Abstract: A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

Abstract: A nuclear power plant, having a reactor pressure vessel; a steam generator arranged to generate steam utilising thermal energy generated within the reactor pressure vessel; and a fluid circuit for transferring thermal energy from the reactor pressure vessel to the steam generator. The plant also has a coolant reservoir for storing coolant for supply to the steam generator under gravity in emergency conditions. The steam generator has a steam drying zone comprising one or more steam separators configured to dry steam; and the steam generator and coolant reservoir are configured such that when coolant is supplied from the coolant reservoir to the steam generator in emergency conditions the coolant stays below a threshold level defined by the steam drying zone.

Abstract: An aerofoil component (32) defining an in use leading edge (38) and a trailing edge (40). At least one of the leading edge and the trailing edge (38, 40) comprises a plurality of first and second recesses (52, 56) projecting in a direction corresponding with an in use flow direction, the first and second recesses being spaced apart normal to the in use flow direction and having a different chordal extent.

Abstract: A synchronous electrical machine includes a stator having a circumferential row of teeth carrying stator windings. The electrical machine further includes a coaxial rotor having a circumferential row of poles carrying field windings. Each pole has first and second side flanks and a tip surface which extends continuously there between to form an air gap to the teeth of the stator. On a transverse cross-section through the machine, one of the side flanks forms a leading edge of the pole, and the other side flank forms an opposite, trailing edge of the pole. Each pole carries a row of permanent magnets which extends across the tip surface from one of the side flanks to the other side flank, the permanent magnets compensating for armature magnetic reaction. The radial thickness of the permanent magnets increases smoothly with progressive distance across the tip surface from one of the side flanks to the other side flank.

Abstract: A fuel nozzle for a gas turbine engine is disclosed which includes a nozzle body having a longitudinal axis, an elongated annular air passage defined within the nozzle body, and a plurality of circumferentially spaced apart axially extending swirl vanes disposed within the annular air passage, wherein each swirl vane has multiple joined leads and a variable thickness along the axial extent thereof.

Abstract: Disclosed is a gas turbine engine comprising: a low pressure spool having a low pressure compressor and a low pressure turbine connected by a low pressure shaft; a reduction gear train having a sun gear, a carrier having a plurality of planet gears attached thereto, and a ring gear, wherein the sun gear is driveably connected to the low pressure shaft, and either of carrier and ring gear provides an output drive connected to a propulsive fan; wherein the connection between the low pressure shaft and the sun gear includes a flexible drive shaft having serially connected concentrically nested first and second input shafts between the low pressure shaft and sun gear.

Abstract: Described is a seal segment (310) for a gas turbine engine, comprising: a gas facing wall (312) having a gas facing surface (314) and a first internal surface (316); an outboard wall (318) having an outboard facing surface (320) and a second internal surface (322) which is radially separated from the first internal surface with a gap therebetween; a first conduit (324) located between the first and second internal surfaces; and, a second conduit (326) located between the first and second internal surfaces, wherein the first and second conduits are radially separated by a party wall (328).

Abstract: The invention provides a gear pump bearing block and method of manufacturing gear pump bearing block. Bearing block includes bush formed of antifriction alloy, having a cylindrical portion providing bore adapted to receive bearing shaft of a gear of pump, and further having a flange portion extending radially outwardly at end of cylindrical portion to provide thrust face adapted to slidingly engage with side surface of gear. Bearing block also has backing layer covering radially outer surface of cylindrical portion and rear face of flange portion, backing layer being formed of relatively less dense alloy compared to antifriction alloy. Furthermore, there is an annular formation of one or more stiffening members, formation surrounding bore, the, or each, stiffening member being embedded in flange portion, and the, or each, stiffening member being formed of material having higher elastic modulus than antifriction alloy.

Abstract: A computer-implemented method of optimizing an automatically meshable shape is provided. The method includes the steps of: providing a continuous boundary of the automatically meshable shape, the continuous boundary being defined by a spline formed by two or more spline segments, wherein each segment has a terminal point at each end of the segment; parameterizing shape properties of the segments such that selected ones of the shape properties can be varied under operation of an optimization algorithm; linking each segment to its immediately adjacent segments such that the terminal points of the segment remain coincident with the terminal points of its immediately adjacent segments under operation of the optimization algorithm; and using the optimization algorithm to vary selected ones of the shape properties of the segments, whereby the spline defines an adjusted boundary that remains continuous so that the shape remains automatically meshable.

Abstract: A method of calibrating a rotor tip clearance arrangement that includes measuring a rotor parameter indicative of rotor efficiency and altering a position of a tip clearance control actuator by an increment to reduce the rotor tip clearance. The method further includes iterating the measuring and altering, and calculating a rate of change of the rotor parameter between pairs of iterations. The method further includes identifying a knee point where the rate of change of the rotor parameter changes and record the corresponding tip clearance control actuator position as a calibrated position. Also included is a rotor tip clearance arrangement calibrated by the method and a method of monitoring deterioration of a rotor tip clearance arrangement.

Abstract: A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element. An annular fan track liner is provided comprising a first fan track liner panel positioned circumferentially adjacent a second fan track liner panel. A coupling connects the first fan track liner panel to the second fan track liner panel and the first fan track liner panel and the second fan track liner panel each comprise a groove along an axial face thereof and a portion of the coupling is received in each of said grooves.

Abstract: A fuel injector includes a central member arranged on axis of fuel injector and a first member arranged around central member. A first swirler is arranged between central member and first member. A pilot fuel injector is arranged to supply fuel onto inner surface of first member. A second member is arranged between downstream end of first member and downstream end of shroud. A second swirler is arranged between upstream end of first member and upstream end of shroud and between downstream end of first member and upstream end of second member. A third swirler is arranged between downstream end of shroud and second member. A main fuel injector is arranged to supply fuel into an annular passage between first member and second member and a fourth swirler extends through first member.

Abstract: A combustion chamber arrangement comprises an annular combustion chamber arranged radially between an inner casing and an outer casing. The combustion chamber comprises a metering wall arranged upstream of an upstream wall and the upstream wall and the metering wall each have a plurality of circumferentially spaced apertures. Each aperture in the metering wall is aligned with a respective one of the apertures in the upstream wall. A fuel injector is arranged in each of the apertures in the upstream wall. An air swirler is aligned with a respective one of the fuel injectors. Each air swirler is arranged between the upstream wall and the metering wall. The metering wall has a plurality of metering holes arranged to provide a controlled supply of air to each of the air swirlers and the combustion chamber is secured to the inner casing by a mounting feature.

Abstract: An imaging probe (102) for use in measuring surface roughness by angular speckle correlation is shown. The imaging probe comprises a first illumination fibre (201) to illuminate a sample location (103) on a surface, and having an input end for coupling of coherent light into the fibre, and an output end cleaved at an angle ?1, a second illumination fibre (202) to illuminate the sample location on the surface, and having an input end for coupling of coherent light into the fibre, and an output end cleaved at an angle ?2 that is different from ?1, and an image transmission system (204) for transmission of a to speckle pattern caused by illumination of the sample location on the surface by coherent light from either the first illumination fibre or the second illumination fibre.

Abstract: A gas turbine engine includes: a core engine surrounded by a core fairing; a propulsive fan; a nacelle surrounding the propulsive fan, the core fairing and the core engine; and a fan duct for receiving a bypass air flow accelerated by the propulsive fan, the fan duct being defined between the nacelle and the core fairing. The gas turbine engine further includes an air-oil heat exchanger for cooling engine oil using an air flow diverted from the bypass air flow, the heat exchanger being mounted behind a wall of the fan duct. The gas turbine engine further includes a flow passage which receives the diverted air flow at a first location in the fan duct, delivers the diverted air flow to the heat exchanger, and returns the diverted air flow to the fan duct at a second location which is downstream of the first location.

Abstract: An annulus filler for mounting to a rotor disc in a gas turbine engine includes a body portion having a top wall arranged to bridge the gap between two adjacent blades extending from the rotor disc and to define an air flow surface for air passing between the blades; and a separately formed rear interface portion, fixed to the body portion adjacent to a down-flow end of the top wall. The rear interface portion forms a lip projecting below the top wall.

Abstract: A nickel-base alloy of, in atomic percent unless otherwise stated, up to 8 percent Fe, up to 16 percent Co, between 15 and 25 percent Cr, up to 3 percent Mo, up to 2 percent W, between 3 and 5 percent Al, between 3 and 7.5 percent Nb, up to 3 percent Ta, up to 0.2 percent Ti, up to 0.5 percent C, up to 0.175 percent B, up to 0.07 percent Zr, up to 1 percent Mn, up to 1 percent Si, up to 0.2 percent Hf, the balance of Ni and incidental impurities, wherein the atomic ratio of Al to Nb is between 0.4 and 1.7, the atomic ratio of the sum of Al and Ti to Nb is between 0.4 and 1.8, and, the composition including at least 10 percent of elements from the group of Al, Nb, and Ti.

Abstract: A pressure sensing apparatus is provided for sensing gas pressure at a pressure tapping. The apparatus has a pressure sensor which provides a pressure measurement signal in response to the pressure of a gas admitted into the sensor at a gas inlet port thereof. The apparatus further has a gas conduit which extends from the inlet port. An end of the conduit distal from the inlet port is adapted to receive the gas at the pressure tapping. The apparatus further has a condenser on the gas conduit. The condenser contains condensation surfaces on which humidity in the gas flowing from the pressure tapping to the inlet port condenses out. In operation the temperature at the condenser is lower than at the pressure tapping.

Abstract: A fluid intake including first and second ducts and a particle separation spinner defining an interface between the first and second ducts is disclosed. Spinner includes flow passages passing from first duct side of the spinner to second duct side of the spinner and splitter bodies separating the flow passages. Flow passages and splitter bodies are arranged in thread-like screw manner about spinner. In use, the spinner is spun about an axis of rotation, axis and direction of rotation being such that, from static frame of reference with respect to first duct, splitter bodies and flow passages have a component of movement towards a main travel direction of a fluid flow incident towards spinner from first duct. Splitter bodies are arranged such that they oblige fluid in the fluid flow to follow a convoluted path if it is to pass from first duct to second duct via the flow passages.

Abstract: A combustion staging system has a splitting unit receiving and splitting metered fuel flow into out-going pilot and mains flows; pilot and mains fuel manifolds receiving the pilot and mains flows; and parallel mains flow scheduling valves distributing the mains flow. The mains flow scheduling valves pass the pilot fuel flow to injector pilot discharge orifices. Each mains flow scheduling valve has a chamber containing a piston, the chamber to a piston pilot side communicating with the pilot fuel manifold and the chamber to a mains side of the piston communicating with the mains fuel manifold. The piston is biased towards a closed pilot-only position preventing flow out of the chamber mains side to the injector mains discharge orifice. The piston is movable under increased pressure in the mains fuel manifold to an open pilot-and-mains position allowing flow out of the chamber mains side to the injector mains discharge orifice.