Abstract: An actuator (12) is disclosed for example controlling gas flow in a gas turbine engine. The actuator (12) comprises a first portion (14) having shape memory properties, and a second portion (16) formed of substantially the same material as the first portion and having reduced shape memory properties relative to the first portion. The first portion (14) is movable from a first position to a second position at a temperature above the phase transition temperature of the shape memory material of the first portion (14). The second portion (16) is arranged to urge the first portion (14) from the second position to the first position at a temperature below the phase transition temperature of the shape memory material.

Abstract: A method of growing a single crystal seed bar (10) in which a mold provided with a grain selector filter (16) above a starter chamber is filled with molten metal, whereupon the metal is allowed to solidify slowly upwardly from the starter chamber. The filter (16) is provided with a pattern of openings, with the diameter of the openings being at least as large as the primary dendrite tip radius of the metal, but smaller than half the primary dendrite arm spacing.

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. While 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: Electrical machine arrangements have advantages with regard to providing local electrical power and starting. Embedding such electrical machine arrangements in machinery such as gas turbine engines is advantageous in removing mechanical linkages and reducing aerodynamic drag. However, the components utilized must be able to withstand harsh environmental conditions and therefore the DC link capacitor used for smoothing of voltage fluctuations are limited to relatively low capacitance densities. Low density DC link capacitors require large sizes which render electrical machines less acceptable for embedded usage. By providing offset of electrical current in inductance elements such as stator windings and stator coils of electrical machines in dead periods of the cycle a reduction in DC link capacitor requirements is achieved reducing the size, weight and complexity of installing electrical machines in gas turbine engines.

Abstract: A nose cone assembly is provided comprising a nose cone 104, a support ring 106 on which the nose cone 104 is mounted, and an insulating layer 110 disposed between the nose cone 104 and the support ring 106, the insulating layer 110 at least partially comprising glass fibres. A composite nose cone is also provided comprising an attachment region A, in which composite fibres are oriented substantially perpendicular to an axis of rotation of the nose cone 104, and an impact region I, in which composite fibres are oriented substantially parallel to the axis of rotation of the nose cone 104. Also provided is a support ring 106 for a nose cone assembly, the support ring 106 comprising an annular main body 140 and an annular projecting attachment flange 142, the attachment flange 142 terminating in a plurality of circumferentially spaced attachment tabs 144, wherein the attachment flange 142 forms with the main body 140 a cross section having at least two C curves 160, 162.

Abstract: A fixture for securing a cylindrical or shell thin-walled component includes a support having one or more securing devices for securing the component to the support. The fixture also includes an inflatable pressure element which, in use, is positioned within the secured component and is adapted to press outwardly, when inflated, against a liner inserted between the pressure element and the inner thin wall of the component. The liner has one or more elastic members, which bias it against the outward expansion of the inflated pressure element. The inflated pressure element and the liner damp vibrations in the component during machining of the outer side of the thin wall.

Abstract: A nose cone assembly 102 is disclosed, comprising a one piece nose cone 104 and a support ring 106 on which the nose cone 104 is mounted. The support ring 106 comprises a plurality of circumferentially distributed resilient attachment tabs 114, via which the nose cone 104 is mounted on the support ring 106. The support ring 106 further comprises a load spreader 122, and each of the resilient attachment tabs 114 is operably connected to the load spreader 122, such that deflections and forces experienced by any one attachment tab 114 are distributed to other attachment tabs 114 via the load spreader 122.

Abstract: A gas turbine engine blade containment arrangement comprises a casing, a first layer of cellular material arranged within the casing, a septum layer within the first layer of cellular material, a second layer of cellular material within the septum layer, a strong and ductile layer within the second layer of cellular material and a layer of abradable material within the strong and ductile layer.

Abstract: A tool and method for capturing information gathered during an analysis project is provided. The tool comprises a storage means for storing the analysis information generated or acquired during progress of an analysis project, wherein the analysis information is in the form of a plurality of graphical representations. Each graphical representation denotes a plurality of entities under analysis and the plurality of graphical representations comprises at least one representation of a first kind and at least one representation of a second kind. Input means is provided to allow a user to generate each graphical representation using a first or second predetermined structure according to its kind, said graphical representations being arranged for storage as a plurality of graphical representation files in the storage means.

Abstract: A method of manufacturing a component having first and second layers, the first and/or second layers including one or more depressions provided on a surface of the respective layer. The method including: arranging the first and second layers so that they face one another and with the depressions on inner facing surfaces of the layers; diffusion bonding the first and second layers together about their edges; applying a first differential pressure across each of the first and second layers to evacuate an inner space defined by the layers, thereby forming one or more depressions on an outer facing surface of the first or second layer; and applying a second differential pressure across each of the first and second layers to expand the inner space defined by the layers.

Abstract: With regard to gas turbine engines it will be appreciated that blades are typically cooled in order to ensure that the materials from which the blades are formed remain within acceptable operational parameters. Coolant is judiciously used in order to maintain engine operational efficiency. Unfortunately with regard to rotor blades horseshoe vortices tend to increase heating towards a pressure side of a blade resulting in localized overheating. Such localized overheating may result in premature failure of the blade component. Traditionally coolant flows have been presented over a forward projection of a blade platform. In such circumstances coolant flow will not be used as efficiently as possible with regard to protecting a pressure side of a platform in a blade assembly and arrangement. By provision of a deflector element on the forward blade platform coolant flow can be proportioned either side of a leading edge of the blade.

Abstract: Provision of panels within casings can cause problems where retaining bolts require apertures in the casings, which in turn may reduce the structural strength of that casing. By providing a ring within the casing and appropriate retainer elements secured to that ring, which elements in turn appropriately present panels, it is possible to provide a casing assembly which avoids the necessity of drilling or otherwise forming holes in the casing. Dam elements can be provided at each end of the assembly to prevent axial movement and therefore retain panel position within the casing.

Abstract: A method of manufacturing a rotating component, the method comprising the providing a component comprising a first portion, which first portion defines a first cavity, characterised by; identifying a first inertial property of the first portion and/or the entire component, introducing material into the first cavity to achieve an adjusted inertial property of the first portion and hence a desired inertial property of the component. A rotating component including a first portion defining a first cavity, a second portion defining a second cavity, the second portion being circumferentially spaced from said first portion, the first cavity has a first material deposit therein, said material having predetermined inertial characteristics so as to adjust the centre of mass (Z) of the rotating component.

Abstract: The invention is related to a fastener assembly of the kind used to secure a gas turbine engine rotor disc assembly on a shaft in a situation which otherwise would required the use of a trapped nut. It thereby removes a design constraint limiting bore diameter of the disc assembly to permit access to a securing nut on the shaft, and avoids the use of a trapped nut. One of the rotors hubs is adapted to be mounted on the shaft and the securing nut is engaged with a thread on the shaft to trap the hub. In the improvement of the invention the hub is provided with an axial keyway through which the securing nut is passed into the limited access space. Once the shaft is engaged with the hub the nut is then engaged with the thread on the shaft and tightened using a special tool extending through the centre of the shaft. The tool is withdrawn after use. The nut may be undone and retrieved in an opposite operation.

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: A method of inspecting an article, comprising applying an organic liquid substance over at least a portion of the article to be inspected so as to form a surface layer thereon, wherein said surface layer is luminescent. The article is irradiated with the surface layer thereon; and, scanning the article to determine its shape.

Abstract: A component (10) and method for manufacturing a component. The component comprises first and second panels (16, 18) spaced apart from each other, the first panel (16) having at least one protrusion (20) extending therefrom towards the second panel (18). The protrusion (20) extends partially across the space (19) between the first and second panels so as to define a free end of the protrusion. The free end is surrounded by damping material (24).

Abstract: A blade for a turbomachine extends in use, in a radial direction relative to the axis of the turbomachine. The turbomachine has at least one operating condition which generates supersonic fluid flow at the blade. The blade is adapted to provide, at the supersonic operating condition, a leading edge sweep angle which varies such that successive radial positions (i) to (iii) along the leading edge are at respective sweep angle turning points. Position (i) is the radially inner and position (iii) the radially outer of the positions. Position (i) is at or radially outward of the 30% span position, where 0% span is the radially innermost point of the leading edge and 100% span is the radially outermost point of the leading edge.

Abstract: This invention relates to a superconductor device, comprising: a superconductor; a former which supports the superconductor; and, an intermediate electrical connector attached to the former for coupling the superconductor to a power source, wherein the intermediate electrical connector is connected to the superconductor via a deformable portion in the intermediate electrical connector, wherein the deformable portion allows relative movement between the superconductor and former.

Abstract: A hollow component is adjusted in shape, for example to correct circularity, by means of a shape adjusting tool. The tool comprises a base structure 2 on which adjuster elements 6 are guided. An adjustment ring 8 has a ramp surface 26 corresponding to each adjuster element 6 so that rotation of the adjustment ring 8 causes radial displacement of the adjuster elements 6. The adjuster elements 6 are displaced in unison, and engage the internal surface of the component to be adjusted so as to deform the component to the desired shape. The segments 20 are interconnected by rigid links 32 and a single flexible link 34, and are supported on baring rollers 36 mounted on the base structure 2.