Abstract: A guide 2 for a burr cutter 34, the guide 2 comprising: a body portion 4 having first and second guide surfaces 12a, 12b which are spaced from one another to define a slot 14 between the first and second guide surfaces 12a, 12b; a bearing 32a, 32b for rotatably mounting the body portion 4 to a shank 38 of the burr cutter 34 with a cutting head 36 of the burr cutter 34 adjacent the slot 14; wherein the first and second guide surfaces 12a, 12b and the bearing 32a, 32b are positioned relative to one another such that the first and second guide surfaces 12a, 12b are tangential to the cutting head 36 of the burr cutter 34.

Abstract: A fluted drill comprises, in axial sequence, a body portion, and a cutting portion. The cutting portion comprises two or more cutting edges, with each cutting edge extending from a distal end of the cutting portion, along the cutting portion towards the body portion, to the body portion. Each cutting edge has a first rake angle at the distal end of the cutting portion, progressively increasing to a third rake angle at a proximal end of the cutting portion. Each cutting edge has a first uncut chip thickness at the distal end of the cutting portion, progressively decreasing to a third uncut chip thickness at the proximal end of the cutting portion.

Abstract: A fan casing assembly comprising an annular casing member for circumferentially surrounding a fan, and an annular fan track liner comprising a plurality of circumferentially adjacent liner panels. The annular fan track liner is positioned radially inward of the annular casing member. A tilting arrangement is provided and configured to selectively circumferentially tilt one or more of the liner panels, such that, in the event of a fan blade being released from a fan, the tilting arrangement can initiate tilting of one or more liner panels so that the liner panels can trim one or more of the remaining fan blades.

Abstract: An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.

Abstract: A method of, and apparatus for, urging blades of a gas turbine engine radially outwardly is disclosed. The method may be used to grind blade tips of blades of a rotor stage of a gas turbine engine. The method comprises locating a fluid-tight bag which is in a radial gap formed between a radially inner surface of a respective blade root and a slot in a disc which the blade root cooperates. The method comprises inflating the fluid-tight bag and rotating the rotor stage relative to a grinding surface so as to grind any blade tips that contact the grinding surface during rotation. This results in more accurate positioning of the blades during the grinding process and/or during operation.

Abstract: The present disclosure relates to a method of heat treating a component (e.g. a combustor tile) which may be formed of a first material e.g. a nickel superalloy. The component may be formed using an ALM method. The method comprises enclosing at least part of the component in a foil envelope which may be formed of a second material wherein the second material (e.g. stainless steel) is more susceptible to reactive oxidation than the first material. Next the envelope is purged with an inert gas (e.g. argon) and the envelope is sealed. The component is then heated e.g. using hot isostatic pressing.

Abstract: A rotary abrasive machining tool (101) is shown. The tool comprises a hub (103) having plurality of axially-oriented radial slots in the outer circumference thereof, and plurality of abrasive segments each of which is located in a respective slot in the hub and which form an abrading surface (102). The abrasive segments comprise a tab for location in a slot in the hub, and an abrading edge defining a plurality of abrasive elements.

Abstract: An electrical machine has a stator with windings, first and second rotors, and an electrical output regulator. The first rotor carries alternating polarity first field magnets, such that, on drive mechanism rotation, the windings interact with the magnetic flux produced by the first magnets to create an EMF. The second rotor carries alternating polarity second field magnets, and has first and second rotational positions to reduce and increase, respectively, the magnetic flux energy. The electrical output regulator regulates a current from the windings to produce a torque on the rotors, as the drive mechanism increases from zero rotational speed, the torque rises above a threshold level that moves the second rotor from the first to the second rotational position, and, as the drive mechanism further increases the rotational speed, the torque peaks and then drops below the threshold level to move the second rotor back to the first rotational position.

Abstract: The present disclosure relates to a method for processing a component formed by an ALM method using a ??-strengthened superalloy having a ?? solvus temperature. The processing method comprises heating the component to a treatment temperature at or above the ?? solvus temperature at a rate equal to or greater than 50 ° C./min and then cooling the component at a rate of greater than 60° C./min.

Abstract: A method is provided of producing a tooling to be used for manufacturing a rigid panel formed of polymer matrix composite material. The panel is for attachment to a gas turbine engine and has a curved shape which allows the panel to be wrapped around at least a part of a circumference of the engine. The panel has plural electrical conductors and/or fluid passages embedded therein. The tooling is either a mould against which the polymer matrix composite material can be moulded to manufacture the panel, or a pattern from which such a mould can be formed. The method includes: providing a plurality of separate tooling segments, each of which corresponds to a respective region of the curved shape of the panel; and joining the tooling segments together to produce the tooling.

Abstract: A Cold spray nozzle assembly for depositing powder material onto a component surface includes a primary spray nozzle, two or more secondary spray nozzles, and a support mechanism supporting each spray nozzle. Each spray nozzle deposits powder material on a single target point on the surface, a reference plane being defined normal to a surface plane at the target point. The primary nozzle is in a primary plane that is normal to the surface plane, and that defines a primary dihedral angle with the reference plane. An axis of the primary nozzle defines a primary nozzle angle with the surface plane. Each of the secondary spray nozzles is in a corresponding secondary plane, with each being normal to the surface plane and defining a respective secondary dihedral-angle with the reference plane. An axis of each secondary spray nozzle defines a respective secondary nozzle angle with the surface plane.

Abstract: A method of analysing blade tip displacements (dijk) derived from a rotor having an array of blades that rotate at a rotational speed (?). The blades are monitored by an array of stationary timing probes for at least two revolutions (j) of the rotor. Define asynchronous displacement (dijk_A) as a sum of a sinusoidal term (Va) and an offset per probe term (Oo). Define synchronous displacement (dijk_S) as a sum of a sinusoidal term (Vs) and a common offset term (Cc). Solve the asynchronous displacements (dijk_A) using the blade tip displacements (dijk) to give asynchronous amplitude (|a|), offset per probe (ok) and asynchronous residuals (rijk_A). Solve the synchronous displacements (dijk_S) using the blade tip displacements (dijk) to give synchronous amplitude (|s|), common offset (cj) and synchronous residuals (rijk_S).

Abstract: An oil cooling system for an engine includes an oil input line configured to receive heated oil from a component, an oil cooler configured to cool oil and direct oil to an oil return line and a first bypass line configured to selectively bypass oil from the input line to the return line without passing through the oil cooler. The first bypass line includes a first oil pressure actuated valve urged toward a closed position, and configured to move toward an open position where a pressure differential across the valve exceeds first predetermined pressure. The first bypass line further includes a second oil pressure actuated valve urged toward an open position, and configured to move toward a closed position where pressure differential across the valve exceeds a second predetermined pressure. The second predetermined pressure is greater than first predetermined pressure, and the first and second valves are provided in series.

Abstract: A turbine blade has a body enclosing a labyrinth of internal channels for circulation of coolant received through an inlet integrally formed in terminal portion of blade root. The labyrinth includes; inlet arranged on an axially upstream face of terminal portion leading to an upstream duct portion having first section adjacent the inlet and a second section axially downstream of first, second section having reduced cross section compared to first section. Leading edge passage intersects first section and extends through blade body towards the tip. Main blade passage intersects second section. Trailing edge passage intersects downstream duct portion which is in axial alignment with but separate from second section and channel connects second section with the downstream duct portion. Channel has reduced cross section compared to second section and downstream duct portion. The inlet has an inverted keyhole shape with cross section extends through upstream duct portion first section.

Abstract: A component including a substrate with dielectric coating on the substrate. The electrical reactance of the dielectric coating configured for the propagation of electromagnetic surface waves. The dielectric coating is arranged as a plurality of discrete pathways. Also a signal transmission system including a component, an electromagnetic surface wave transmitter coupled to the substrate, and an electromagnetic surface wave receiver also coupled to the substrate.

Abstract: A clearance control arrangement (26) for a rotor (28), the arrangement comprising a rotor and a casing (32) radially outside the rotor. An annular array of segment assemblies (33) mounted to the casing and radially spaced from the rotor by a clearance (42). Each segment assembly comprising a heat transfer cavity (48) radially adjacent to the casing. A birdmouth cavity (66) towards the rear of the segment assembly. A bypass hole (68) configured to deliver air to the birdmouth cavity to reduce the amount of air which leaks from the heat transfer cavity to the birdmouth cavity.

Abstract: A clearance control arrangement (26) for a rotor (28) comprising a segment assembly (33) spaced radially inwards from a casing (32) and defining a radial clearance (42) between the rotor (28) and the segment assembly (33). A front carrier (35a) and a rear carrier (35b) supporting the segment assembly (33). A heat transfer cavity (48) formed between the carriers (35a, 35b), the segment assembly (33) and the casing (32). A settling chamber (60) formed adjacent to the casing (32) and upstream of the heat transfer cavity (48). The clearance control arrangement (26) is configured to receive air into the settling chamber (60) and thence to deliver it to the heat transfer cavity (48).

Abstract: For forming a shell mould for investment casting, first and second core components are provided. These are formed of ceramic material. The core components are assembled together for manufacturing a wax pattern containing the core component for formation of a shell mould for investment casting. The core components have an arrangement of precursor location features. The method includes machining at least one of the precursor location features to a required shape to provide an arrangement of final location features. The core components are then positioned with respect to each other and/or with respect to a wax pattern die by contacting the arrangement of final location features with corresponding positioning features of a receiving device and/or the wax pattern die.

Abstract: A rotor for a turbo-machine, the rotor having a rotational axis and circumferentially spaced-apart radially extending blades of aerofoil configuration, each blade having a suction side, an oppositely directed pressure side, and a pair of oppositely directed snubbers each of which extends from a respective side towards a circumferentially adjacent blade and presents an abutment surface for abutment with the abutment surface of a respective adjacent snubber extending from the adjacent blade. Each snubber is configured such that its abutment surface makes an acute snubber angle to the axis of rotation. At least one pair of adjacent snubbers are configured such that their abutment surfaces are at an equal first snubber angle, with all of the other snubbers being configured such that their abutment surfaces are at equal second snubber angles. The first snubber angle is larger than the second snubber angle.

Abstract: A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system is disclosed. The compressor tip injector system comprises a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system. The compressor case comprises one or more injectors of the compressor tip injector system through which in use air from the cabin blower compressor is injected towards blade tip ends of blades of the compressor as they rotate.