Abstract: A flow control arrangement 10 for controlling the flow of lubricant discharged from a bearing 12 includes a flow control member 24 locatable, in use, adjacent to the bearing 12. The flow control member 24 defines a generally circumferential outer edge 26a and is rotatable to direct lubricant discharged onto the flow control member 24 radially outwardly towards the outer edge 26a for ejection therefrom.

Abstract: A fluid calming member (18, 118, 218) for use in a fluid carrying arrangement (10) is disclosed. The fluid calming member is formed of a material that includes a porous metallic material.

Abstract: A method of manufacturing a fibre reinforced metal matrix composite article (10) comprises forming an annular groove (32) in the first metal component (30), forming a second metal component (36) and forming a number of fibre preforms (20). The fibre preforms (20) are placed in an annular channel (80) in a cassette (70). The cassette (70) and the first metal component (30) are arranged such that the annular channel (80) in the cassette (70) is coaxial with and faces the annular groove (32) in the first metal component (30). The fibre preforms (20) are moved from the annular channel (80) in the cassette (70) to the annular groove (32) in the first metal component (30). The second metal component (36) is placed on the first metal component (30) such that the fibre preforms (20) are arranged between the first metal component (30) and the second metal component (36). The second metal component (36) is sealed to the first metal component (30).

Abstract: Condition monitoring of an electrical machine is achieved by using electro-magnetic finite element analysis to analyse the machine based on model parameters corresponding with at least one fault condition. This allows the effect of the fault condition to be predicted. Metrology is used to recover live measurements for comparison with the predictions from the electro-magnetic finite element analysis to identify any fault signatures within the live measurements, in principle allowing those faults to be detected or diagnosed before they become catastrophic.

Abstract: A seal for an annulus filler for a gas turbine engine comprises a seal body releasably attached in use to the fan annulus filler, the seal body supporting two seal members so that in use one seal member is brought into contact with, and forms a seal against, an aerofoil surface of one of the fan blades, and the other seal member is brought into contact with, and forms a seal against, an aerofoil surface of the other of the fan blades.

Abstract: A bleed valve (30) for a gas turbine engine (10) comprises a diffuser (50), through which heated compressor bleed air flows (54) into a bypass duct (22) air stream (B), has a plurality of small holes (40). The plurality of holes (40) is divided into two or more arrays of holes (52p,q,r), each array of holes (52p,q,r) is angled (?) away from one another so that their respective bleed flows (54p,q,r) do not coalesce. This separation improves mixing with the air stream (B) and helps prevent hot bleed air damaging nacelle and other engine components.

Abstract: In a contra rotating propeller engine propeller blade assemblies are provided which rotate in opposite directions as a result of association with an epicyclic gear assembly acting as a differential gearbox. A carrier is provided to drive one propeller blade assembly. Actuators are provided to cause pitch angle adjustment of the respective propeller blades of the assemblies. These actuators, are secured upon a stationary structure and act through actuator rods and appropriate mechanisms to cause such angular pitch adjustment. Rotational de-couplers are provided to rotationally isolate the actuators whilst an actuator rod part acts across the assemblies and a rotational de-coupler to de-couple contra rotation between the assemblies whilst still allowing axial displacement for adjustment of the other propeller blade assembly.

Abstract: A sealing arrangement for sealing a leakage gap between relatively moveable parts in a flow path between a region of high fluid pressure and a region of low fluid pressure comprises a sealing member having an upstream surface, a downstream surface, a radially outer surface and a radially inner surface, the sealing member being in communication with a housing via a resilient element. The resilient element is fixedly joined to the upstream surface of the sealing member such that during operation both the radial force induced on the sealing member by fluid flowing axially into and circumferentially over the radially inner surface and the axial force induced on the sealing member because of a pressure difference across the sealing member is resisted by the resilient element.

Abstract: A method of forging a titanium alloy component comprises applying a protective coating onto the surface of the titanium alloy component. A glass lubricant coating is applied onto the protective coating and the titanium alloy component is forged at a high temperature. The glass lubricant coating comprises a borosilicate glass lubricant coating. The protective coating comprises an aluminide coating, a silicon modified aluminide coating, a platinum aluminide coating, an aluminium coating or a platinum coating. The titanium alloy component may be a compressor blade, or a compressor vane, of a high-pressure compressor of a gas turbine engine.

Abstract: A method of forging a titanium alloy component comprises applying a protective coating onto the surface of the titanium alloy component. A glass lubricant coating is applied onto the protective coating and the titanium alloy component is forged at a high temperature. The glass lubricant coating comprises a borosilicate glass lubricant coating. The protective coating comprises an aluminide coating, a silicon modified aluminide coating, a platinum aluminide coating, an aluminium coating or a platinum coating. The titanium alloy component may be a compressor blade, or a compressor vane, of a high-pressure compressor of a gas turbine engine.

Abstract: Transportation of larger diameter gas turbine engines can be problematic. In such circumstances it is known to separate the fan assembly (30) from the engine core (1) and other parts to facilitate transportation. Separation of the fan assembly (30) and engine core (1) can require a gantry which adds to inconvenience and costs. By utilising a platform (2, 44) with suspender members (43) in the form of boot straps (43) which extend down from an existing pylon (31) it is possible to remove an engine core (1) through a carriage dolly (3, 45) which moves along a rail (21 within the platform (2, 44) generally laterally until it is possible to lower the engine upon the platform to ground level. The platform (2, 44) and carriage dolly (3, 45) can then act as a stand for transportation of the engine core.

Abstract: A seal (48) between first and second relatively rotatable members (26,28). The seal comprises an abradable material on at least one of the relatively rotatable members (26,28). The abradable material comprises an open cell metallic foam (60) and polymeric films (64) closing the cells (62) of the metallic foam (60). The seal (48) is used between compressor rotor blades (26) and a stator casing (28) of a gas turbine engine (10). The seal (48) combines the sealing properties of a closed cell metallic foam with the abradability and manufacturing control of open cell metallic foam.

Abstract: The invention provides a method of forming a metal matrix composite (MMC) comprising a metal matrix and a fibrous material embedded therein, the method comprising bringing the metal matrix into the molten state and contacting the fibrous material with the metal matrix in the molten state in a directionally controlled manner, whereby the Young's modulus of the resultant cooled MMC is controlled in one or more particular direction and optionally at one or more particular location.

Abstract: A turbine disk (20) has a sealing plate (28) fixed to it by bayonet fixing features (36) and (40) formed in sealing plate flange (30) and disk flange (38). Abutments (42) and (44) are formed on the bayonet fixings, between which a multi part anti relative rotation locking member (46) is positioned in abutting relationship.

Abstract: Seal arrangements utilizing leaf seal elements are susceptible to excessive wear at their tips due to blow-down pressures. When the seal element is forced against a rear surface across the pressure differential between the sides A, B of an arrangement. These tips may be forced into engagement with the rotating shaft and therefore wear on the shaft as well as at the tip occurs. By providing channels which extend laterally across more than one seal element pressure relief is maintained and therefore a limit to blow-down force maintained. The channels also extend radially and normally on a low pressure side of the seal arrangement.

Abstract: In order to provide simpler manufacture and lift up and blow down control, leaf elements are provided which have profile edges arranged to associate with each other in order to create a ring carousel, either about the front or rear edge of a leaf seal arrangement. In such circumstances gas flow through the leaf seal arrangement encounters the profile edge in order to adjust leaf section position for appropriate sealing efficiency.

Abstract: A method of removing a deposit from a passage extending through a component comprising the steps, immersing the passage within a liquid, directing a liquid jet at the passage from a source within the liquid bath and with a sufficient velocity so as to remove at least a portion of the deposit.

Abstract: A hose assembly comprising a flexible hose and at least one co-extending flexible member. The hose and the member are secured together for tandem movement by means of at least one intermediate resilient mounting means. In operation tension and/or compression induced in the hose assembly by relative motion of the hose and co-extending flexible member is reduced by the compression and/or expansion of the at least one resilient mounting means.

Abstract: Power generating apparatus (10) including a cable (12) which rotatably mounts a plurality of power units (14). The power units (14) include wind power turbines (46) for producing power from the wind as the power units (14) fly in the sky whilst connected to the cable (12).

Abstract: A method of manufacturing an article by diffusion bonding at least two metal components (30,36) comprises assembling the metal components (30,36) into a stack relative to each other so that the surfaces (34,40) are in mating contact. The edges of the metal components (30,36) are sealed together, except for an aperture (49) where a pipe (50) is to be connected. A connector (51) has a first end (52) and a second end (53). The first end (52) has a smaller diameter than the second end (53) and a bore (54) extends through the connector (51) from the first end (52) to the second end (53). The second end (53) of the connector (51) is joined (57) to the stack. The pipe (50) is joined (58) to the first end (52) of the connector (51). The interior of the sealed assembly is evacuated via the pipe (50) and the pipe is sealed. Heat and pressure are applied to diffusion bond the metal components (30,36) together to form an integral structure.