Abstract: An apparatus for measuring erosion of an edge of an aerofoil portion of a fan blade includes a laser source to direct light at a position on the edge of the fan blade. A detector detects light reflected from the position on the edge of the fan blade. A computer measures the distance from the laser source to points on the edge of the fan blade to produce a profile of the edge in terms of x and z coordinates. The computer calculates the distances of points on the edge of the fan blade from a centroid of the profile. The computer detects peaks in the distance of points from the centroid of the profile. The computer selects two peaks with the greatest distance therebetween. The computer determines the distance between the two peaks and compares the determined distance and a predetermined distance to determine if there is unacceptable erosion.

Abstract: The invention provides a method of forming a metal matrix composite (MMC) comprising a metal matrix and a fibrous material embedded therein, the method comprising bringing the metal matrix into the molten state and contacting the fibrous material with the metal matrix in the molten state in a directionally controlled manner, whereby the Young's modulus of the resultant cooled MMC is controlled in one or more particular direction and optionally at one or more particular location.

Abstract: A component is repaired by removing a damaged region to form a cavity, in which layered repair inserts are installed. The profile of the cavity, and of the exposed surface of each repair insert is measured to serve as the basis for the contact surface of each subsequent repair insert. The repair inserts are fused to the wall of the cavity and to each other in a process in which heated locations of each repair insert are successively heated to minimise heat transfer within the repair inserts and in the underlying substrate material. The repair inserts may be made in a powder bed process from an alloy powder having the same composition as the material of the substrate.

Abstract: Provided is a method for determining the presence of an alumina layer on a surface of a component. The method includes illuminating a surface of a component with radiation; detecting radiation emitted at a particular wavelength; analyzing the detected radiation; to determine the thickness of the alumina at at least one point on the surface of the component; and comparing the determined thickness of the alumina at the at least one point on the surface of the component with a predetermined thickness of alumina at that point to decide if the thickness of alumina at the at least one point on the surface of the component is satisfactory.

Abstract: The present invention relates to a sealing arrangement between a stator assembly and a rotor 12 of a gas turbine engine, the rotor 12 being rotatable about an engine axis, the stator assembly comprising vanes 22 provided at their radially inner ends with a vane support structure 28 which comprises an annular platform 30 supporting the vanes and a radial flange 32 which extends radially inwardly from the platform, the sealing arrangement comprising an array of leaves 36 which extend inwardly from the radially inner periphery of the flange 32, towards a circumferential sealing surface 13 of the rotor 12.

Abstract: A method of producing an integral self supporting coating test piece (16) from particulate material comprising the steps of (i) producing a reusable mould (10) having a depression (12) which conforms to the desired shape and volume of said coating test piece (16), the reusable mould (10) comprising silicone rubber, (ii) roughening the surface (14) of the reusable mould (10), (iii) heat treating the reusable mould (10), (iv) thermally spraying particulate material into the depression (12) in the reusable mould (10), and (v) removing the reusable mould (10) from the solidified coating test piece (16).

Abstract: An apparatus for generating vibrations in a component comprising a clamp assembly for clamping the component and a vibration generator for generating vibrations in the clamped component, the clamp assembly including: a base member, a pair of fixedly-spaced clamp members and a wedge for laterally wedging part of the component between the clamp members thereby to clamp the component. The base member, or a fixed clamp member, is inclined and the wedge having an inclined wedging surface arranged to engage the inclined base member or inclined fixed clamp member. The apparatus may form part of a test rig for vibration testing components such as turbo machine blades.

Abstract: A method of forming a hollow component with an internal structure from first and second panels includes the step of forming at least one protrusion on a surface of at least one of the first and second panels by a material deposition process. The first and second panels are assembled into a preform the panels being oriented such that each panel defines an interior and an exterior facing surface, with the at least one protrusion extending from an exterior facing surface of a panel. The preform is expanded against a die, such that the at least one protrusion is transferred from the exterior surface of a panel to the interior surface of a panel so as to define an internal structure. Forming the at least one protrusion may include encapsulating an elongate member on the surface of a panel by a material deposition process.

Abstract: A rotor disc 2 is provided with blade receiving recesses 40 at its outer periphery. The disc 2 has an internal cavity 34 for conveying cooling air to blades 4 retained in the recesses 40. Each blade-receiving recess 40 intersects the cavity 34 to provide communication between the cavity 34 and the recesses 40. The disc 2 may be made from separate disc components 12, 14 which define the cavity 34 between them.

Abstract: A method and associated system for managing power within an aircraft electrical system, the aircraft comprising a generator driven by a gas turbine engine for the supply of electrical power to the system, wherein the generator and electrical system are connected to a common energy store. The method comprises determining predicted electrical energy demands of the system and predicted thrust demands for the gas turbine engine over at least a portion of a flight. A plurality of time periods within at least said portion of the flight are defined and a desired rate of charge of the energy store for each time period is determined based upon the predicted thrust and electrical energy demands over said time period. The rate of charge of the energy store is controlled during the flight in accordance with the determined desired rate of charge for each time period.

Abstract: A compressor is provided for pressurising carbon dioxide produced by a carbon dioxide production plant and introducing the pressurised carbon dioxide to a carbon dioxide sequestration system. The compressor has a measuring system which determines the amount of carbon dioxide produced by the production plant. It also has a control system which varies the power of the compressor depending on the determined amount of produced carbon dioxide.

Abstract: The fragmentation of a bird or similar soft body, following its impact on an angled target plate, is modelled by representing the body as a combination of fragments and slurry, their relative proportions depending on the severity and angle of impact. The method is particularly suitable for modelling the behaviour of a bird striking an obscuring intake of a gas turbine engine.

Abstract: Seal arrangements utilizing leaf seal elements are susceptible to excessive wear at their tips due to blow-down pressures. When the seal element is forced against a rear surface across the pressure differential between the sides A, B of an arrangement. These tips may be forced into engagement with the rotating shaft and therefore wear on the shaft as well as at the tip occurs. By providing channels which extend laterally across more than one seal element pressure relief is maintained and therefore a limit to blow-down force maintained. The channels also extend radially and normally on a low pressure side of the seal arrangement.

Abstract: It is difficult to bend materials for forming beyond 180° in terms of bend angle due to the entrant nature of prior press forming arrangements including a press tool with a press recess of a static nature. By providing a press recess which is formed from actuators allowed to dynamically shift about a deflection member it is possible as a press tool engages and forces a material to be formed into the press recess to envelope the press tool and therefore achieve greater than 180° bending angles. The actuators are formed in a stack with alternate left right presentation of shaped receiving apertures which include an actuator surface 34 engaged by the material to be formed in order to cause the necessary deflections during the pressing process.

Abstract: A spray nozzle 10 for a laser deposition apparatus, comprises an elongate nozzle aperture 16, a powder supply chamber 18 in fluid communication with the elongate nozzle aperture and upper and lower elongate gas apertures 26, 28 located above and below the elongate nozzle aperture respectively and extending substantially parallel to the elongate nozzle aperture. In use the powder supply chamber supplies powder to the nozzle aperture under pressure so as to cause a wide powder stream to be ejected from the nozzle aperture and the upper and lower elongate apertures eject a wide gas stream above and below the wide powder stream. When used with a laser deposition apparatus 10 a relatively wide coating of a substantially uniform thickness can be deposited.

Abstract: The present invention relates to a flow discharge device (30) for discharging a flow of gas (F) from a first gaseous fluid (A) into a second gaseous fluid (B) which is of a lower pressure than the first gaseous fluid. The discharge device comprises a valve (34) disposed between the first and second gaseous fluids and arranged to regulate the discharge flow (F) and a swirler means (50) disposed between the valve (34) and the second gaseous fluid. The swirler means (50) comprises a plurality of radially extending circumferentially spaced vanes (61, 63, 65). In use the swirler means (50) swirls the discharge flow (F). This acts to reduce the energy, and therefore the pressure of the discharge flow. This results in quieter operation.

Abstract: A back-up featherer for an engine arrangement having a main hydraulic actuator which angularly displaces propellers of a propeller assembly of the engine arrangement, and fluid supply lines for transferring hydraulic fluid between a hydraulic pressure power source located on a static structure of the engine arrangement and the main hydraulic actuator. The back-up featherer has a back-up actuator assembly for angular displacement of the propellers, the back-up actuator assembly rotating with the propeller assembly, a signal detector operatively connected to the back-up actuator assembly and rotates with the propeller assembly, and a back-up rotating coupling. A static side of the back-up rotating coupling is mounted to the static structure of the engine arrangement and communicates with a regulator located on a static structure of the engine arrangement. A rotating side of the back-up hydraulic rotating coupling rotates with the propeller assembly and communicates with the signal detector.

Abstract: A spray nozzle 10 for a laser deposition apparatus comprises an array of nozzle apertures 16 arranged side-by-side, and a powder supply chamber 18 in fluid communication with the nozzle apertures 16. In use the powder supply chamber 18 supplies powder to the nozzle apertures 16 under pressure so as to cause a wide powder stream to be discharged from the array of nozzle apertures 16. When used with a laser deposition apparatus 100, a relatively wide coating of a uniform thickness can be deposited.

Abstract: Fuel injection apparatus 54, for a gas turbine engine, includes pilot fuel injection circuits 42 which supply pilot injectors 44 with fuel from a manifold 60, through a pilot control valve 46. The state of the control valve 46 is set by pneumatic pressure in the manifold 56. Main injectors 50 are supplied with fuel from the manifold 60 by main injection circuits 48, through main valves 52. The state of the main valves 52 is set by hydraulic pressure in a manifold 58. Accordingly, control signals to the valves 46, 52 are conveyed independently by means of the pneumatic manifold 56 and the hydraulic manifold 58.

Abstract: A component such as a turbine blade of a gas turbine engine has a cooling arrangement comprising a cascade impingement array in which cooling air flows from a supply chamber through impingement passages in webs to an internal passageway comprising first and second limbs. The cooling air flow through the limbs, provides improved heat transfer compared with continued impingement cooling in the chordwise direction of the blade.