Abstract: A method of determining the location of a fault within a first inductive part of an electrical circuit, including a voltage source, first inductive part and second inductive part. A shortened circuit created by the fault includes the voltage source, a portion of the first inductive part and the second, connected in series. The fault occurs across first and second points in the first inductive part. The length of first inductive part between a positive terminal and first point is substantially equal to the length of first inductive part between a negative terminal and second point. The voltage source supplies a known voltage Vs when the fault occurs and the second inductive part has a known inductance L2 when the fault occurs. The method takes advantage of the initial transient response of the circuit to determine the inductance of the portion of the first inductive part in the shortened circuit.

Abstract: An arrangement for vibro-polishing one or more components, the arrangement comprising a container for containing vibro-polishing media, an agitator to agitate the vibro-polishing media relative to the container, one or more partitions extending substantially across the container so as to provide two or more sectors and, a fixture comprising at least one member which extends around one or more components for insertion into the vibro-polishing media, each member defining an opening which is sized to prevent any further fixture or partition from contacting the or each component.

Abstract: A method of forming a fibre composite component (10), the method comprising: providing a plurality of first fibres (102), the first fibres (102) being arranged in a plurality of layers (104a-e) with an uncured thermoset resin matrix (106) being provided therebetween. The resin matrix (106) comprises a plurality of second electrically conductive fibres (108) suspended therein having a shorter length than the first fibres (102). The method comprises then applying an energy field to the resin matrix (106) to thereby align the second fibres (108) such that they provide an electrically conductive path between adjacent layers (104a-e) of first fibres (102) to form an electrically conductive fibre network comprising the first and second fibres (102, 108). The method comprises then inducing an electric current through the electrically conductive fibre network to thereby heat and cure the resin matrix (106).

Abstract: A solid state power control apparatus includes: (a) at least one IGBT and at least one FET, for supplying current to a load, and (b) a current controller for shutting off the IGBT and FET. The current controller is arranged to start shut off of the IGBT before it starts shut off of the FET. Further, the current controller is arranged to reduce current flow prior to start of the turn off of the IGBT and FET.

Abstract: Method of manufacturing a metal matrix composite component includes the steps of providing a first tubular member having a first end and an opposite second end, the first tubular member's first end being formed as a first end block; positioning a metal matrix composite tubular member concentrically the first tubular member; positioning a second tubular member concentrically over metal matrix composite tubular member, second tubular member having a first end and an opposite second end, the second tubular member's second end being formed as a second end block; welding first tubular member's first end to the second tubular member's first end, and the first tubular member's second end to second tubular member's second end, to join the first and second tubular member and thereby to form a metal matrix composite preform; and consolidating metal matrix composite preform by a hot isostatic pressing process to form the metal matrix composite component.

Abstract: A component for releasing a flow of material into an environment subject to periodic fluctuations in pressure, which has: a first surface that includes an inlet; a second surface that includes an outlet; a duct formed in the component and extending from the inlet to the outlet so, when the component is in use, a flow of material received at the inlet can flow along the duct to be released at the outlet into an environment subject to periodic fluctuations in pressure. The duct includes a constriction at which it decreases in cross-sectional area as it progresses from the inlet to the outlet. This can help reduce the variation in flow rate of material released at the outlet caused by the periodic fluctuations in pressure, and may help to avoid/reduce ingestion, when the component is in use. Preferably, the component is configured to form part of a gas turbine engine.

Abstract: There is disclosed a laminated composite structure (12) having a plurality of laminae (13) formed of composite material, and at least one reinforcing pin (3) provided within the structure so as to extend between adjacent laminae (13). The at least one reinforcing pin (3) is formed from a plurality of interlaced metal filaments (1, 2). There is also disclosed a related method for reinforcing a laminated composite structure (12) via the use of at least one said reinforcing pin (3).

Abstract: A fan containment system includes an annular casing element and a hook projecting in a generally radially inward direction from the annular casing element. A fan track liner is connected to the hook via a fastener. The fan track liner has a forward end proximal to the hook and a rearward end distal to the hook. A pivot member protrudes radially inward from the annular casing element and is arranged and positioned between the forward and rearward end of the fan track liner such that a forward portion of the fan track liner is pivotable about the pivot member, so that upon release of a fan blade the forward portion of the fan track liner pivots about the pivot member into a voidal region provided between the annular casing element and the forward portion of the fan track liner to encourage engagement of the hook with a released fan blade.

Abstract: In a gas turbine engine, each vane has pressure and suction surfaces extending radially from an inner to outer endwall of an annular working gas engine passage, and extending axially from a leading to a trailing edge of the vane. Each vane has transverse sections providing respective aerofoil sections. Neighboring vanes are arranged in unequally-shaped pairs in which either: (i) the first vane of each pair exhibits compound lean, and the second vane of the pair exhibits reverse compound lean or has substantially no tangential lean, (ii) the first vane of each pair has substantially no tangential lean, and the second vane of the pair exhibits reverse compound lean, or (iii) the first vane of each pair exhibits reverse compound lean, and the second vane of the pair exhibits greater reverse compound lean. Within each unequally-shaped pair the first vane is on the pressure surface side of the second vane.

Abstract: The present invention relates to a pressure-measuring device for measuring dynamic pressures in the high-temperature range, with a pressure line connected to a volume subjected to pressure and with a pressure sensor which is arranged at a distance from the inlet area of the pressure line to the volume, wherein the pressure line is provided with at least one pinhole diaphragm and connected to an additional damping volume, as well as to the use of the pressure-measuring device in a combustion chamber of a gas turbine.

Abstract: A stator assembly for a rotary machine having a rotor arranged to rotate about an axis in use. The stator assembly has a circumferential support member or casing arranged about said axis and a plurality of elements extending in a substantially radial direction from the support. The elements have a platform at an end thereof for engagement within the support, wherein the elements each comprise a hollow internal cavity having an opening through the platform at the end of the element, wherein said internal cavity is filled with a vibration damping material. The elements may be filled vanes in a gas turbine engine compressor. The platforms may also be filled with the vibration damping material.

Abstract: An aerofoil for a gas turbine engine including a pressure wall and a suction wall and defining leading and trailing edge, the walls define a passage into which is supplied a cooling fluid, an array of cooling holes is provided through at least one of the walls to allow the cooling fluid to flow from an interior surface to an exterior surface. The array of holes include two groups, the holes of each group are angled to intersect the holes of the other group and are characterised in that the holes of at least one of the groups includes two or more holes at different angles to one another to vary the porosity of the wall to account for otherwise varying wall temperatures. This arrangement also allows either less coolant mass flow to maintain a constant metal temperature, or a lower metal temperature for a given coolant mass flow.

Abstract: A method of manufacturing a magnetically graded material, including depositing a steel filler material to a substrate, and applying a directed energy source to first and second regions of the filler material to thereby join the filler material to form a joined material. The energy source is directed to the first region while the first region is provided with an inert shield gas such that the material of the first regions includes a magnetic phase, and the energy source is directed to the second region while the second region is provided with a nitrogen containing shield gas to thereby impart an non-magnetic phase to the joined material.

Abstract: A method of applying an electroplated layer to a surface of a polymeric composite material, the method includes the steps of: providing an uncured polymeric composite substrate; positioning a veil layer over a surface of the uncured polymeric composite substrate, the veil layer providing a conductive surface on the uncured polymeric composite substrate, the veil layer having a mat of metal coated fibres consolidated by an organic binder material; subjecting the uncured polymeric composite substrate to a curing cycle to form a cured polymeric composite material in which the veil layer is partially exposed; and applying an electroplated layer to the conductive surface of the cured polymeric composite material.

Abstract: An aircraft fuel pumping arrangement comprises a first fuel pump, an electrically powered motor operable to drive the first fuel pump to deliver fuel to an outlet, a second fuel pump, a gas driven turbine operable to drive the second fuel pump to deliver fuel to the outlet, and a controller operable to control the operation of the gas driven turbine to determine the rate at which the second fuel pump is driven.

Abstract: A nacelle for a turbofan gas turbine engine, having in flow series an intake lip, a diffuser and a fan casing. The diffuser has, in flow series, a main section and a recessed section adjacent to the fan casing. A transition region, such as a step, slope or curve, is provided between the main section and the recessed section. In some arrangements the transition region may be configured to promote flow separation and the formation of a separation bubble in the recessed section.

Abstract: A method of controlling an inverter, in which the inverter includes a single-phase inverter arrangement having a complementary pair of power switches, including the steps of: controlling the complementary pair of power switches with a modulating signal to output an AC signal; monitoring a collector-emitter voltage of each of the pair of power switches; if the collector-emitter voltage exceeds a predetermined value, the corresponding one of the pair of power switches is judged to be in a short circuit condition; and if either one of the pair of power switches is judged to be in a short circuit condition, executing a shutdown operation to switch off the corresponding one of the pair of power switches.

Abstract: A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum and a second air duct that provides a cooling airflow to the nozzle guide vane. A common manifold is upstream in the cooling airflow of the ducts and provides cooling air to the ducts. A two-way valve modulates air provided to the ducts from the manifold. The valve is operates in a first or second mode. In the first mode, air flow to the first duct is relatively high and airflow to the second duct is relatively low compared to where the valve is operated in the second mode.

Abstract: A gas turbine engine comprising an electrical machine 30, 130, 200, 210, the electrical machine 30, 130, 200, 210 having an axis of rotation that is canted with respect to the main rotational axis of the gas turbine engine.

Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard hot gas flow path facing side and an outboard side; a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion; a first cooling circuit within the plate for cooling a first portion of the plate; a second cooling circuit within the plate for cooling a second portion of the plate; wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another. Also described is a method of cooling a seal segment in a gas turbine engine.