Abstract: A fuel flow valve, for example for use in supplying fuel to a gas turbine engine. Example embodiments disclosed include a staging fuel valve (300), comprising: a valve housing (301) having first and second fuel inlets (306, 307) and first and second fuel outlets (305, 308); a piston (302) slidably mounted within a chamber (303) in the valve housing (301) and being moveable between a first position in which the first inlet (306) is in fluid communication with the first outlet (305) while the second inlet (307) and second outlet (308) are blocked, and a second position in which the second inlet (307) is in fluid communication with the second outlet (308). The piston (302) comprises a magnet assembly (312) and the valve housing (301) comprises a coil (313) arranged to provide, when energised, a magnetic force to actuate the piston (302) between the first and second positions.

Abstract: A device is provided for inserting coil inserts into threaded holes. The device includes an insertion tool having a manipulator end which is configured to receive and hold a coil insert, and which is operable to apply a torque to the coil insert to screw the coil insert into a threaded hole when presented thereto, the manipulator end having an insertion axis which is coincident with the axis of the coil insert when held by the manipulator end. The device further includes a tool support to which the insertion tool is mounted, the tool support being fixable to an end of a robot arm whereby the manipulator end is presentable by the robot arm to the threaded hole for insertion therein of the coil insert.

Abstract: A double skinned feed or scavenge pipe assembly comprises; an inner pipe (22) and an outer pipe (23) enclosing the inner pipe and defining an annular space (24) between the inner pipe and the outer pipe and a sleeve (28) configured to slip over the outer pipe (23). Complementary threads (29) are provided on an outer wall of the outer pipe (23) and an inner wall of the sleeve (28). A lock, for example in the form of a locking nut (31) is positioned over the outer pipe (23) when the complementary threads (29) of the outer pipe and sleeve are engaged. The configuration of the assembly is such that, in use, the sleeve (28) is slidable between a first position where the inner pipe (22) is accessible and a second position wherein the inner pipe (22) is completely enclosed.

Abstract: A tail bearing housing of a turbomachine comprises an inner casing and an outer casing concentrically arranged along a longitudinal axis, and a plurality of vanes having a leading edge, a trailing edge, a first wall extending from the leading edge to the trailing edge and a second wall extending from the leading edge to the trailing edge, the first wall and the second wall defining an aerofoil, the vanes being connected at a first end to the outer casing and at a second end to the inner casing. At least one vane of the plurality of vanes is a vent vane comprising a first aperture arranged in the first end and a second aperture arranged in the aerofoil, the second aperture being configured to be in fluid communication with the first aperture through an inner cavity to vent bleed air.

Abstract: An aircraft cabin blower system comprising a transmission and a compressor is disclosed. The system has a forward configuration in which the compressor is drivable in use via the transmission. The transmission comprises a toroidal continuously variable transmission giving selectively variable control over the rate at which the compressor is driven.

Abstract: A gas turbine engine comprising: a bypass duct having a bypass nozzle; an engine core having a core nozzle; and, a mixer duct defined by a mixer fairing and having a mixer nozzle, wherein the mixer duct is arranged to receive an airflow from the bypass duct through a mixer duct inlet and an airflow from the engine core, when in use, and the geometry of the mixer duct is selectively adjustable by moving the mixer fairing relative to the bypass duct and engine core in use.

Abstract: The invention concerns an aircraft propulsion system having an engine core within which fuel is combusted to produce an exhaust containing water produced from the combustion of fuel, at least one propulsive fan for generating a mass flow of air which mixes with the exhaust of the engine core, and one or more sensor arranged to sense a condition indicative of vapor trail formation by the exhaust flow from the engine; and a controller arranged to control the ratio of the mass flow of water in the exhaust to the mass flow of air propulsed by the propulsive fan such that the ratio is reduced upon sensing of said condition by the one or more sensor.

Abstract: Described is a nozzle guide vane assembly may comprise: a plurality of nozzle guide vane passages arranged in an annular array, each nozzle guide passage comprising inner and outer radial platforms, a suction surface of a first vane, and a pressure surface of a second vane, wherein the nozzle guide passages are made from a plurality of layers of ceramic fibers held in a ceramic matrix, wherein a first nozzle guide passage includes at least one attachment lug attaching the nozzle guide passage to either or both of an engine casing and an adjacent second nozzle guide passage, the attachment lug being integral with the first nozzle guide passage.

Abstract: Vibratory treatment apparatus including a first receptacle arranged to receive media for vibratory treatment of the article, the first receptacle defining a first aperture; and a first valve positioned at the first aperture of the first receptacle, the first valve being arranged to allow passage of the article there through and to prevent the flow of media through the first aperture.

Abstract: An aircraft cabin blower system includes a transmission configured to receive mechanical power from a gas turbine engine in the form of a first transmission input; and an electrical circuit including a first electrical machine, a second electrical machine, and power management system, wherein, when operating in a blower mode, the first electrical receives mechanical power from the gas turbine engine and act as a generator to provide electrical power to the power management system, and the second electrical machine acts as a motor providing mechanical power to the transmission in the form of a second transmission input, the second electrical machine being driven by electrical power from the power management system. The transmission's output drives a cabin blower compressor when operating in the blower mode, a speed of the output of the transmission being determined by a function of a speed of the first and second transmission inputs.

Abstract: An aircraft cabin blower system includes: a transmission configured to receive mechanical power from a first part of a gas turbine engine in the form of a first transmission input; and an electrical circuit including a first electrical machine, a second electrical machine, and a power management system, wherein an output of the transmission is configured to drive a cabin blower compressor when operating in a blower mode, the first electrical machine being configured to receive mechanical power from a second part of the gas turbine engine and act as a generator to provide electrical power to the power management system, and the second electrical machine being configured to act as a motor providing mechanical power to the transmission in the form of a second transmission input, the second electrical machine being driven by electrical power from the power management system.

Abstract: A circumferential seal for a rotating component comprising a static seal part and a rotating seal part having a common rotational axis. The rotating seal part comprises a fin seal, wherein the fin seal comprises a protective coating. A first portion of the fin seal has a first sealing gap to the static seal part and a second portion of the fin seal has a second sealing gap to the static seal part. The first sealing gap has a greater radial dimension than the second sealing gap.

Abstract: A transmission for receiving mechanical power from a gas turbine engine; and a cabin blower compressor, an output of the transmission being configured to drive the cabin blower compressor; wherein the transmission has a variable gear ratio and the cabin blower compressor has a variable geometry, wherein variation of the gear ratio and the geometry provides a variable output of the cabin blower compressor.

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 pitch change mechanism for a bladed rotor includes a driving sleeve, a drive shaft, a first pitch-changing element, a second pitch-changing element, and a plurality of blade drive gears. The driving sleeve has, in axial sequence, a first helical connection portion and a second helical connection portion. The driving sleeve is positioned concentrically with and surrounding the drive shaft. The first pitch-changing element has a first end drivingly engaged with the first helical connection portion, and a first ring gear portion at a second opposite end, while the second pitch-changing element has a first end drivingly engaged with the second helical connection portion, and a second ring gear portion at a second opposite end. The plurality of blade drive gears are arranged in a circumferential array around a longitudinal axis of the drive shaft.

Abstract: A fan for gas turbine engine that includes hub and annular array of fan blades mounted to hub and extending radially outwardly from hub, each fan blade includes blade root. The hub includes a plurality of hub grooves having shape complimentary to shape of blade root and each hub groove receives and radially retains one blade root. A slot is provided on the suction side and on the pressure side of each blade root. Plurality of keys is provided, each key engages with slots in one blade root and with corresponding hub groove so as to axially retain fan blade. The key includes two arms and joining member, two arms are received in slots provided on blade root and joining member extends between the arms. Interface is defined between key arms and slots in blade root, and greater or equal percentage of interface is curved than is planar.

Abstract: A powder deposition apparatus for producing a component comprises a base plate, an annular stack of heating elements, accommodating the base plate, one or more insulating elements, being interleaved between adjoining heating elements, a mechanism operable to deposit a plurality of layers of a powder material onto the base plate, and a laser energy source operable to selectively fuse a portion of the deposited layer. The annular stack of heating elements is sized such that a predetermined clearance is defined between the component and the annular stack of heating elements. As successive layers of the powder material are deposited onto the base plate, the base plate is lowered into the stack of heating elements, the heating elements being actuated sequentially to maintain a pre-determined temperature profile in the deposited layers.

Abstract: A gas turbine engine comprising a fan, a bypass duct positioned downstream of the fan and defined by an inner casing and an outer casing, a series of outlet guide vanes arranged downstream of the fan, the outlet guide vanes extending between the inner casing and the outer casing of the bypass duct; and a bifurcation positioned downstream of the outlet guide vanes and extending between the inner casing and the outer casing. The bifurcation comprises a leading edge, and the leading edge of the bifurcation is shaped so as to protrude axially forward by a varying distance from the inner casing to the outer casing so as to improve uniformity of a static pressure field formed, in use, immediately upstream of the bifurcation.

Abstract: A gas turbine engine comprises a gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a carrier. The carrier comprises a primary structure and at least one reinforcing structure. The primary structure comprises a first material and the at least one reinforcing structure comprises a second material. The primary structure includes a first ring, a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring. Each planet gear is rotatably mounted on a respective one of the axles by a bearing. The reinforcing structure is secured to the primary structure and the reinforcing structure comprises a particulate reinforced material or a fiber reinforced material. The reinforcing structure increases the stiffness of the carrier and reduces the weight of the carrier.

Abstract: A turbine blade having labyrinth of internal channels for circulation of coolant, the novel labyrinth geometry includes; inlet arranged on axially upstream face of terminal portion leading to an upstream duct portion having first section adjacent the inlet and a second section, the second section having reduced cross section compared to first section; a first passage intersecting first section and extending through the blade body towards tip of the blade, a proximal end of leading edge passage arranged to capture incoming air flow; a main blade passage intersecting a downstream duct portion, the downstream duct portion arranged in axial alignment with the upstream duct portion but separate from upstream duct portion; and a restrictor passage intersecting with the mid-blade passage and extending towards a mid-blade duct portion, the mid-blade duct portion in axial alignment with the upstream and downstream duct portions and in fluid communication with the upstream duct portion.