Abstract: A method of manufacturing a fibre reinforced metal matrix composite article, the method comprising placing metal coated (18) fibers (14) between a first metal ring (30) and a second metal ring (36). Each of the metal-coated (18) fibres (14) having a glue (22) to hold the metal-coated (18) fibers (14) in position. A solvent is supplied to the glue (22) on the metal-coated (18) fibers (14) to soften the glue (22) and pressure is applied to allow the metal-coated (18) ceramic fibers (14) to become more closely packed. Thereafter the glue (22) is removed and the metal coated (18) fibers (14) and first and second metal rings (30, 36) are consolidated and diffusion bonded together.

Abstract: A flux-switching machine stator comprising two or more C-cores, each C-core having two legs and a back portion joining the legs, and a permanent magnet arranged between legs of adjacent C-cores. Each leg has a main portion and a tip portion further from the back portion characterized in that the tip portion of each leg is angled relative to the main portion of the respective leg.

Abstract: A gas turbine engine blade containment system that includes a laminate material including first and second layers. The first layer is an inner layer within the second layer. The second layer includes a plurality of resiliently compressive springs extending transversely relative to the first layer, and each spring is encased in a crushable support material. The first layer includes a hard material to blunt a broken blade. The springs in the second layer are compressed and the crushable support material of the second layer is crushed to absorb energy of a broken blade.

Abstract: A nickel base superalloy consisting of 20 to 40 wt % cobalt, 10 to 15 wt % chromium, 3 to 6 wt % molybdenum, 0 to 5 wt % tungsten, 2.5 to 4 wt % aluminium, 3.4 to 5 wt % titanium, 1.35 to 2.5 wt % tantalum, 0 to 2 wt % niobium, 0.5 to 1 wt % hafnium, 0 to 0.1 wt % zirconium, 0.01 to 0.05 wt % carbon, 0.01 to 0.05 wt % boron, 0 to 2 wt % silicon and the balance nickel plus incidental impurities. The gamma prime phase comprises (Ni/Co)3 (Al/Ti/Ta).

Abstract: In a fluid system for a gas turbine engine, oil is supplied from an oil tank (10) by a constant displacement pump (12) to lubricate engine components (18). The oil is supplied to the components (18) via a heat exchanger (16) in which oil and fuel are placed in direct heat exchange relationship. The flow of oil to the components (18) is controlled by recirculating a proportion of the oil flow through a bypass (20). The bypass (20) regulates the flow of oil to the components (18) so that the amount of heat transferred to the fuel in the heat exchanger (16) is controlled. At low engine powers a greater proportion of the oil flows through the bypass (20) to reduce the oil flow to the components (18). This reduces the heat transferred to the fuel in the heat exchanger (16) and so prevents overheating of the fuel.

Abstract: A method of assessing the degradation of an oxide-forming coating on a component after a period of operational use of the component, said degradation of the coating being caused by depletion of the oxide-forming element within a remnant coating layer due to inter-diffusion of said element between the remnant coating and both an outer oxide layer and an inner, secondary diffusion layer, wherein a depletion parameter indicative of the depletion of the oxide-forming element in the remnant coating layer varies as a function of the surface roughness of the coated component, the method comprising the steps of: carrying out a non-destructive, quantitative measurement of the surface roughness of the component after said period of operational use; and, based on an estimation of the functional relationship between the surface roughness and the depletion parameter, using the result of said measurement of surface roughness to quantitatively assess the degradation of the coating.

Abstract: Engine health monitoring is used to assess the health of an engine, such as a gas turbine engine. Blades mounted on a shaft produce a modal response when excited. The shaft has an order related component that varies with the rotational velocity of the shaft. Modal responses are increased when the natural frequency range of the selected blade mode intersects with one of the order related components. By applying a short time chirp-Fourier transform with a frequency speed that is a function of a rate of change in the rotational velocity of the shaft a selected signal can be isolated. Cracks in the blades can be detected from the isolated signal.

Abstract: A pipe assembly including secondary leak containment and leak indication is described with particular reference to a lubricant-carrying pipe for supplying oil to an internal bearing chamber in a gas turbine engine. The oil pipe crosses a hot gas zone to a manifold on the engine inner casing so that an oil leak is a potential fire hazard. The connection into the bearing chamber manifold includes a secondary containment system that ensures that any leakage from the oil pipe seal is contained within an interstitial space between the pipe and a co-axial, secondary containment member. The interstitial space opens into a relatively safe zone outside the outer engine casing where the fire or safety hazard is eliminated or does not exist.

Abstract: A rotor arrangement comprising a rotor-section and a circumferential moveable seal around the rotor-section, the arrangement being such that, for a given rotation rate, the rotor-section is subject to an associated radial growth and a corresponding related axial displacement, relative to the seal, wherein the rotor-section is provided with an axially-varying profile for off-setting said radial growth of the rotor-section, adjacent the circumferential seal, at said given rotation rate.

Abstract: An aerofoil for a gas turbine engine, the aerofoil comprises a leading edge and a trailing edge, pressure and suction surfaces and defines therebetween an internal passage for the flow of cooling fluid therethrough. A particle deflector means is disposed within the passage to deflect particles within a cooling fluid flow away from a region of the aerofoil susceptible to particle build up and subsequent blockage, such as a cooling passage for a shroud of a blade.

Abstract: A cooling arrangement is provided in which an incident coolant flow is presented to a passage such that a proportion of that flow is diverted in order to create a standing relative overpressure in a chamber compared to the actual static pressure of the flow in the passage. In such circumstances through flow transfer apertures in the walls of the chamber forced coolant flows are presented for impingement upon surfaces and therefore greater heat transfer. Generally, coolant flow is presented to both ends of the chamber in order to create the relative standing overpressure in the chamber relative to the current static pressure presented in the passage through the incident flow. In such circumstances through utilizing the dynamic rotation or other motion of a component incorporating the arrangement a higher relative pressure is achieved for greater force coolant flow projection compared to the incident or actual static pressure of the incident coolant flow in the.

Abstract: An apparatus (10) for measuring temperature using luminescence thermometry, comprising: a photon emitter (42) for providing photons (3) of at least a first frequency; photoluminescent material (30) that produces photons (5) of at least a second frequency in response to the incidence of photons (3) of the first frequency; one or more photon receivers (44); and an optically dispersive element (50) for directing photons (5) of at least a second frequency produced by the photoluminescent material (30) into the photon receiver(s).

Abstract: A rotor (38) for a gas turbine engine (10) has a low emissivity surface finish, or high emissivity surface finish (44), on at least a portion of its surface (42) to reduce temperature differentials between an upper portion and a lower portion of the rotor (38). This reduces bowing of the rotor (38) to allow the gas turbine engine (10) to be started without harmful vibrations of the rotor (38).

Abstract: A method of manufacturing an article by diffusion bonding, the method comprising the steps of assembling first and second component parts having a joint therebetween; sealing the joint against infiltration by solid particulate material, without causing phase change of the component parts; and applying heat and isostatic pressure via a solid particulate material to form a consolidated joint by diffusion bonding.

Abstract: Apparatus for forming a cast component has a chamber for holding an alloy and which is rotated about an axis to separate an impurity from the alloy by centrifugal force. The chamber feeds a mould that is also rotating and into which the alloy is supplied to form a component by centrifugal casting.

Abstract: A method of heat treating a superalloy component comprises solution heat treating the component at a temperature below the gamma prime solvus temperature to produce a fine grain structure in the component. Insulation is placed over a first area of the component to form an insulated assembly. The insulated assembly is placed in a furnace at a temperature below the solvus temperature and maintained at that temperature for a predetermined time to achieve a uniform temperature in the component. The temperature is increased at a predetermined rate to a temperature above the solvus temperature to maintain a fine grain structure in a first region, to produce a coarse grain structure in a second region and to produce a transitional structure in a third region between the first and second regions of the component.

Abstract: The ducted fan (12) of a ducted fan gas turbine engine (10) is surrounded by a compartment (26), which is packed with bristles (38). Should a blade of the fan stage (12) disintegrate during operation of engine (10), the resulting fragments, if they pass through an abradeable honeycomb structure (32), will collide with the bristles (38), which will absorb the energy exerted by the fragments, and thus prevent puncturing of the outer wall (18) of the fan duct structure.

Abstract: A mounting arrangement 31 incorporates a blade pocket cavity 35, 135, 235 between a blade platform 34, 134, 234 and a rotor disc post 53. Coolant air is presented within the cavity 35, 135, 235 in order to provide cooling of the platform 34, 134, 234. In order to inhibit ingress of hot air from adjacent wheel spaces 36, an air curtain is created across an open end 45, 145 whereby coolant air is contained within the cavity 35, 135, 235. Air flow from the air curtain itself may pass along a surface 48, 148 to provide more direct cooling for the platform 34, 134, 234. Apertures 49, 50 may be provided in order to bleed coolant air from the cavity 35 and also draw an air flow 51 across the surface 48 for greater cooling efficiency.

Abstract: Interruption in supervisory position control signals can cause problems with respect to actuators which upon loss of such control signals for the actuator will generally slew to a fixed idle position. In such circumstances a machine such as a gas turbine engine in which an actuator is associated will not sustain performance even though there is continued local power supply to the actuator. By utilising a local controller which stores actuator response profiles for certain machine status stages through perturbation or marginal activation of the actuator an appropriate actuator response profile can be chosen and therefore sustaining control signals presented to the actuator to maintain machine operation.

Abstract: An integrally bladed rotor is constructed from a plurality of layers of organic matrix composite material wound together in a spiral fashion to form the disc portion of the rotor, and at each rotor blade position at least the outermost one of the layers is turned substantially radially outwards from the periphery of the rotor disc to form a blade. Each blade is finished with further pieces of organic matrix composite material bonded into position on the. An encircling blade tip shroud may be formed by further layers of material wound around the tips of the blades in conjunction with closed loop inserts in the spaces between blades.