Abstract: A method of manufacturing a metal component from metal powder comprises preparing (12) a metal powder, providing (14) gallium on at least part of the surface of at least some of the metal powder particles, encapsulating (16) the metal powder in a container, evacuating (18) the container to remove air and/or gas from the container, sealing (20) the container, hot isostatically pressing (22) the container to consolidate the metal powder particles to produce the metal component and removing (24) the container from the metal component. The process is used to produce gas turbine engine metal components, for example turbine discs with improved fatigue properties.

Abstract: An airblast fuel injector for the combustor of a gas turbine engine has, in order from radially inner to outer, a coaxial arrangement of an inner swirler passage, an annular fuel passage, an annular mid swirler passage, and an annular outer swirler passage. The fuel passage extends to a prefilming lip, and the inner and mid swirler passages swirl air past the prefilming lip so that fuel fed from the fuel passage to the prefilming lip is entrained by the swirling air into a fuel spray stream. The outer swirler passage has a convergent portion. The radially inward wall of said convergent portion is defined by a frustoconical separator element which separates the outer swirler passage from the mid swirler passage, the separator element converging in the direction of air flow to terminate in a lip at the mouths of the mid swirler passage and the outer swirler passage.

Abstract: A containment assembly for a turbo fan engine, has a casing arranged in use around a rotatable fan, to form a duct for the fan and a liner element disposed on an interior surface between the casing and blades of a rotatable fan. The liner element includes a body portion mounted in a recess in the casing and a wall portion arranged to form part of an inner wall of the duct. The wall portion and the body portion being attached and defining a containment cavity therebetween for containment of a detached fan blade fragment in use, wherein the wall portion has a moveable portion movable between a first configuration in which it lies substantially flush with the inner wall of the duct, and a second configuration in which it provides an opening through which a fan blade fragment can enter the containment cavity.

Abstract: A method of calibrating a high energy beam with a material source, the method comprising the steps of: using the high energy beam to provide an aperture, depositing material from the material source towards the aperture for a selected length of time and collecting the material which passes through the aperture, and adjusting the position and/or alignment of the material source relative to the high energy beam dependant on a comparison of the amount of material collected with a predetermined value.

Abstract: A liner panel for a fan casing of a gas turbine engine includes a honeycomb layer, a septum layer and an abradable layer. The fan casing is provided with a containment system in case of fan blade failure. In use, ice may be released from a fan blade in a first direction, and (in the case of a blade-off event) a fan blade or part of a fan blade may be released in a second direction. The panel has a compressive strength greater in the first direction than in the second direction such that the released ice will be deflected by the panel but the released fan blade or part of a fan blade will pass through the panel.

Abstract: A cutting tool (10) comprises a shank (12) for receiving a cutting insert (14) and a block (16) for delivering a flow of fluid to the cutting insert (14). Fluid is delivered to the cutting insert (14) through a fluid passageway (18) that extends through the shank (12) and the block (16). The block (16) is pivotable mounted on the shank (12). The block (16) pivots about screw (22) between a first and a second position. In the first position the block (16) is held in sealing arrangement with the shank (12) to allow the passage of a coolant through the fluid passage (18) to the cutting insert (14). In the second position the block (16) has moved to allow removal of the cutting insert (14) from the shank (12).

Abstract: The invention concerns an oil seal assembly 12, especially for a gas turbine engine, for use in situations, for example, where a shaft passes 2 through the wall of a bearing chamber 10, so that one side of the seal is in a “wet” zone 8 and the other side in a “dry” zone 14. The seal comprises two parts, a relatively stationary annular seal member 32 which runs against the surface 34 of a seal runner 36 carried by the rotatable shaft 2. Both parts of seals of this kind are designed to be a demountable service items. Usually the seal runner 36 is bolted to a flange 16 on the shaft 2. However, problems may arise with oil leakage through the bolt holes formed in the flange 16 and along the bolt threads. In order to solve these problems the invention proposes a double flange arrangement 42, 44, 46 (FIG. 3) in which the seal runner 36 spans both flanges 42, 44 and is secured to the flange 42 in the dry zone 14.

Abstract: An apparatus (60) for applying a dry film lubricant comprises a tool (62) and a pad (64). The tool (62) includes a handle (66), a cranked member (68) and a supporting member (70). The pad (64) is removably locatable on the supporting member (70). The supporting member (70) is oval in cross-section and the pad (64) includes an oval cross-section hollow member removably locatable on the supporting member (70). The supporting member (70) comprises locking means (78) to lock the pad (64) on the supporting member (70). The supporting member (70) comprises positioning means (80) to position the pad (64) on the supporting member (70). The tool (62) also has a shielding member (72) spaced from and arranged parallel to the supporting member (70). The handle (66) is arranged in a plane (A) substantially parallel to a plane (B) containing the supporting member (70) and to a plane (C) containing the shielding member (72). The pad (64) is substantially dovetail shape in cross-section to correspond to a rotor slot (40).

Abstract: An anti-icing coated metallic substrate includes molecules of an anti-icing material chemically bonded to the metallic substrate. The substrate is suitably a metallic article, particularly a high-performance weight-critical rotor component such as an aircraft propeller blade or an air intake fan blade of a gas turbine engine.

Abstract: A method for making a hybrid component comprises the steps of placing a lower shell in the lower half of an RTM form tool; placing layers of composite fabric on top of the lower shell to define a composite core; placing an upper shell on top of the layers; closing the RTM form tool; infiltrating the composite fabric with resin; curing the resin. At least one of the lower and upper shells comprises pins projecting generally perpendicularly to its surface, and the pins penetrate the composite fabric.

Abstract: A cutting tool (10) comprises a shank (12) for receiving a cutting insert (14) and a block (16) for delivering a flow of fluid to the cutting insert (14). Fluid is delivered to the cutting insert (14) through a fluid passageway (18) that extends through the shank (12) and the block (16). The block (16) is pivotable mounted on the shank (12). The block (16) pivots about screw (22) between a first and a second position. In the first position the block (16) is held in sealing arrangement with the shank (12) to allow the passage of a coolant through the fluid passage (18) to the cutting insert (14). In the second position the block (16) has moved to allow removal of the cutting insert (14) from the shank (12).

Abstract: An aerofoil structure (2) comprising: a cavity (12), the cavity (12) having a viscoelastic material (14) disposed therein; and a temperature regulating means (16) for regulating the temperature of the viscoelastic material (14).

Abstract: There is disclosed an aircraft propulsion arrangement including a gas turbine aircraft engine having a compressor, an oil system configured to route engine oil through a heat exchanger mounted so as to define part of an aerodynamic surface to the flow of ambient air, and a duct arrangement fluidly connecting the compressor to the heat exchanger. There is also proposed a method of operating the engine, the method involving the steps of: (a) flowing engine oil through the heat exchanger and thus into heat-exchange relationship with said ambient air; and (b) directing a bleed flow of compressor gas drawn from the compressor along said duct arrangement and into heat-exchange relationship with said oil in said heat exchanger, wherein said directing step (h) is performed selectively.

Abstract: A separator device is provided for separating dirt particles from a flow of cooling air fed to airfoils of the turbine section of a gas turbine engine. In use the separator device extends across a conduit which bypasses the combustor of the engine to convey pressurised cooling air carrying dirt particles from the compressor section of the engine to openings which direct the air into the airfoils. The separator device is configured to direct a first portion of the impinging cooling air flow away from the openings and to allow a second portion of the impinging cooling air to continue to the openings. The first portion of cooling air has a higher concentration of the coarsest dirt particles carried by the cooling air than the second portion of cooling air.

Abstract: A local electrical system having an electrical generator is connected to an electrical generator network. The local electrical system has a controller to avoid the non-detection zone of loss-of-mains relays. The controller is arranged to monitor the real power flow from the electrical generator network to the local electrical system and to determine if the absolute value of the real power flow is below a first predetermined value to determine if there is a close match between the power requirements of the local electrical system and the electrical generator. If there is a close match, then the controller is arranged to monitor the reactive power flow the same way. If there is a close match also with the reactive power, then the controller is arranged to adjust the target reactive power output from the electrical generator of the local electrical system.

Abstract: Disclosed are methods for designing vanes that, in use, are expected to be exposed to vibratory loading, in particular rotor or stator vanes for aero engines or turbomachinery. A quantitative characteristic (modeshape) is used which is a measure of correlation between the excitation force to which the vane is to be subjected in use and a vibrational mode of the vane, corresponding to a characteristic frequency of the excitation. The modeshape of the first design is determined. Then the first design is modified to give a second design, by one or more of leaning, sweeping or twisting the blade design, or by altering the local shape of the design, or by altering the material of the design. Then the modeshape of the second design is determined. The design modification gives rise to a reduction in the forced response levels.

Abstract: A cooling arrangement for an electrical connector for a superconductor including at least one superconductor arranged in a container and the container is arranged in a vacuum chamber. A cryocooler is thermally connected to the container to cool the container and the contents of the container including the superconductor. The electrical connector extends through the vacuum chamber and the container to the at least one superconductor. The electrical connector has a thermally conducting and electrically insulating arrangement. The thermally conducting and electrically insulating arrangement comprises an electrically insulating member contacting the electrical connector. A thermally conducting member contacts the electrically insulating member and the thermally conducting member is thermally connected to the to cool the electrical connector.

Abstract: Forming processes such as hot creep forming or superplastic deformation require a die former. This die former comprises a lower die and an upper die within which an initial roughly shaped component is placed and then shaped by downward pressure between the die parts. Previous arrangements have included a simple stop to engage edges of the component to define position. In use, due to the nature of the forming process, movement of the component can occur, and in such circumstances it may be necessary for the operator to adjust the position of the component during the forming process. By utilising pegs about the periphery at least of leading and trailing edges of a component a better edge definition is created, thereby reducing the requirement for interim positioning of the component in use.

Abstract: A conduit assembly for the communication of electricity, light or fluid, including at least one conduit, wherein the conduit assembly also includes a core member, the at least one conduit in contact with the core member and arranged in a convoluted path defined with respect to the shape of the core mernber, the at least one conduit thereby having a first direct length between its ends such that removal of at least a portion of the core member permits the at least one conduit to straighten in the region of the core member removal to increase its direct length to a second direct length, the second direct length being greater than the sum of the first direct length and the length removed from the core member.

Abstract: A pumped oil delivery system for delivering oil to moving parts of an aircraft jet engine includes a scoop delivery pump and an accumulator oil reservoir to maintain oil feed to the pump at all times. The system includes a first line to feed oil from the scoop pump to the oil reservoir, a second line to return oil from the oil reservoir to the scoop pump, and pressurized air for pressurizing the oil within the oil reservoir so as to maintain a continuous feed of oil to the pump. The system includes further lines for delivering oil from the scoop pump to the moving parts and for returning oil from the moving parts to the scoop pump. Moving parts include a self scavenging gear box utilizing the centrifugal pumping action of its gears to return oil to the scoop pump, and self scavenging bearing chambers using centrifugal effects of their rotating parts also to return oil to the scoop pump.