Abstract: Asymmetric loading within such machines as gas turbine engines can cause distortion of a casing surrounding a rotating assembly. Such distortion may cause rub and therefore inefficient energy usage and shorter operational life. By providing driver arms 112, 212, 312 which extend from radially extending links 113, 213 in a first or high pressure compressor inner casing 101, 201 to a second outer casing 108, compensation for asymmetric loading can be achieved. The casings 101, 201, 108, 208 are presented upon relatively stable bearing supports 102, 110 and therefore, reaction loads are compensated for in order to retain concentricity of the casing 101, 201.

Abstract: An aircraft (40) electrical actuator arrangement comprises a plurality of electrical actuators (11) coupled to an electrical power distribution network, the electrical power distribution network has a master power converter (1) to convert electrical power from the electrical power distribution network for supply to each electrical actuator (11). The electrical actuators (11) comprise an environmental control system actuator (68), an aileron actuator (78), a flap actuator (70), a slat actuator (72), a landing gear actuator (76), a thrust reverser actuator (74), a brake actuator (80) and a taxiing actuator (82). A controller is coupled to the master power converter (1). The controller is arranged to allow the supply of electrical power from the master power converter (1) to the environmental control system actuator (68) during a first mode of operation of the aircraft (40).

Abstract: Apparatus indicated generally at 26 is incorporated within an aircraft. The apparatus 26 includes an electric motor 28, a first drive train 30 and a second drive train 32. The first drive train 30 provides drive from the electric motor 28 for one or more of the wheels 20, allowing the electric motor 28 to propel the aircraft when taxiing. The second drive train 32 provides drive from the electric motor 28 for an aircraft system which is operational at least when the aircraft is in flight. In this example, the electric motor 28 is illustrated using the second drive train 32 for driving a compressor 34 of the ECS 24, the compressor 34 being responsible for cabin pressurisation during flight. A clutch 36 allows the drive train 30 to be connected or disconnected from the electric motor 28, thereby connecting or disconnecting the drive from the electric motor 28 to the wheels 20. The clutch 36 is controlled to disconnect the first drive train 30 when the aircraft is in flight.

Abstract: A stator vane assembly comprising: an inner vane support (44); an outer vane support; and a plurality of vanes (50) extending radially between the inner vane support (44) and the outer vane support; wherein each of the inner (44) and outer vane supports has openings for receiving respective first and second ends of the vanes (50) and each said vane (50) is connected to the inner vane support (44) at its first end by a first vane boot (40) received in a said opening and to the outer vane support at its second end by a second vane boot (40) received in another said opening, wherein each vane boot (40) has a rim portion (41) shaped to locate the boot (40) within the corresponding opening in the vane support, the rim portion (41) engaging with the inner surface defining the opening, an abutting portion (47) for abutting against the vane support (44) in the region surrounding the opening, and a vane pocket (42) for accommodating the end of the vane, wherein the vane pockets (42) of the first and second vane boots

Abstract: An engine mounting assembly for an engine, e.g. a gas turbine engine comprises a plurality of carrying arrangements. Each carrying arrangement comprises a rear load absorbing assembly. Each load absorbing assembly provides a rear mounting point for an engine carrier. Each carrying arrangement further comprises first and second stabilising members extending forwardly from the rear mounting point of the rear load absorbing assembly to first and second spaced forward mounting points for an engine carrier.

Abstract: A lead for transmitting an electrical signal within a gas turbine engine, from a node at a first part of the gas turbine engine having a first surface to a second part of the gas turbine engine having a second surface, wherein the first part and the second part are coupled at a compressed joint, wherein the lead comprises: a node on the first surface of the first part; a first interconnect, adhered to the first surface of the first part; and a second interconnect, adhered to the second surface of the second part, wherein the first interconnect and the second interconnect abut at the compressed joint to provide, by their contact, a continuous electrical connection from the node to the second part.

Abstract: A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force absorbing arrangement circumferentially surrounds a major proportion of the axial length of the engine.

Abstract: A combustor assembly comprising a combustor liner having an opening and a combustor chute, which is formed of a sheet material which is bent to form the desired chute. The chute allows the passage of cooling and dilution air into the combustor.

Abstract: Asymmetric distortion between an inner casing and outer casing such as with regard to a gas turbine engine between an inner high pressure compressor casing and an outer combustion casing can result in problems with regard to rub between a rotary assembly within the inner casing. By providing hairpin mountings between the inner casing and outer casing such distortions can be dislocated. Individual hairpin segments are provided. These hairpin segments can be configured and formed from different material types and have different spacing distributions to tune the casing arrangement to the particular requirements and operational performance necessities of an assembly incorporating the casing arrangement.

Abstract: Processing of components such as turbine blades for gas turbine engines requires formation of holes and other shaping. It is known to use electrical discharge machining processes to produce such holes and apertures in work pieces. Removal of debris is important to avoid short circuiting and/or arcing and to allow rapid processing. Utilisation of high pressure dielectric fluid flow reduces debris build up but can still result in short circuit switching or interrupt continuous processing. By provision of vibration and in particular ultrasonic vibration cavitation is induced within the pressurised dielectric fluid flow to enhance debris removal and therefore improve continuous machining processes.

Abstract: This invention relates to a bearing arrangement for supporting a rotatable shaft relative to a support structure. The bearing arrangement comprises a first bearing having radially inner and outer races, the inner race being rotatable relative to the outer race in use, and a second bearing arranged such that the first bearing is mounted to the support structure via the second bearing. The second bearing may allow for deflection of the shaft supported by the bearing arrangement. The bearing arrangement may be applied to high speed thrust bearing applications, such as, for example, within a gas turbine engine.

Abstract: A bainitic steel alloy and a method for making such an alloy are disclosed, in which the bainite plates are particularly small, less than 50 nanometres in width. In preferred embodiments of the invention, each bainite plate is surrounded by a film of retained austenite; the level of retained austenite in the alloy is greater than 10%; and the alloy is substantially free of blocky unstable austenite and cementite.

Abstract: A superconducting electrical machine comprises a rotor and a stator. The stator comprises a stator having a plurality of circumferentially spaced radially extending teeth and a plurality of superconducting electric coils. Each superconducting electric coil is positioned around a respective one of the teeth. A thermally conducting member surrounds and contacts the stator. A cooler is arranged to cool the thermally conducting member. A vacuum enclosure encloses the thermally conducting member, the stator and the superconducting electric coils and a pump is arranged to evacuate the vacuum enclosure. The superconducting electrical coils comprise magnesium diboride.

Abstract: A pivot ring arrangement for a stage of variable stator vanes (VSVs) (38) in a gas turbine engine comprises a plurality of segments (12) secured in a segment carrier (22). The segments are injection molded from self-lubricating material, obviating the need for separate bushes for the VSV spindles (36).

Abstract: A thermocouple connector has a first member and a second member which couples to the first member. The first member carries two first terminals for electrically joining to the respective ends of a pair of thermocouple wires. The second member carries two corresponding second terminals for electrically joining to the respective ends of a pair of thermocouple extension wires. Each first terminal contacts a respective second terminal when the first and second members are coupled.

Abstract: A boundary layer control arrangement comprises a pulse generator communicating with a surface having a fluid boundary layer thereacross. The boundary layer control arrangement further includes a fluid supply means for supplying a fluid to the surface via the pulse generator. The pulse generator is constructed such that fluid acts on the pulse generator to cause the fluid to pulse. Pulsing fluid passes from the pulse generator to the surface.

Abstract: A method of manufacturing a component by superplastic forming and diffusion bonding a first layer, a second layer, a first membrane, and a second membrane, the first and second membranes being disposed between the first and second layers with the first membrane adjacent the first layer and the second membrane adjacent the second layer, by a method of applying a stop-off material in a first predetermined pattern between the first layer and the first membrane so preventing a diffusion bond from forming between the first layer and the first membrane across regions defined by said first predetermined pattern; applying the stop-off material in a second predetermined pattern between the second layer and the second membrane preventing a diffusion bond from forming between the second layer and the second membrane across regions defined by said second predetermined pattern; and providing a damping material between the first and second membranes.

Abstract: An actuator (12) is disclosed for example controlling gas flow in a gas turbine engine. The actuator (12) comprises a first portion (14) having shape memory properties, and a second portion (16) formed of substantially the same material as the first portion and having reduced shape memory properties relative to the first portion. The first portion (14) is movable from a first position to a second position at a temperature above the phase transition temperature of the shape memory material of the first portion (14). The second portion (16) is arranged to urge the first portion (14) from the second position to the first position at a temperature below the phase transition temperature of the shape memory material.

Abstract: An assembly for a turbomachine comprising: a plurality of components (16, 26) which, in use, are assembled into a circumferentially extending annular array; each component having a radially outer platform (20, 28), the outer platforms (20, 28) of the components (16, 26) forming a ring in the assembled array; wherein adjacent components (16, 26) interface at adjacent surfaces (22, 30) of their outer platforms (20, 28); wherein the outer platforms (20, 28) each comprise at least one lug (24) which extends from the outer platform (20) over a portion of the outer platform (28) of an adjacent component (26), and in use prevents relative radial displacement of the outer platform (20, 28) of the adjacent component (16, 26).

Abstract: A magnetoplasmadynamic (MPD) generator comprising a conveying duct (6) shaped for conveying a high velocity, conductive fluid; a magnetic field generator arranged to generate a magnetic field (2) across the conveying duct (6), substantially perpendicular to the direction of travel of the fluid, such that the fluid passes through the magnetic field (2) when conveyed by the duct (6); electrodes (4) arranged to conduct a current (5) induced in the fluid as it is conveyed by the conveying duct (6) through the magnetic field (2); and a fluid break-down circuit arranged to electrically break-down the fluid by developing an additional voltage across the electrodes (4).