Abstract: A core for casting a container comprising a casting surface, where the core is divided into at least two core segments. The casting surface of each core segment adjoins a division surface, and the division surface of each core segment is spaced apart from the division surface of a neighbouring core segment by a gap. The gap is spanned by a frangible collapsible member such that substantially all of the casting surface is free of the collapsible member.

Abstract: A gasket or seal member constructed of elastomeric material has at least one slot extending lengthwise of the member and across its thickness at an oblique angle to the sealing faces. There may be a plurality of slots spaced apart across the width of the member. In a preferred form of the invention multiple, parallel slots are formed at an oblique angle to the seal faces of the member forming branchiate-like layers of gasket material, in which each of the layers partially overlays at least one other layer.

Abstract: In order to determine displacement, axial and radial in a rotating component, an optical displacement probe is used incident upon a target formed from surface features in a rotating component surface. The surface features create a target which is axially variable in terms of reflectivity, but substantially consistent for the same circumferential band incident position. In such circumstances, differences in responses can be determined by a controller deducting time period ?T differences between peaks 20, 21, 30, 31 in one axial position from the time period in a different axial position in order to provide an axial signal proportional to axial displacement. In terms of determining radial displacement, an angularly presented probe part in the form of an optical fiber 3 is used so that variation of the time period is proportional to radial as well as axial displacement.

Abstract: A method of manufacturing an article by diffusion bonding at least two metal components (30,36) comprises assembling the metal components (30,36) into a stack relative to each other so that the surfaces (34,40) are in mating contact. The edges of the metal components (30,36) are sealed together, except for an aperture (49) where a pipe (50) is to be connected. A connector (51) has a first end (52) and a second end (53). The first end (52) has a smaller diameter than the second end (53) and a bore (54) extends through the connector (51) from the first end (52) to the second end (53). The second end (53) of the connector (51) is joined (57) to the stack. The pipe (50) is joined (58) to the first end (52) of the connector (51). The interior of the sealed assembly is evacuated via the pipe (50) and the pipe is sealed. Heat and pressure are applied to diffusion bond the metal components (30,36) together to form an integral structure.

Abstract: A generator assembly for a gas turbine engine. The assembly includes an electrical generator connected via a first sprag clutch to an accessory gearbox driven by the engine. The generator is also connected by a second sprag clutch to an air turbine connected to engine bleed valves which are selectively open when the engine speed falls below a predetermined level. The clutches are arranged such that the generator is driven at any time by the fastest rotating of the gearbox and turbine.

Abstract: Work support arrangements 1 are provided in order to support work pieces 20 when it is necessary to machine those work pieces 20. The work pieces 20 may simply passively rest upon contact ends 6, 16 or be in compressive engagement to retain position but in either event it is advantageous to determine contact force. By providing a contact pad element 15 which directly provides contact force at an interface between contact end 6, 16 and the work piece 20 without taking any load force itself robust determination of contact force is achieved. Generally, the contact pad element 15 is suspended upon a guide 13 extending from a mounting such as an actuator seat 11.

Abstract: A gas turbine engine re-pressurisation device (36) for cooled cooling fluid, the re-pressurisation device (36) comprising a compressor stage (42) and a turbine stage (46), characterised in that a common mounting means (58) is provided between the compressor stage (42) and the turbine stage (46) such that one of the compressor stage (42) and the turbine stage (46) is located radially inwardly of the other, the re-pressurisation device (36) further comprising fluid flow directing means (44) to direct a first portion of the fluid (40) through the compressor stage (42) and a second portion (54) through the turbine stage (46).

Abstract: The angular nature of corners 3 to roots 2 of a conventional blade 1 used in a gas turbine engine has resulted in relatively thick fan casings in order to contain any blade fragments from these corners 3 as a result of blade failure. By angling the end face 26 of the root 22 such that it is nearer to perpendicular to an axis of curvature 27 for a blade 21 the corners 23 are reduced in their angular nature. In such circumstances the potential for penetration of a fan casing through impingement with such corners 23 is reduced and the fan casing thickness can more confidently be thinned reducing overall weight. Furthermore by appropriate profiling of an aerofoil 24 adjacent to the front and trailing edges 20 of the aerofoil about the root 22 and face 26 further reductions in angular parts of the blade can be achieved.

Abstract: A ternary nickel eutectic alloy consisting of 4.5 to 11 wt % chromium, 1 to 6 wt % cobalt, 1 to 4 wt % aluminium, 0 to 1.5 wt % titanium, 0 to 3 wt % tantalum, 16 to 22 wt % niobium, 0 to 3 wt % molybdenum, 0 to 4 wt % tungsten, 0 to 1 wt % hafnium, 0 to 0.1 wt % zirconium, 0 to 0.1 wt % silicon, 0.01 to 0.1 wt % carbon, 0 to 0.01 wt % boron and the balance nickel plus incidental impurities.

Abstract: A blade arrangement (22) comprises an aerofoil (26) and a mounting support (28) to mount the blade arrangement to a disc. The aerofoil (26) is supported on the mounting support (28). The aerofoil (26) comprises a plurality of elongate aerofoil portions (34) arranged adjacent one another to provide the aerofoil.

Abstract: During friction welding a disc (10) is mounted on a support member (16). A cavity (18) is defined between the support member (16) and an internal surface (9) of the disc (10). The cavity (18) is filled with a low melting point alloy. The low melting point alloy solidifies and expands to form a compressed layer that provides a load path from the disc (10) to the support member (16). The compressed layer has a thickness of the order of 3 mm and allows for tolerances in the disc (10) whilst offering the required level of support during the subsequent welding operation.

Abstract: A duct installation, for example a casing 4 and an exhaust duct 8 of a gas turbine engine, comprises a main body 12 and an end section 14 of the casing 4 which are separable at a coupling including end flanges 18, 20. The end section 14 is axially slidable over the exhaust duct 8, taking with it a liner section 36, so as to provide access to the engine or to permit removal of the engine without disturbing the exhaust duct 8.

Abstract: A method of manufacturing a forging for forming a split casing comprising the steps of creating a forging, for example, by a ring rolling process and then deforming the forging by compressing it along a first axis and/or extending it along a second axis.

Abstract: With regard to components it is necessary to test specimens of materials in order to determine acceptability for objective component performance. Previously such testing generally involved fixing and clamping of the test specimen which produced artificial stressing conditions. By providing a specimen component typically in the form of an elongate member 2 which is suspended between mounting ends 3 a combination is provided which has inertia. In such circumstances when a projectile impacts upon the elongate member that elongate member flexes and deforms and this deformation can be monitored for testing purposes. The projectile 4 is arranged to have a relatively facile compliant nature upon impact with the component 2 such that there is no local stressing of the component whilst suspending the mounting ends substantially avoids clamp resilience distorting objective or realistic stressing conditions.

Abstract: An apparatus for determining a clearance between rotor blade tips of rotor blades mounted on a rotor and a stator lining mounted on a stator casing. The stator lining is movable radially relative to the stator casing. The stator lining comprises an abradable material. At least one probe is arranged to measure the clearance between blade tips and stator lining. A first portion of the at least one probe is arranged within the stator lining and a tip of the first portion of the at least one probe is arranged flush with the surface of the abradable material. The tip of the first portion of the at least one probe comprises an abradable material. A second portion of the at least one probe is secured to the stator casing. A wire-less and connector-less coupling transmits a measurement signal from the first portion to the second portion of the at least one probe to allow radial movement of the stator lining relative to the stator casing.

Abstract: A gas turbine engine comprising a rotor and a stator which define first, second and third cavities; the rotor and stator define a seal therebetween and which is located for sealing between the second and third cavities, the rotor comprises an aperture through which a gas flow passes from the first cavity to the second cavity characterized in that the seal comprises a deflector that extends axially over at least a portion of the aperture to deflect at least a part of the gas towards the rotor.

Abstract: In order to allow dual fuel operation, that is to say gas and liquid fuel, a fuel injection arrangement and an assembly are provided in which an injection conduit provides constriction to an airflow towards an outlet. In an assembly a plurality of arrangements including liquid fuel jets are arranged to such that through high angle incidents by the airflow appropriate vaporization and droplet formation is achieved for a fuel/air mixture combustible in a combustor of a turbine engine. At low liquid fuel flow rates below a pre-determined level the liquid fuel is atomised and entrained by the airflow. At high liquid fuel flow rates the fuel splash impinges upon a wash surface to develop a wash film which is again vaporised and atomised about an edge for a fuel/air mixture capable of combustion.

Abstract: A drive arrangement for driving, or for being driven by, a fluid is disclosed. The drive arrangement comprises a rotatable member (40) for receiving the fluid, and having mounted thereon a plurality of drive members (56). The drive members (56) are movable between a drive position, in which the drive members can drive, or be driven by, the fluid, and a non-drive position in which the drive members (56) are substantially prevented from driving or being driven by a fluid received in the rotatable member (40).

Abstract: A solid oxide fuel cell component (12) comprises a plurality of solid oxide fuel cells (24) arranged in spaced apart relationship, and in electrical series, on a surface of the porous gas permeable support structure (16). Each solid oxide fuel cell (24) comprises a dense gas tight electrolyte member (28), a porous gas permeable first electrode (26) and a porous gas permeable second electrode (30). Each electrolyte (28) is arranged in contact with a corresponding one of the first electrodes (26), each second electrode (30) is arranged in contact with a corresponding one of the electrolytes (28). Each of the first electrodes (26) is arranged in contact with the surface of the support structure (16). The interconnectors (32), the peripheral seal layer (34) and the electrolytes (28) are arranged to encapsulate all of the first electrodes (26) except for the surfaces of the first electrodes (26) in contact with the surface of the support structure (16) to prevent leakage of reactant from the first electrodes (16).

Abstract: A boss 10 is welded onto a thin casing 12. The casing 12 is held in a fixture (not shown) with a backing plate 20 adjacent surface 18. The backing plate 20 is located on the opposite side from the surface 14 onto which the boss 10 is to be welded. By using a backing plate 20 the depth of the weld zone, h, can exceed the casing thickness, t. The backing plate 20 is sacrificial and is released by removing the central part of the boss 10 where it has been bonded to the plate 20. Provided that the diameter D1 of the central part of the boss 10 exceeds the diameter of the bonded region D2 the plate 20 is released from the casing 12.