Abstract: A method of testing the oxidation resistance of an alloy includes applying a layer of salt on the alloy's surface and placing the alloy in a furnace at a temperature of at least 1000° C. and containing an oxygen containing gas. The alloy is maintained in the furnace at the predetermined temperature for a period of time then the alloy is removed from the furnace and the alloy is to cool to ambient temperature or other suitable temperature. These steps are repeated for a number of times to maintain the salt on the alloy's surface at a level of 0.5 to 30 ?g cm?2 h?1. The alloy is weighed periodically to determine oxidation resistance. The addition of salt reduces the time to test the oxidation resistance of the alloy and the addition of the salt mimics the degradation of the alloy in a real working environment in a gas turbine engine.

Abstract: A method for friction welding of inter alia coarse grain superalloy components, involving conditioning a shear zone of components to be welded by; a) pre-determining temperature profile for which the material of the shear zone of the components approaches viscoplasticity but does not undergo undesirable phase transformations, b) introducing friction at one or both surfaces of the components to be welded to provide a pre-defined quantum of energy sufficient to generate a peak temperature of the temperature profile at that surface whilst simultaneously applying pressure to the surfaces which is below a pressure which will cause upset at the surface, c) withdrawing the friction and/or pressure allowing the heat to disperse by conduction through the shear zone; d) after the temperature at the surface falls below peak temperature, repeating steps b) and c); and repeating step d) as necessary until the pre-determined temperature gradient is achieved throughout the shear zone.

Abstract: A method for the manufacture of a component of defined geometry from two or more materials using a powder bed ALM process includes providing a bed of a first powdered material, selectively fusing portions of the first powdered material to build up a first three dimensional portion of the component geometry and fusing a powder containment bund from the first material to contain unfused first powdered material. A bed of a second powdered material is deposited onto the powder containment bund and selectively fused to build up a second three dimensional portion of the component geometry. Unfused first powdered material can subsequently be removed from a first side of the bund and unfused second powder from a second side of the bund. Remaining parts of the bund which do not form part of the defined geometry of the component can be removed to provide the net shape component.

Abstract: A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. The retainer plate is formed from fiber-reinforced composite material, at least a portion of the composite material being reinforced by 3D-woven fiber tows.

Abstract: An aerofoil component defines an in use leading edge and a trailing edge. The leading edge has at least one serration defining an apex and a nadir. The leading edge has a generally chordwise extending slot located at the nadir of each serration.

Abstract: A gas turbine engine has two connected parts that rotate together during use. The two parts have a tensile loading that acts to separate the two parts in use. The two parts may be neighbouring rotating stages of a gas turbine engine. The two parts are connected together using both a mechanical fastener and an interlocking feature. The interlocking feature may be, for example, interlocking conical surfaces and/or interlocking protrusions.

Abstract: A component 2 for a bearing, the component 2 comprising a bearing surface 4, wherein the bearing surface 4 is formed so as to be tapered at rest, thereby offsetting deformation of the bearing during an operational condition which generates an induced angle in the bearing surface 4 or an opposing surface of the bearing. A method of manufacturing a bearing is also provided. The method comprises: determining an induced angle of a component 2 of the bearing caused by deformation of the bearing during an operational condition: and providing a surface 4 of the component 2 or an opposing component with a taper at rest so as to offset the induced angle generated during the operational condition.

Abstract: A combustion staging system includes a splitting unit receiving a metered fuel flow and controllably splitting the received flow into pilot and mains flows. Pilot and mains fuel manifolds distribute fuel. A cooling flow recirculation line provides a cooling flow to the mains manifold during pilot-only operation, and a return section to collect mains manifold cooling flow. The cooling flow enters a delivery section and exits the return section. A fuel recirculating control valve on the delivery section has an open position so that the cooling flow enters the delivery section during pilot-only operation; a shut off position prevents the cooling flow entering the delivery section through the cooling flow orifice during pilot and mains operation. A supplementary valve bleeds or feeds cooling flow. The mains manifold cooling flow pressure is determined by the cooling flow and pressure raising orifices flow numbers, and a control setting of the supplementary valve.

Abstract: A combustion chamber arrangement has an annular outer wall and an annular inner wall having an upstream row of tiles and a downstream row of tiles. The outer wall has a concave bend which is less than 175°. The downstream end of the upstream tiles and the upstream end of the downstream tiles are adjacent the concave bend. The downstream ends of the upstream tiles are spaced at a greater distance from the inner surface of the annular outer wall than the upstream end of the downstream tiles. The upstream tiles have curved lips extending in a downstream direction which overlap but are spaced radially from the upstream ends of the downstream tiles. The outer wall has a row of apertures to direct coolant onto the outer surfaces of the curved lips and the upstream tiles has a row of apertures extending to the inner surfaces of the curved lips.

Abstract: A boroscope includes a working head having first and second ends. A first optical fiber extends through the boroscope to a position between the first and second ends. A second optical fiber extends through the boroscope to the second end of the working head. A laser optical fiber extends through the boroscope. At least one lens is arranged between the first end and the second end of the working head and a mirror is gimballed to the second end of the working head. The laser optical fiber directs laser light transmitted through the laser optical fiber onto the lens and then onto the mirror. A first LED is arranged at a position between the first end and the second end of the working head and a second LED is arranged at the second end of the working head and an actuator devices adjust the position of the mirror.

Abstract: The invention concerns an aircraft propulsion control system in which a gas turbine engine has an actuable flow opening for control of flow to or from a portion of the engine. One or more sensor is arranged to sense a condition indicative of vapor trail formation by the exhaust flow from the engine. A controller is arranged to control actuation of the flow opening so as to reduce the efficiency of the engine upon sensing of said condition by the one or more sensor. In one example, the flow opening is a variable area fan nozzle.

Abstract: An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler is substantially entirely formed from a polymer matrix composite material. It has an outer lid which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and a support structure which is connectable to the rotor disc to support the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. In use, under centrifugal loads, the opposing support walls resiliently deform to allow outward radial movement of the lid. Each support wall is thickened in a region neighboring the attachment strap.

Abstract: A fuel injector comprises a swirler and the swirler comprises a plurality of vanes, a first member and a second member. The second member is arranged coaxially around the first member and the vanes extend radially between the first and second members. The vanes have leading edges and the second member has an upstream end. The leading edges of the vanes extend with radial and axial components from the first member to the upstream end of the second member and the radially outer ends of the leading edges of the vanes form arches with the upstream end of the second member. The arrangement of the swirler enables the fuel injector to be built by direct laser deposition.

Abstract: A panel connection assembly connects a panel to a casing including hanger, first locating, and second locating plates. The hanger plate has elongate body, first end, and opposite second end portions, with each of the first and second end portions having a circular profile. The hanger plate has a dumbbell shape. The first locating plate has a first circular locating aperture, the first locating aperture to accommodate the first end portion, and the second locating plate has a second circular locating aperture, the second locating aperture to accommodate the second end portion. In use, the first locating plate is secured to the casing, the second locating plate is secured to the panel, the first and second end portions are respectively accommodated within the first and second locating apertures with the elongate body portions extending therefrom, to connect the panel to the casing.

Abstract: An engine fuel control system is provided, including a supply line for the supply of fuel to a fuel metering valve which controls the flow of fuel to burners of an engine. Fuel is delivered at a first high pressure to the supply line by a pump arrangement. The engine fuel control system includes a restrictor located in the supply line for passage of the fuel delivered by the pump arrangement therethrough. The restrictor is configured such that fuel exiting the restrictor for onward supply to the fuel metering valve is at a second high pressure which is lower than the first high pressure. The engine fuel control system includes pressure limiting valves which actuate when the pressure difference between the first high and low pressure reaches a predetermined level to open a flow path for fuel on the supply line to by-pass the restrictor, thereby limiting the pressure difference.

Abstract: An aircraft cabin blower system is described having a hydraulic circuit comprising a first hydraulic device and a second hydraulic device. The first hydraulic device is mechanically coupled to a cabin blower compressor and the second hydraulic device is arranged in use to be mechanically coupled to a spool of a gas turbine engine. The first hydraulic device is capable of performing as a hydraulic motor and the second hydraulic device is capable of performing as a hydraulic pump. When, in use, the system is operating in a cabin blower configuration, a driving force supplied by the spool of the gas turbine causes the second hydraulic device to pump liquid provided in the hydraulic circuit and thereby to drive the first hydraulic device, which in turn rotates the cabin blower compressor.

Abstract: An electrical harness assembly is provided that comprises a flexible printed circuit electrically connected to one end of an electrical connector. The other end of the electrical connector is presented for connection to another electrical component. Electrical tracks or conductors in the flexible printed circuit terminate in receiving holes. The electrical connector comprises terminals, each of which has a first end that is received in one of the receiving holes to form a connection formation, and a second end which is present for connection to the other electrical device. The connection formation is encapsulated so as to be sealed, thereby providing a reliable and robust connection between the connector and the flexible printed circuit.

Abstract: This invention relates to a laminated core for an electrical machine, including: a plurality of laminations configured to define a channel in a surface of the laminated core for the flow of a cooling fluid, wherein the channel has a base and at least one side wall, the at least one side wall having a stepped profile.

Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element and one or more arcuate fence elements positioned between the first and second casing elements. Following impact of a detached fan blade, a radially outward movement of the first casing element causes the or each fence element to project into the air flow passing through the turbomachine.

Abstract: A heat exchanger includes a heat exchanger core, a fluid path through the heat exchanger core, and a fluid guiding member. The fluid path has an inlet and an outlet. The fluid guiding member is adjacent to the inlet and/or outlet of the fluid path. The fluid guiding member is operable to change the direction of fluid flow.