Abstract: A method of grinding the tip of a blade which forms part of a rotor for a gas turbine engine is provided. The method includes mounting a plurality of blades in a disc to provide a blade assembly; mounting the blade assembly in a grinding apparatus; aligning the plurality of blades in a predetermined position using compressed fluid; and, grinding the blade tips.

Abstract: A protection system is provided for an electrical power network. The system has one or more circuit breaker arrangements which on activation isolate electrical faults within the network, and one or more fault detectors. The or each fault detector measures an inductance of a respective section of the network. The system is configured to activate one or more of the circuit breaker arrangements in response to measured inductances which are indicative of a fault.

Abstract: A method of connecting three-dimensional structured meshes to form a conformal mesh, for solutions of flow problems, including: forming an interface by overlaying surfaces of two structured meshes; defining an interface set of mesh points in the interface; merging mesh points in the interface set that are within a predetermined distance of each other and projecting mesh points of one mesh in the interface that are within a predetermined distance of a line of the other mesh; generating an interface layer in the form of an unstructured mesh; and inserting a node at the centre of each hexahedra, and producing an unstructured layer of cells between the two structured meshes by joining the nodes to the mesh points of the interface layer.

Abstract: A casing treatment for a fan or compressor stage 10 of a gas turbine engine comprises circumferential grooves 16A, 16B, 16C, 16D and 16E which extend in a series disposed between the leading edges 20 and trailing edges 22 of blades 6 of a fan or compressor stage 10. The grooves 16 vary in depth d in order to optimise the stall margin of the fan or compressor stage 10 while preserving peak efficiency.

Abstract: A lubrication and scavenge system for a gas turbine, capable continued operation in nose-down or nose-up orientations, has a number of oil drainage passages to return oil to one or more collection chambers adjacent a rolling element bearing. A rotary impellor in the chamber forces the oil into a scavenge off-take passageway in the chamber wall leading to a scavenge pump. However, in some orientations windage effects in the chamber can return the oil to the drainage passage rather than permitting the impellor to centrifuge it into the off-take passageway. As a result oil starvation may occur. To avoid this and improve scavenging a shield is located between the drainage path and the off-take passageway adjacent to a face of the impellor. The shield may comprise an additional member, but preferably is formed integrally with a bearing race so as to ease assembly.

Abstract: A gas turbine engine includes a fan, a bypass duct having a nozzle, through which fluid from the fan flows, and a variable area nozzle device located in the nozzle. The variable area nozzle device has an arcuate fairing having one end in slidable cooperation with the bypass duct. In a deployed position the area of the nozzle is reduced from that when stowed, thereby improving engine operability and efficiency.

Abstract: An aeronautical propulsor has a core engine, one or more open rotors driven by the engine, and a nacelle which encloses the core engine and provides an aerodynamic external surface. At least a portion of the external surface of the nacelle is acoustically treated to attenuate noise produced by the open rotors.

Abstract: This invention relates to a magnetic gearbox, comprising: an inner rotor having a first plurality of magnetic flux sources; an outer rotor having a second plurality of magnetic flux sources; and, a modulator having a plurality of pole pieces positioned between the first and second magnetic flux sources and separated from each by an air gap, wherein upon relative rotation of the inner rotor, outer rotor and modulator the first and second magnetic flux sources and pole pieces are arranged to provide a modulated magnetic field in the air gap adjacent each rotor; wherein either or both of the modulator and inner rotor include at least one nozzle for directing fluid radially across the respective air gap so as to impinge on the adjacent rotor or modulator.

Abstract: An erosion testing assembly adapted to test an abradable surface of a component, the testing assembly including: a shroud attachable to the component; the shroud being adapted to receive an erosion gun. The present disclosure also relates to a method of testing an abradable surface of a component, wherein the method includes: attaching a shroud to the component; connecting an erosion gun to the shroud; and testing the abradable surface with the erosion gun. The present disclosure may also relate to a method of testing an abradable surface of a component, wherein the method includes: using the component; and testing a portion of the abradable surface with an erosion gun after use of the component.

Abstract: A fan casing for a gas turbine engine has a fan track liner extending only over an upstream part of the fan blades, and the local stiffness and internal shape of the casing are arranged to promote the break-up of a released fan blade while permitting the leading edge region of the blade to pass through the fan track liner and be contained by the fan casing. This arrangement is particularly suitable for fan blades in which the stiffness and compressive strength are significantly higher in the leading edge region than in the remainder of the blade; for example, hollow metal fan blades or composite fan blades having a metal leading edge cap.

Abstract: A vibration damper assembly for damping non-synchronous vibration between adjacent, spaced apart components comprises a vibration damper located in both of a pair of generally confronting passages in each of the components. The assembly comprises at least two spaced apart articulation surfaces for contact between damper and component, each of the articulation surfaces is arcuate in a first direction and is characterized by having a substantially linear portion in an orthogonal and second direction. Thereby the contact area is greatly enlarged and material loss minimized. The cross-sectional shape of the damper or passage is non-circular and there is a clearance between the damper and passage sufficiently small to prevent rotation of the damper in the passage during use.

Abstract: A rotor blade has a radially extending aerofoil body having pressure and suction sides. The rotor blade further has squealer tip. The squealer tip includes a peripheral wall surrounding a cavity which is open at the radially outward end of the blade and at the trailing edge of the aerofoil body. The peripheral wall has at least one first region which extends radially from the aerofoil surface which has a first outer surface. The peripheral wall further has, along at least part of at least one of the pressure and suction sides, at least one second region inclined outwardly of the cavity with respect to the radial direction of the blade which has a second outer surface which extends obliquely outwardly of the blade. A radially outer portion of the second outer surface turns towards the radial direction to truncate the outward extension of the second outer surface.

Abstract: A bearing race for a rolling-element bearing, the race comprising: a circumferential channel which defines a raceway, wherein the raceway comprises a base portion and first and second side portions; and an oil scavenge passageway extending through the race from a boundary between the base portion and the first and/or second side portions of the raceway to an external surface of the race.

Abstract: A mechanical joint for joining two components, the joint having a male part on one component and a corresponding female part on the other component. The male and female parts have respective castellations which intercalate on insertion of the male part into the female part along a direction of insertion. Respective abutment surfaces are formed on the projections of the castellations. The castellations are configured such that, after the insertion of the male part into the female part, the male and female parts can be rotated relative to each other around the direction of insertion to bring: (i) the abutment surfaces into facing alignment and thereby prevent the parts from being pulled apart, and (ii) the indentations of the castellations into facing alignment. The joint has one or more locking members which are insertable into the facing indentations to prevent further relative rotation of the male and female parts.

Abstract: A method is provided whereby confidence in a validation parameter set is achieved by comparison with a known sample of a parameter in terms of the expected template comparison score as well as mean values and deviation from that score. Thus, with respect to user individual identification, biometric parameters such as fingerprint or handwriting or voice recognition can be utilised to compare the stored template for that individual with the putative biometric response in order to determine deviation from the mean. Previous systems provided a stored template and then ranging either side to simply give a pass/fail response. By adaptation of the ranging quotient for a particular individual, a percentage confidence in the pass/fail response can be achieved. For example an individual -may have a wider range of deviation than another individual and therefore close repetition of the biometric data may be indicative of a lower percentage confidence than with an individual with a narrower deviation.

Abstract: A method of manufacturing a component, the method including the steps of: providing a component having a first portion, which first portion defines a cavity, characterized by; identifying a first frequency response of the first portion and/or the entire component, and introducing material into the cavity to achieve an adjusted frequency response of the first portion and hence a desired frequency response of the component.

Abstract: An arrangement for controlling flow of fluid to at least one component of a gas turbine engine, the arrangement includes a first conduit for providing fluid to the component; a flow valve, for controlling the flow of fluid in the first conduit, having first and second configurations; a second conduit for providing fluid to the flow valve to the control the configuration of the flow valve; and a magnetic valve, for controlling the flow of fluid in the second conduit, having first and second configurations and including at least one ferromagnet forming a portion of a magnetic circuit; the member comprising ferromagnetic material is thermally coupled to one of the group comprising the fluid in the first conduit, the fluid in the second conduit and the component; and the configuration of the flow valve is dependent on the configuration of the magnetic valve.

Abstract: A method of forming a blade assembly for a gas turbine engine, the method comprising mounting turbine blades on a rotor in a number of radial stages. Sacrificial supports are placed on the blades, and nozzle guide vanes are located on the supports. The rotor is introduced into a casing, and the guide vanes are mounted to the casing.

Abstract: A gas turbine engine has in flow series: a compressor section, a combustor, and a turbine section. The engine further has a steam generator, and a water and steam delivery system. During an engine start-up period, the delivery system delivers liquid water to the combustor and mixes the delivered water in its liquid state with working gas in the combustor. After the start-up period, the delivery system accepts steam from the steam generator, delivers the steam to the combustor and mixes the delivered steam in its gaseous state with the working gas in the combustor.

Abstract: An apparatus for characterizing the fragmentation of a body following impact with a surface, particularly the fragmentation of a bird following impact with part of an intake of a gas turbine engine, comprises a gun, a target plate, a soft recovery plate across which the body's trajectory can be tracked, and a soft recovery system, characterized in that damage to the body is caused substantially only by the impact on the target plate.