer casing liner members. The septum includes predetermined weakened regions which permit penetration of the septum in use by a rotor blade in the event of impact of the radially inner casing liner member by a detached rotor blade. Assembly otherwise capable of resisting ice shed from the blade impacting the same region.

Abstract: Interruption in supervisory position control signals can cause problems with respect to actuators which upon loss of such control signals for the actuator will generally slew to a fixed idle position. In such circumstances a machine such as a gas turbine engine in which an actuator is associated will not sustain performance even though there is continued local power supply to the actuator. By utilizing a local controller which stores actuator response profiles for certain machine status stages through perturbation or marginal activation of the actuator an appropriate actuator response profile can be chosen and therefore sustaining control signals presented to the actuator to maintain machine operation.