Abstract: A flow reverser comprising a sleeve having a first part and a second part to define a flow path and axially separable from each other about a conjunction formed by a respective profile edges for the first part and the second part, the profile edges in a stowed position overlapping, the reverser characterised in that in a deployed position a nozzle part of each profile edge define together a nozzle jet and a reverser part of one edge profile is adjacent to a core to provide an effective flow deflector.

Abstract: A solid oxide fuel cell component (12) comprises a plurality of solid oxide fuel cells (24) arranged in spaced apart relationship, and in electrical series, on a surface of the porous gas permeable support structure (16). Each solid oxide fuel cell (24) comprises a dense gas tight electrolyte member (28), a porous gas permeable first electrode (26) and a porous gas permeable second electrode (30). Each electrolyte (28) is arranged in contact with a corresponding one of the first electrodes (26), each second electrode (30) is arranged in contact with a corresponding one of the electrolytes (28). Each of the first electrodes (26) is arranged in contact with the surface of the support structure (16). The interconnectors (32), the peripheral seal layer (34) and the electrolytes (28) are arranged to encapsulate all of the first electrodes (26) except for the surfaces of the first electrodes (26) in contact with the surface of the support structure (16) to prevent leakage of reactant from the first electrodes (16).

Abstract: In prop fan and contra fan gas turbine engines particularly utilized with regard to pusher configurations towards the aft of an aircraft, there is a significant problem with regard to debris and bird strikes resulting in particulate matter which may damage the engine thrust core. By providing an inlet rotor which fragments and creates a centrifugal aspect to the inlet flow, particulate matter can be directed to a bypass chute normally in the form of an annular section extending into a number of chute exits. In such circumstances, the particulate matter is removed continuously from the inlet flow and the chutes are normally angled to project any particulate matter towards propellers of the engine at robust positions.

Abstract: Structural components are traditionally made by rolling or extruding to define a desired shape. Such processes lead to extra costs and inflexibility with regard to bespoke design. By providing a structural component (28) comprising plates (1, 8, 9 having edges (2, 3, 16) extending regularly in a cruciform appropriate structural components (28) can be provided. The plates (1, 8, 9) are secured together through lock tabs (13, 18) passing through lock apertures (4a) and twisted into locking engagement. Either side of the locking tabs (13, 18) respective orientation tabs (14, 19) are provided to engage orientation apertures (4b) to facilitate local stability in the plates (1, 8, 9) for robust locking location. Components (28) can be formed from sheet materials and the outer profile of the components. (28) specifically shaped for particular requirements.

Abstract: There is disclosed a homopolar machine comprising a rotor and a stator. The rotor is arranged for rotation within the stator about a central axis and comprises a pair of axially spaced-apart rotor poles formed of magnetic material and which are interconnected by a structure comprising an axially magnetised magnet. The stator comprises a pair of conductor assemblies each of which is substantially annular in form and is provided around a respective rotor pole. The proposed arrangement provides a very simple and robust machine suitable for operation at very high speeds as a generator and which produces a purely is DC output.

Abstract: A rotor assembly, for a gas turbine, has a plurality of rotor discs interconnected by an axially extending rim. The outside of the rim has a circumferential array of dovetail slots and the underside of the rim has a circumferential channel which extends radially part way into the slots, the respective discs thus being interconnected axially across the channel by an array of circumferentially spaced connecting portions. There is an array of blades, each blade having a blade root secured in a respective one of the dovetail slots.

Abstract: A sealing assembly (100) for at least partially sealing a gap (102) leading to a void (104) between first and second members (110, 120), the first and second members forming part of a gas-washed surface of a jet engine, wherein the sealing assembly comprises: a bridging portion (130) couplable to one of the first and second members and movable to engage the other of the first and second members so as to block off the void between the first and second members from the gas-washed surface.

Abstract: A method of replacing a integrally bladed rotor section in a one-piece drum rotor, the method comprising removing the integrally bladed rotor section, replacing the integrally bladed rotor section with a replacement rotor section, and joining the replacement rotor section to the drum rotor by diffusion bonding under an axial contact pressure exerted between one or more respective pairs of bonding surfaces on the new rotor section and the drum rotor.

Abstract: A combustor wall element arrangement for a gas turbine engine comprises an upstream wall element (50A) overlapping a downstream wall element (50B) and defining a gap (37) and an outlet (35) therebetween. In use, a coolant flow exits the outlet (35) to provide a coolant film (D) across at least a part of the downstream wall element (50B). The outlet (35) has a smaller dimension, normal to the downstream wall element (50B), than the gap (37) thereby increasing the velocity of the coolant flow across at the downstream wall element (50B). The resultant film coolant flow is effective further across the downstream wall element.

Abstract: A method of analysing measured data from a system having multiple associated system variables, the method including the steps of: a) optimizing an error function relating the measured data to a predetermined number of the system variables to adjust the system variables; b) selecting a subset of the adjusted variables; and c) re-optimizing the error function by adjusting only the variables in the subset. A method of identifying likely contributors to an error caused in measured data from a system which has multiple associated system variables. A method of analysing measured engine service or test data form an engine having a plurality of associated system variables, includes the step of optimizing an error function which relates the measured data to a predetermined number of the system variables, by least-absolutes optimization wherein the error function is a sum of absolute variations.

Abstract: Within a turbine engine a heat exchanger may be provided to cool compressor air flows to be utilized for cabin ventilation or other functions. A fluid flow acting as a coolant for the heat exchanger is generally drawn from the by-pass duct of the engine and a dedicated outlet duct is provided such that the exhausted fluid flow from the heat exchanger is delivered along the conduit duct to a low pressure region. In such circumstances, an appropriate pressure differential across the heat exchanger is maintained for operational efficiency when required, whilst the exhausted fluid flow is isolated and does not compromise the usual engine ventilation vent exit area sizing. Over-sized ventilation vents would create an aerodynamic step and therefore drag upon the thrust of the engine.

Abstract: First and second components 2, 4, which may be metallic components, are joined together in a process which comprises introducing a sinterable powder 20 between the components, the powder being retained within a receptacle 16, displacing the component 4 towards the component 2 to compress the powder, and subsequently applying heat and pressure to the powder 20 to form a sintered bond.

Abstract: A tile is provided for lining the hot side of a wall of a combustor. The tile has a tile body with one or more bosses protruding from the cold side thereof. The or each boss extends, in use, through the wall of the combustor and has a threaded recess formed therein for threadingly connecting with a bolt which is inserted into the recess from the cold side of the combustor wall. The bolt fastens the tile to the combustor wall.

Abstract: An electrical generator arrangement comprising a distribution network having a first generator and a second generator, the first generator arranged to provide electrical power to a transmitter source, the second generator coupled to the distribution network by a switch to enable isolation of the second generator, the switch associated with an electrical characteristic comparator to compare the phase and/or frequency of the voltage provided by the second generator with the incidental modulation of a transmitter signal from the transmitter due to variations in the phase and/or frequency of the voltage provided by the first generator to the transmitter, the comparator arranged to operate the switch to isolate or connect the second generator to the distribution network dependent upon a variation in the change of the phase and/or frequency of the voltage provided by the second generator and the incidental modulation of the transmitted signal.

Abstract: A turboprop propulsion unit for an aircraft comprises a propeller 22 which is driven by a core engine by means of a propeller turbine 26 which drives the propeller 22 through a shaft 28 and a propeller gearbox 24. Restarting of the engine in flight is achieved by windmilling of the propeller 22, which drives a propeller gearbox lubricant pump 30. A diverter valve 40 causes lubricant delivered by the propeller gearbox lubricant pump 30 to be supplied to a turbomachinery lubricant pump 18 along a restart conduit 44, so as to drive the turbomachinery lubricant pump 18 as a motor. Torque generated by the turbomachinery lubricant pump 18 is transferred through an accessory gearbox 12 to a spool 4, 6, 8 of the core engine 2 and to a fuel pump 16. Control of the pitch of blades 36 of the propeller 22 enables the windmilling propeller 22 to achieve a desired speed of the spool 4, 6, 8 and output of the fuel pump 16 sufficient to restart the engine 2, even at low air speeds.

Abstract: A method of friction welding comprising providing a first workpiece (24) having a first weld surface (38) and a second workpiece (26) having a second weld surface (40). In a first region (42) adjacent the first weld surface (38) the first workpiece (24) is arranged at an angle (?) of substantially 90° to the first weld surface (38) and in a second region (44) adjacent to the first region (42) the first workpiece (24) tapers away from the first weld surface (38). The first workpiece (24) is arranged such that in the second region (44) the first workpiece (24) is arranged at an angle (?) greater than 90° and less than 180° to the first weld surface (38). The first and second workpieces (24, 26) are arranged such that first weld surface (38) of the first workpiece (24) abuts the second weld surface (40) of the second workpiece (26).

Abstract: A balancing assembly for a rotor comprises a mass, a displacement arrangement for displacing the mass along a guide arrangement. The guide arrangement extends circumferentially and the displacement arrangement can move the mass circumferentially around the principal axis of the rotor during rotation of the rotor.

Abstract: A method of manufacturing a reinforcing edge for attachment to a turbo machine aerofoil, wherein the reinforcing edge comprises a relatively thick nose portion contoured for fitting along the edge of the turbo machine aerofoil, and a pair of opposing, relatively thin, tail portions for overlapping the suction surface and pressure surface respectively of the aerofoil, the method comprising: pressure forming a predefined hollow workpiece under fluid pressure from a respective pre-form, the hollow workpiece incorporating the reinforcing edge; and cutting out said reinforcing edge from the hollow workpiece, wherein the pre-form is created by bonding a pair of relatively thin metal sheets to opposite faces of a relatively thick inner plate or bonded stack of inner plates, the inner plate or stack of inner plates having an opening which defines a closed cavity between the metal sheets for introducing said fluid pressure, each tail portion of the reinforcing edge being constituted by part of a respective one of the

Abstract: A protective leading edge strip component for an aerofoil is formed from a sheet of PEEK fabric woven in two-dimensions by draping the sheet over a male moulding tool (12) the shape of which represents the shape of a leading edge of the aerofoil, and applying a female moulding tool (14) so as to trap a portion of the PEEK fabric between the two moulding tools and applying heat and pressure.

Abstract: A superconducting fault current limiter comprises a superconducting element having a plurality of superconducting portions and at least connector. Each superconducting portion has end regions and each connector is connected to the end regions of adjacent superconducting portions to electrically and thermally connect adjacent superconducting portions of the superconducting fault current limiter together. Each connector provides a local reduction in the critical current and quench current of the end regions of the superconducting portions in contact with the at least one connector. This provides a phased transition of the superconducting fault current limiter in relation to the severity of a fault current.