Abstract: A fluid management apparatus and method, the apparatus including: a fluid conduit for the passage of a dispersion containing particulate matter; a laser arranged to provide laser light inside the fluid conduit; wherein, in use, the laser light heats the particulate matter sufficiently to generate incandescence; one or more sensors for detecting the incandescence of the particulate matter so as to determine a characteristic of the dispersion; and an electromagnetic wave generator operable to provide electromagnetic waves inside the fluid conduit at a position downstream of the laser light so as to vaporize at least a portion of the dispersion.

Abstract: A mounting assembly 2 for mounting a gearbox 10 to a gas turbine engine, comprising a mount ring 4 and a spigot pin 8 having a flange 22 at one end. The spigot pin 8 extends radially outwardly through a bore 14 in the mount ring 4 for engagement with a gearbox 10 and the flange 22 locates against a radially inner surface of the mount ring 4. The bore 14 supports the spigot pin 8 and dissipates forces exerted on the spigot pin 8, for example forces generated during a fan blade-off event.

Abstract: A shaft break detection system and a method of detecting shaft break for a gas turbine engine. A first indication is calculated from measured rotational speed of a shaft. A second indication is calculated from the rotational speed. A shaft break signal is generated if both indications are true.

Abstract: A flow discharge device, such as a compressor bleed outlet discharging into a bypass duct of a gas turbine engine, comprises an outlet panel 46 which is perforated by openings 48, 50 disposed in an array which tapers in the downstream direction with respect to the flow B in the bypass duct. The configuration of the array of openings 48, 50 creates a plume 60 of tapering form, which enables the bypass flow B to come together downstream of the plume 60 with minimal wake generation, to provide a shield of cooler air so as to avoid contact between the hot gas plume 60 and a wall of 27 of the bypass duct 22. The resulting aerofoil-shaped cross section of the plume 60 also reduces any blocking effect in the bypass duct 22, with consequent performance benefits for the engine fan.

Abstract: A connector is provided for joining two electrical harnesses. Each harness is formed from a flexible printed circuit board which provides a plurality of conductive tracks, and each harness has a substantially planar terminating region at which the conductive tracks of the harness fan out. One or more receiving holes are formed in each terminating region to extend to respective conductive tracks. Each receiving hole extends in a direction substantially perpendicularly to the plane of the respective terminating region. When in use, the connector includes a connection formation between respective terminating regions of the two electrical harnesses. The connector further includes a housing configured to hold the respective terminating regions of the two electrical harnesses in face-to-face relationship with the connection formation. The housing has one or more apertures through which the harnesses can exit the housing as they extend away from their terminating regions.

Abstract: An actuator is provided having a temperature activatable actuating member comprising an inductively couplable material. The actuator has an electrical heating element for electrically heating the actuating member. The heating element is configured to inductively couple with said material when an AC current is passed through the heating element such that an opposing electromotive force is induced in the heating element. A detector is provided for detecting activation of the actuating member by sensing a change in the AC impedance of the heating element.

Abstract: An acoustic panel includes a first cellular layer with cells having a first axis, a second cellular layer with cells having a second axis, and a perforated septum layer separating the first layer and the second layer. The cells of both layers have an end distal to the septum layer and an end which meets the septum layer, and the maximum diameter of the cells of the first layer is less than the maximum diameter of the cells of the second layer.

Abstract: A gas turbine engine having a rotational axis, an intake and a compressed gas source; the intake includes a lining having a facing which defines an inlet surface and an array of holes; the array of holes includes at least a first set of holes and a second set of holes, the holes of the first set of holes are angled a relative to a radial line and the holes of the second set of holes are angled ? relative to the radial line; the angles ? and ? are different. An active flow control arrangement including a compressed gas supply pipe, a valve arrangement, a controller, a compressed gas distribution pipe may be provided. Compressed gas may be provided to prevent the formation of separation of a main gas flow through the intake and prevent or remove ice accretion.

Abstract: By providing a tube of deformable material which can be located within a hollow cavity of a blade it is possible to provide an element which through friction engagement can absorb vibration energy and therefore damp vibration in a hollow blade. The tube incorporates a number of cuts and/or grooves in an appropriate pattern in order to define a deformation profile once the tube is expanded in location. The tube is secured in position internally upon an expandable element which is typically an inflatable device. Once in position the tube is retained in its expanded deformable profile and the engagement between the tube and the hollow cavity wall surface results in energy absorption through vibration episodes. It is possible to provide a tube formed from a shape memory alloy which will expand in location to engage the hollow cavity wall surfaces for energy absorption during vibration episodes.

Abstract: The present invention relates to a flow discharge device (30) for discharging a flow of gas (F) from a first gaseous fluid (A) into a second gaseous fluid (B) which is of a lower pressure than the first gaseous fluid. The discharge device comprises a valve (34) disposed between the first and second gaseous fluids and arranged to regulate the discharge flow (F) and a swirler means (50) disposed between the valve (34) and the second gaseous fluid. The swirler means (50) comprises a plurality of radially extending circumferentially spaced vanes (61, 63, 65). In use the swirler means (50) swirls the discharge flow (F). This acts to reduce the energy, and therefore the pressure of the discharge flow. This results in quieter operation.

Abstract: A turbine fuel supply system is disclosed as including a first sub-system having: a first nozzle for injecting fuel into a combustor of a turbine engine; a first valve controllable to communicate fuel to the first nozzle; and a first fuel manifold for communicating fuel to the first valve from a fuel source; the system further including a controller assembly for raising the pressure of fuel in the first fuel manifold; and the system being characterized in that the first valve is adapted to open in response to a predetermined pressure difference between the first fuel manifold and the pressure in the combustor, thereby allowing fuel to be communicated from the first fuel manifold to the first nozzle. The system may include a first recirculating conduit in fluid communication with the first fuel manifold and the fuel source, the first recirculating conduit allowing fuel not communicated by the first valve to be returned to the fuel source.

Abstract: A turbomachine casing assembly including: a first casing element arrangeable adjacent to one or more rotating aerofoil structures of a turbomachine; a second casing element provided at a radially outer position with respect to the first casing element; and an infill member disposed between the first and second casing elements, wherein an end of the infill member is set back from an end of the first casing element such that a void is provided between the first and second casing elements.

Abstract: An assembly for the removal of contaminants from a contact zone between respective contact surfaces 6, 8 of a first component 2 and a second component 4. At least one of the contact surfaces has a low friction element 10 provided with grooves 12 which extend through the contact zone such that, in operation, a pressure difference across the contact zone causes contaminants entering the grooves 12 to be expelled along the grooves 12 from the contact zone.

Abstract: A fan casing for a turbofan engine including an annular casing component of composite material including a body portion having an outwardly directed stiffening flange at one end, the stiffening flange being connected to the body portion by a radially outwardly stepped region, the fan casing also including a metallic ring which is coaxial with the annular casing component, the metallic ring being situated at least partially within the stepped region and being secured to the annular casing component.

Abstract: An epicyclic gearbox oil scavenge arrangement. The epicyclic gearbox is of the planetary or differential type and comprises an input sun gear (28); a plurality of planet gears (32) that mesh with the sun gear (28) and are driven therefrom; an annular planet carrier (34) that couples the planet gears (32) in known relative orientation and is configured to precess around the sun gear (28); and a ring gear (38) that meshes with each planet gear (32). The ring gear (38) comprises ejection apertures (44) that extend radially therethrough and the planet carrier (34) comprises at least one lobe (42) that extends radially from the periphery of the planet carrier.

Abstract: There is disclosed a rotary air-riding seal between a first structure and an adjacent second structure, including: first and second seal members defining respective seal surfaces facing to one another. The first seal member is provided on the first structure and the second seal member is mounted to the second structure towards the first seal member. At least one of said seal members is configured to generate a riding film of air between said seal surfaces. One of said seal members is supported for axial oscillation relative to the other seal member by a secondary support arrangement configured to bias said seal member towards the other seal member. The said secondary support arrangement accommodates relatively high frequency axial movements between the seal members.

Abstract: An aerofoil has first and second panels spaced apart from each other to provide a cavity, the cavity containing a damping material, the first panel has at least one protrusion extending therefrom within the cavity towards the second panel, the protrusion having a proximal end and a distal end, wherein the proximal end is secured to the first panel and the distal end is slidably mounted to the second panel.

Abstract: A composite material and method for manufacturing the material, the material including: a plurality of plies layered one on top of the other; and one or more through-thickness fibers which join one or more of the plurality of plies to one another; wherein the one or more through-thickness fibers form a boundary which delineates one or more discrete regions of the material.

Abstract: A bleed assembly for a gas turbine engine is provided. The assembly includes: a duct having an inlet and an outlet; a bleed valve that controls the flow of bleed fluid into the inlet; and a dome-shaped diffuser screen which covers the outlet. The diffuser screen has a plurality of through-holes for passage of the bleed fluid. Each through-hole has one or more nearest-neighbour through-holes at a nearest-neighbour spacing. At the periphery of the diffuser screen, the average nearest-neighbour spacing of the through-holes at a given radial distance from the centre of the diffuser screen increases with increasing radial distance.

Abstract: The invention relates to a fluid separator 40 having first and second inlets, a turbine and a separation chamber having a centrifugal separation member. The first inlet is in direct fluid communication with a turbine inlet, and in use delivers high pressure vent air flow from a first gas turbine engine bearing housing to the turbine. The second inlet is in direct fluid communication with the centrifugal separation member, and in use delivers low pressure vent air flow from a second gas turbine engine bearing housing to the centrifugal separation member. An outlet of the turbine is in direct fluid communication with the centrifugal separation member. The centrifugal separation member is driven by the turbine.