Abstract: In certain circumstances recovery of a fluid flow presented through a heat exchanger into another flow can create problems with respect to drag and loss of thrust. In gas turbine engines heat exchangers are utilized for providing cooling of other flows such as in relation to compressor air taken from the core of the engine and utilized for cabin ventilation and de-icing functions. By providing an outlet valve through an outlet duct in a wall of a housing the exhaust fluid flow from the heat exchanger can be returned to the by-pass flow with reduced drag effects whilst recovering thrust. The valve may take the form of a flap displaceable into the by-pass flow before an exit plan to create a reduction in static pressure drawing fluid flow through the heat exchanger.

Abstract: A window lift system includes a motor drive assembly (10) constructed and arranged to control movement window glass of a vehicle, and a door module (35) to which the drive assembly is coupled. The door module has surface features (36) disrupting a surface (37) of the door module to reduce the transfer of vibration energy from the door module to the drive assembly or vise versa. In an embodiment, the door module includes a diaphragm (34) and the surface features are annular, undulating, wave-like features in the diaphragm.

Abstract: A self-powered fan for circulating air for use in cooperation with a heat source, such as a wood stove, and having a first heat transfer member thermally and physically connected with the heat source. The fan blades operably create a first or warm air flow and a second or cooler air flow. The fan has a second heat transfer member with a thermocouple module structure located between the two heat transfer members. The first heat transfer member is of suitable material, size, mass and shape as to provide a suitable temperature gradient between the thermocouple structure and the heat source to operably allow of such sufficient heat transfer from the first heat transfer member to the thermocouple to generate sufficient power to effect rotation of the blades, but not to cause thermal damage to the thermocouple structure.

Abstract: Cooling with regard to high-pressure turbine platforms is important in order to maintain gas turbine engine efficiency. Cottage Roof dampers located below junction gaps between adjacent platforms have been used but tend to present spent coolant flow at a high angle relative to hot gas flows about the aerofoil blades. The present arrangement has the junction gap angled such that the emergent coolant flow remains adjacent to the suction side to create a coolant film lingering above that suction side of the platform.

Abstract: This invention relates to a Pet toy, comprising a body structure (1) provided with a plurality of retaining compartments (2) presenting openings (3), arranged to enable hiding and retrieving of objects (4) therein, wherein said body structure (1) comprises a plurality of flexible, sheet formed layers (10, 11, 12) fixedly attached to each other one on top of the other, at least one lower layer (11) has a larger size than a layer (12) positioned on top of the lower layer (11), and wherein said retaining compartments (2) are in the form of pockets between next to each other positioned layers (10, 11, 12).

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: 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: An elongate railway crosstie for supporting rail tracks on a bed of stones or the like, said tie having a first end, a second end, a length between said first and second ends and a top surface, a bottom surface and a pair of side surfaces between said first and second ends, characterized in that at least one of said side surfaces has a portion of a non-planar stone-embeddable form extending between said first and second ends, so-shaped as to effect reduced lateral and longitudinal slippage of said tie within said bed, while providing a reduction in the volume of material used.

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: In a DC electrical power system used in an aircraft, an earthing arrangement is provided between electrical power supply rails in the form of a pair of capacitors with a mid electrical voltage earthing point, having an earthing path, in which electrical resistance is provided to limit electrical current flow and therefore allow continued operation despite the earth fault.

Abstract: In order to achieve micro alloying of protective coatings for components such as turbine blades in a turbine engine, a base metal is splutter coated by deposition of a trace element to a desired proportion. A protective layer of the base metal is then applied over the trace element to prevent further reaction or oxidation of the trace elements. A coating consumable is therefore formed from the base metal and the trace element. The consumable may be produced immediately prior to coating of the component or may be inertly stored for subsequent use. The consumable is applied by laser deposition techniques whereby a coating is formed in the melting process.

Abstract: An aerofoil blade for a gas turbine engine, the blade having a metallic core defining a number of cavities that contain a foamed material. The cavities are shaped such that the force of an impact on one surface of the blade is dissipated through the foam and transmitted to the metallic core. A fibrous internal containment device allows the blade to fragment progressively thereby spreading the load imparted by the blade to a casing should the blade fragment upon impact.

Abstract: A turbomachine blade comprising a root portion and an aerofoil portion, the aerofoil portion having a leading edge, a trailing edge, a concave metal wall portion extending from the leading edge to the trailing edge and a convex metal wall portion extending from the leading edge to the trailing edge, the concave metal wall portion and the convex metal wall portion forming a continuous integral metal wall, the aerofoil portion having a hollow interior defined by at least one internal surface, the hollow interior of the aerofoil portion being at least partially filled with a vibration damping material that is separated from the metal wall portions by a thermally insulating material.

Abstract: Method for treatment, in the form of regeneration, of an accumulator (160) having at least one cell, preferably lead batteries, in which a varying direct current from a power source (130) is applied in intermittent current supply periods, which are interrupted by pauses of substantially less current, preferably current free, the direct current being sufficient to generate gas in the accumulator. During the treatment process, process data is registered, which process data is used in order to control the treatment process.

Abstract: A computer system programmed to process a large data set includes means for analysing the data set. The means for analysing the data set typically comprises a means for finite element analysis. The computer system also includes means for applying a data compression technique to the analysed data set such that the compressed analysed data set has high fidelity in regions of interest and has lower fidelity in regions of lesser interest. The data compression technique comprises the use of a wavelet compression technique. The computer system comprises a high specification server and a local workstation. This compressed analysed data set is easily managed by the local workstation to produce different cross-sectional displays without reusing the high capability server. The analysed data set for example comprises a 4D data set of a fan blade containment analysis of a casing.

Abstract: A method of forming a structure by a material additive process, the method comprising the steps: providing a substrate having a surface, providing an interlayer on the surface which conforms to the surface of the substrate, forming a melt pool in the interlayer, the depth of the melt pool being less than the depth of the interlayer, selectively depositing a material within the melt pool, allowing the material to solidify, and applying heat and pressure to diffusion bond the material to the substrate.

Abstract: An improved method of reducing a mixed metal oxide composition comprising oxides of nickel, cobalt, copper and iron in a hydrogen atmosphere to produce a mixture of the respective metals, the improvement wherein the atmosphere further comprises water vapour at a concentration, temperature and time to effect selective reduction of the oxides of nickel cobalt and copper relative to the iron oxide to produce the metallic mixture having a reduced ratio of metallic iron relative to metallic nickel, cobalt and copper.

Abstract: A rotor assembly for a gas turbine engine, the rotor assembly comprises at least two rotors defining a cavity therebetween. A first rotor defines a cooling air inlet in its radially inward portion. A second rotor defines a cooling air outlet in its radially outward portion, such that the cooling air passes radially outwardly through the cavity.

Abstract: A bypass turbofan engine comprises a first propulsion system and a second propulsion system. The first propulsion system comprises a first fan rotor, a core engine, a first low pressure turbine and a first fan shaft drivingly connecting the first turbine and the first fan rotor. The second propulsion system comprises a second fan shaft drivingly connecting to a second fan rotor and the first propulsion system and arranged so that the first and second shafts are not coaxial with one another.