Abstract: A transducer assembly (100) for connecting a transducer (102) to a device, the transducer assembly comprising: a transducer mount (110) adapted to receive the transducer; and a clamp (120) comprising first and second jaws (122, 124), the first and second jaws being adapted to selectively clamp to a flange portion (106) of the device. The transducer mount (110) may comprise a housing (112), a resilient member (114) and first and second end walls (115, 116). The first end wall may be operatively connected to the device. The transducer (102) may be held within the housing and adjacent to the first end wall. The resilient member being disposed between the transducer and the second end wall.

Abstract: The fan duct of a ducted fan gas turbine engine has a fan case (20) lined with a honeycomb structure (22) that acts to absorb the energy of a separated part of a blade (16). A layer of composite material (24) lining honeycomb structure (22) delaminates/breaks when a separated blade part passes through a further, inner honeycomb liner (26) and hits it. The resulting free end of composite liner (24) wraps round the striking end of the blade part, thus blunting the cutting action of the blade part and spreading the generated forces to the extent that the blade part is de-energised sufficiently to prevent it penetrating the fan case (20).

Abstract: An air-cooled oil cooler for the wall of an air flow passage of a gas turbine engine is provided, the oil cooler allowing improved heat exchange performance to be obtained. This is achieved by: (I) diverting air flow from the inner side of the oil cooler towards the outer side of the oil cooler, (ii) enhancing heat exchange performance at the leading edge of the cooler, and/or (iii) suppressing airflow wake at the trailing edge of the cooler.

Abstract: A seal (48) between first and second relatively rotatable members (26,28). The seal comprises an abradable material on at least one of the relatively rotatable members (26,28). The abradable material comprises an open cell metallic foam (60) and polymeric films (64) closing the cells (62) of the metallic foam (60). The seal (48) is used between compressor rotor blades (26) and a stator casing (28) of a gas turbine engine (10). The seal (48) combines the sealing properties of a closed cell metallic foam with the abradability and manufacturing control of open cell metallic foam.

Abstract: A liner is provided for an air flow passage of a gas turbine engine. The liner comprises an acoustic attenuation layer which forms an air-washed surface of the flow passage, and a heat exchanger layer which extends as a backing to the acoustic attenuation layer. The heat exchanger layer is configured to carry a heated fluid flow and to transport heat from the fluid flow to the acoustic attenuation layer from where the heat is transferred to air flowing through the air flow passage.

Abstract: A clamping assembly comprising a bearing support member (16), the bearing support member being clampable to a shaft (2) by virtue of a clamping member (24) adaptable to tighten the bearing support member to the shaft, wherein at least a portion (16?) of the bearing support member (16) is disposable between a first abutment surface (28) provided on the clamping member and a second abutment surface (25) provided on the shaft; and wherein the portion (16?) of the bearing support member (16) comprises one or more protrusions (30) and one or more depressions (32) provided on an end face (16a, 16b) of the portion of the bearing support member, the protrusions and depressions being arranged to interface with one or more corresponding depressions (36) and protrusions (34) provided on one of the first abutment surface of the clamping member and the second abutment surface of the shaft, the respective protrusions and depressions being disposed so as to resist relative rotation between the shaft and the bearing support

Abstract: A stage for a gas turbine engine, having a plurality of circumferentially spaced apart radially extending aerofoils, includes a plurality of annulus fillers to bridge the spaces between adjacent aerofoils to define an inner wall of a flow annulus through the stage. Each annulus filler has opposing side faces which are spaced circumferentially from the adjacent blades and which correspond in profile therewith, and resilient seal strips each including a stiffener are mounted adjacent the opposing side faces of the annulus fillers to seal the gaps between the annulus fillers and the aerofoils. The stiffeners have three-dimensional curvature.

Abstract: A magnetic gear arrangement, having a first gear member for generating a first magnetic field and a second gear member for generating a second magnetic field. An interpole member is provided between the first and second gear members for coupling the two magnetic fields and controlling the gear ratio between the two gear members. The interpole member includes a unitary body of magnetisable material and associated control wiring, and is arranged such that when current is passed through the wiring, space regions of the unitary body are magnetised by an electrically-induced magnetic field. Discrete interpoles, the number and spacing of which define the gear ratio, are then formed in the unitary body between adjacent magnetised regions.

Abstract: A combustor system is provided for a gas turbine engine. The combustor system includes an annular combustion chamber, and outer and inner casings housing the combustion chamber. The outer casing is outwardly radially spaced from the combustion chamber and the inner casing being inwardly radially spaced from the combustion chamber. The combustor system further includes an attachment arrangement at the rearward end of the combustion chamber for attaching the combustion chamber to the engine. The attachment arrangement axially restrains the rearward end of the combustion chamber relative to the casings. The combustor system further includes a first stop surface formed at the forward end of the combustion chamber adjacent a selected one of the outer and inner casings, and a corresponding first baulking surface axially forward of the first stop surface formed by the selected casing.

Abstract: Protection arrangements and methods of operating protection arrangements are important in order to maintain operability with regard to electrical power distribution networks. Such networks generally comprise grids or meshes of electrical distribution pathways from generators and electrical loads. Faults may occur within the network and circuit breakers or other protection elements are utilised to isolate such faults. A number of regimes for protection are known but problems can arise with regard to ensuring an appropriate pan of the distribution network is isolated.

Abstract: A magnetic gear arrangement is provided having a first gear member that generates a first magnetic field and a second gear member that generates a second magnetic field. A plurality of interpoles are disposed between the two gear members for coupling the first and second magnetic fields to control a gear ratio between the gear members. At least one interpole has wiring associated with it that can be activated to alter the magnetic flux at the interpole, so as to vary the coupling between the first and second magnetic fields. The wiring is electrically connected to an electronic filter, which modifies the current passing through the wiring, so as to modify the influence of the wiring on the magnetic flux at the interpole.

Abstract: The present invention relates to a method of manufacturing a multiple composition component 10, comprising: arranging first, second and third constituent parts 40, 30, 42 having first, second and third compositions respectively A, B, C so that the first constituent part 40 shares a first boundary with the second constituent part 30 and the second constituent part 30 shares a second boundary with the third constituent part 40. The first, second and third constituent parts 40, 30, 42 are each either a powder or a solid so that the first and second boundaries are each a solid adjacent to a powder. The arrangement is then processed so as to form a single solid component having first, second and third regions 16, 18, 20 having first, second and third compositions A, B, C respectively.

Abstract: A blade for a gas turbine engine includes a root portion, an aerofoil portion and a transition portion between the root portion and the aerofoil portion. The aerofoil portion and the transition portion are defined by first and second wall members, the first and second wall members being secured together in the transition portion and each having an outer surface. The outer surface of at least one of the first and second wall members is generally concave in the transition portion in a radial direction of the blade.

Abstract: A method of manufacturing a hollow article (10) comprising the steps of cold pressing two members (30,34) to form at least one depression (32,36) in the members (30,34). Arranging the two members (30,34) in abutting relationship such that the at least one depression (32,36) defines at least one chamber between the two members (30,34). Sealing (41) the edges (40,42) of the two members (30,34) together to form a core structure (44). Positioning the core structure (44) in a mold (46) to define a cavity (48) between the external surface (50) of the core structure (44) and the internal surface (52) of the mold (46), the internal surface (52) of the mold (46) substantially defining the external shape of the hollow article (10). Filling the cavity (48) between the core structure (44) and the mold (46) with a powder material (54), sealing the open edge of the core structure (44) to the mold (46).

Abstract: A rotor and a stator assembly, wherein the rotor (30) comprises at least one stage of rotor blades (32) and the stator (34) comprises at least one stage of turbine stator vanes (36). The rotor blades (32) have aerofoils and platforms (42) and the turbine stator vanes (36) having aerofoils and platforms (48). A seal (43,45) is defined between the rotor blade (32) platforms (42) and the stator vane (36) platforms (48) wherein a portion (42B) of the rotor blade platforms (42) and/or a portion (48B) of the stator vane (36) platforms (48) comprise a shape memory alloy member or a bimetallic member. The shape memory alloy member, or bimetallic member, controls the flow of cooling air through the seals (43,45) allowing a greater cooling flow at higher temperatures than at lower temperatures.

Abstract: An arrangement for sealing an opening formed in a wall for receiving a member. The arrangement comprises a sealing member with a passage, and the sealing member is moveably mounted on the wall adjacent to the opening such that the sealing member passage is substantially co-axial with the opening in the wall. Biasing means for biasing the sealing member towards the wall are also provided.

Abstract: A fan blade is provided having a root portion and an aerofoil portion that has a leading edge, a trailing edge and a tip remote from the root portion. A concave pressure surface extends from the leading edge to the trailing edge and a convex suction surface extends from the leading edge to the trailing edge. A portion of the tip of the aerofoil portion between the leading edge and the trailing edge of the aerofoil portion is thinner than the remainder of the tip. The portion of the tip of the aerofoil portion is spaced from the leading edge and is spaced from the trailing edge. The portion of the tip of the aerofoil portion has a recess arranged on the concave pressure surface such that the portion of the tip of the aerofoil portion is thinner than the remainder of the tip.

Abstract: A seal for an annulus filler for a gas turbine engine comprises a seal body releasably attached in use to the fan annulus filler, the seal body supporting two seal members so that in use one seal member is brought into contact with, and forms a seal against, an aerofoil surface of one of the fan blades, and the other seal member is brought into contact with, and forms a seal against, an aerofoil surface of the other of the fan blades.

Abstract: Cavities 4 are defined within an engine nacelle 1 with an inner surface 2 and an outer surface 3. Within these cavities 4, an evaporatable liquid 5 is arranged such that a proportion of the liquid 5 is in a gaseous phase in order to facilitate heat transfer between the inner surface 2 or the outer surface 3 and a hot surface. The liquid condenses upon the inner surface 2 or the outer surface 3 and collects into a pool for subsequent further evaporation by the hot surface of an insulated gate bi-polar transistor or convertor/generator components in order to facilitate further cooling of electric components housed or arranged in the nacelle 1 or nearby.

Abstract: A method of manufacturing a foam having a negative Poisson's ratio comprising the steps: placing a pad 12 of open cell polyurethane foam on a moulding surface 4; placing a flexible membrane 18 over the exposed surface of the foam to create a sealed chamber 20 between the moulding surface 4 and the flexible membrane 18 in which the foam pad 12 is disposed; applying an isostatic pressure difference between the inside and the outside of the chamber 20 thereby collapsing the foam pad 12 between the flexible membrane 18 and the moulding surface 4; heating the foam pad 12 to a predetermined temperature, and subsequently cooling the foam pad 12 while collapsed.