Abstract: A propulsion engine for an aircraft, the propulsion engine comprising: one or more fans (1, 2) rotatably linked to one or more respective shafts (11); a driving means arranged to drive the one or more fans; and a first hydraulic pump-motor (10) connected to one of the fan shafts, the first hydraulic pump-motor comprising a cam (12) disposed about the shaft and one or more radially extending pistons (13) arranged to engage a surface of the cam, the cam and pistons being arranged such that the pistons reciprocate due to the rotation of the cam, wherein the first hydraulic pump-motor is arranged to selectively transfer a variable amount of power to or from the one or more fans so as to control the rotational speed of the one or more fans.

Abstract: A method of manufacturing an annular wall (46) of a combustion chamber (15) comprises depositing layers of a metal sequentially one upon the other to form layers of a spiral wall (45) of the combustion chamber (15). Each layer of metal is deposited in a spiral pathway (122). The ends (E1, E2) of the spiral wall (45) of the combustion chamber (15) are joined together to form the annular wall (46) of the combustion chamber (15). The ends (E1, E2) of the spiral wall (45) of the combustion chamber (15) are at the opposite ends of the spiral pathway (122).

Abstract: A cooling system for a gas turbine engine (10) having a compressor (14), a combustor (16) and a turbine section arranged to receive combustion products from the combustor. The cooling system includes ducting (32,44) defining a flow path from the compressor to a component, such as a turbine blade (26) to be cooled within the turbine section. The ducting (32) bypasses the combustor (16). A heat exchanger (34) may be arranged in the flow path to extract heat from the flow between the compressor and the component. One or more valves (36;64;66) in the flow path are actuated under the control of a controller (48;60) at a predetermined frequency of actuation so as to pulse the flow between the heat exchanger and the component, typically to improve the aerodynamic efficiency of turbine blades in use.

Abstract: There is provided a contact device (10) for application to an opposing surface (46;50) in use. The contact device comprises a support (12) and a plurality of contact members (14) aligned along the support. Each contact member has an end portion (15) spaced from the support and is independently resiliently mounted to the support such that the end portions (15) can conform to the opposing surface (46;50) in use and thereby provide a seal there-against. The contact members and/or support and may be planar in form and may be cut from a sheet metal material. The contact device may serve as a gas shield or a support jig or clamp device.

Abstract: A fluidfoil is disclosed including a leading edge and a leading edge zone behind the leading edge. The leading edge zone extends spanwise for the full length of the fluidfoil. The leading edge zone includes one or more deflected regions which locally reduce the angle of attack of the fluidfoil.

Abstract: A seal assembly including first and second components; a seal arranged between the first and second components to seal a secondary flow region from a primary flow region; and a second recess portion provided on a surface of the second component between the seal and the primary flow region, the second recess portion further being arranged to receive a first portion of a flow from the secondary flow region and being configured to promote a second flow feature within the second recess portion, wherein the second recess portion is set back from the surface of the second component such that a second portion of the flow from the secondary flow region bypasses the second recess portion.

Abstract: A method of determining the proportions of different powders in a powder comprises obtaining a sample of a powder, adding and mixing the sample into a molten material and freezing the mixture of powder and molten material to form a block. Computed tomography is performed on the block to produce a three-dimensional image of the block, the three-dimensional image of the block comprises a first shade, a second and a third shade corresponding to the material, a first powder particle and a sec and powder particle. The three-dimensional image of the block is analyzed to count the number of regions exhibiting the second shade and the third shade corresponding to the number of first powder particles and second powder particles respectively. The fraction of second particles in the powder is determined by dividing the number of second powder particles by the sum of the number of first powder particles and the number of second powder particles.

Abstract: A rotor blade has a radially extending aerofoil body having pressure and suction sides. The rotor blade further has squealer tip. The squealer tip includes a peripheral wall surrounding a cavity which is open at the radially outward end of the blade and at the trailing edge of the aerofoil body. The peripheral wall has at least one first region which extends radially from the aerofoil surface which has a first outer surface. The peripheral wall further has, along at least part of at least one of the pressure and suction sides, at least one second region inclined outwardly of the cavity with respect to the radial direction of the blade which has a second outer surface which extends obliquely outwardly of the blade. A radially outer portion of the second outer surface turns towards the radial direction to truncate the outward extension of the second outer surface.

Abstract: A method is disclosed for controlling a process in which a component 4 is moved relative to another component 6 such that at least one of the components 4, 6 experiences a reduction in magnitude in at least one dimension. Such processes may include for example friction welding. The method comprises monitoring energy input to the process and adjusting an input parameter for the process based on the monitored energy input. The monitoring of energy input is performed before any reduction in component magnitude has begun to take place.

Abstract: Conventional curable polymers tend to shrink upon curing whilst low shrinkage ultraviolet light curing polymers have a problem with respect to curing below surface areas of a component. By providing light transmitting elements and/or local ultraviolet light source precursors, greater depth of ultraviolet curing can be achieved and therefore enhanced acceptability with regard to component manufacture. The light transmitting elements may be formed by optic fibers or coatings to existing reinforcing fibers or through consideration of the refractive index of the cured and uncured polymer to create light transmission paths through the component. Ultraviolet light source precursors can be activated by heat or a “seed” light exposure or vibration to create localised ultraviolet curing of the polymer thereabout.

Abstract: A combustion chamber comprises an outer wall and an inner wall spaced from the outer wall. The outer wall has at least one mounting aperture extending there-through and the inner wall has threaded studs extending there-from. The threaded studs extend through the mounting apertures in the outer wall. Cooperating nuts locate on the studs and washers are positioned between the outer wall and the cooperating nuts. Each washer has a rim and a bore. The washers have one or more passages extending there-through from the rim to the bore of the washer to provide a flow of coolant through the passages in the washers, the mounting apertures in the outer wall and around the threaded studs to cool the threaded studs to increase the working life of the inner wall. Other cooling arrangements for the threaded studs are disclosed.

Abstract: A method of generating a medial mesh of an object. The method first includes obtaining a surface mesh of the object. Define a set of node normal vectors, each having its origin at a node and being directed towards the interior of the object. For each node: select a node normal from the set having their origins at that node; define a sphere wherein a surface of the sphere includes the node and the centre point is positioned at a scalar multiple of the node normal; increment the centre point along the scalar multiple; iterate until the surface of the sphere includes another node or element. The centre point is recorded as a medial point and the diameter as a thickness. The medial mesh is generated from the set of medial points and object thicknesses.

Abstract: A component, for example an aerofoil vane or other gas path structure in a gas turbine machine such as a gas turbine engine, in which an insulated electrical conductor path is embedded structurally integrally, and in which electromagnetic shielding, for the embedded electrical conductor path is provided structurally integrally.

Abstract: A propeller arrangement has a first propeller assembly providing a row of first propellers, and a second propeller assembly, rearward of the first propeller assembly, providing a row of second propellers. The first and second propellers are radially extendable and retractable. The propeller arrangement further has a control system for controlling the extension and retraction of the first and second propellers. The control system is arranged such that when the propellers of one of the first and second propeller assemblies extend, the propellers of the other of the first and second assemblies retract.

Abstract: A method for locating artifacts, such as particles or voids, in a material includes the steps of defining a path through a volume of the material, sensing the presence and type of any artifacts along the path and determining for each sensed artifact, the respective distance along the path. Analysis of the quantity of sensed artifacts and their respective position along the path enables the determination of measures for the artifact density, artifact size and artifact distribution in the material.

Abstract: A method for forming a pressure measurement hole in a component includes the step of forming a hole in a body of the component, the hole extending from a body surface of the component. An insert having a longitudinal passage is fitted into the hole such that the insert protrudes from the body surface. The protruding end of the insert is machined to define an insert surface profile matched to the body surface profile and displaced from the body surface by a distance substantially equal to a thickness of a covering layer that is to be bonded onto the body surface. A blocking pin is inserted into the insert passage. The covering layer is then bonded to the body surface in the region of the hole and insert after which the blocking pin is removed from the insert to open the pressure measurement hole.

Abstract: A diffusion bonded and superplastically formed turbomachine blade, the turbomachine blade comprising: a first layer (4); a second layer (6); and a membrane (2) disposed between the first and second layers (4, 6); wherein the membrane (2) is diffusion bonded to the first layer (4) along a plurality of first strips (10) and the membrane (2) is diffusion bonded to the second layer (6) along a plurality of second strips (12), wherein the first and second strips (10, 12) are offset from one another so that the membrane (2) is bonded to the first and second layers (4, 6) in an alternating pattern; wherein the membrane (2) has a recess (28) which extends into an area between an adjacent pair of first or second strips (10, 12).

Abstract: A rotor blade for a gas turbine engine, comprising an aerofoil having pressure and suction surfaces, leading and trailing edges, and an array of passages at a tip region of the aerofoil. The passages extend from the pressure surface to the suction surface of the aerofoil and are disposed so that the array creates, in operation, a planar jet of gas issuing from the suction surface. The jet is inclined outwardly from the suction surface and towards the tip, and in the direction from the leading edge to the trailing edge. The jet inhibits migration away from the suction surface of a clearance vortex formed by leakage of air over the tip of the rotor blade.

Abstract: An apparatus 2 comprising a cryogenic chamber 4 and a galvanic input interface 6 to the cryogenic chamber 4 configured to receive a lower amplitude electric current 8. A converter 10 is located within the cryogenic chamber 4 and configured to convert the lower amplitude electric current 8, provided by the galvanic input interface 6, to a higher amplitude electric current 12 for supply to a load 14 within the cryogenic chamber 4. A controller 16 is configured to control the converter 10 and to detect the onset of quench by comparing the duration of the charge/discharge cycle of the convertor with a stored value. The controller 16 may also compare an instantaneous value of load current with a stored value of load current.

Abstract: A rotor stage of a turbine has a rotational axis, a shroud and radially inward thereof a turbine blade defined partly by a pressure side wall, a suction side wall and a tip portion. The tip portion has a pressure side tip rib and a tip cavity floor defining a tip cavity. The pressure side tip rib has a width Wps, a height Hps above the tip cavity and defines a tip gap Gps with the shroud. The pressure side tip rib has a sloping side joining the tip cavity floor and having an angle ?ps to a radial line ZZ. The width Wps is in the range Gps to 5Gps, the height Hps is in the range 5Gps to 15Gps and the angle ?ps is in the range 20° to 70°.