Abstract: A gas turbine engine comprising a nacelle having an intake, the intake defining a generally annular chamber, an engine accessory and a heat exchanger for cooling a fluid of the accessory. The chamber is closed and the heat exchanger is disposed within the chamber operable to provide heat to prevent ice forming on the intake during engine operation.

Abstract: A turbine component such as a turbine blade has a cooling chamber that is tapered. The taper induces and maintains a helical swirl that improves the cooling efficiency of the cooling process and enables the turbine component to operate at higher temperatures.

Abstract: Rotatable discs combined with turbine blades in engines must be tested for critical life analysis. Thus, consideration must be made as to life expectancy for such components as a result of tensile circumferential hoops as generated by the weight of blades under rotation as well as compressive axial stress as a result of thermal gradients during initial warm up. Previous testing arrangements have considered tensile circumferential hoop stress but not compressive axial stress combinations such as “Von Mises” stress. By provision of bend structures 13, 223 a bending moment is created about a base 2, 22 formed in a test component 1, 21 such that a bending moment force 4, 24 creates a bending moment in the test component 1, 21. This bending moment results in a compressive axial stress reminiscent of that in a practical turbine engine disc as a result of initial thermal gradients. In such circumstances a more realistic testing of the component 1, 21 representative of a practical disc/blade combination is achieved.

Abstract: A solid oxide fuel cell (10) comprises an anode electrode (12), a cathode electrode (14) and an electrolyte (16) between the anode electrode (12) and the cathode electrode (14). A gaseous fuel is supplied to an anode chamber (18) partially defined by the anode electrode (12) and a gaseous oxidant is supplied to a cathode chamber (20) partially defined by the cathode electrode (14). The electrolyte (16) comprises a first dense non-porous layer (22), a second porous layer (24) on the first dense non-porous layer (22) and a third dense non-porous layer (26) on the second porous layer (24). The anode electrode (12) is arranged on the first dense non-porous layer (22) and the cathode electrode (14) is arranged on the third dense non-porous layer (26). The second porous layer (24) acts as a buffer between the first dense non-porous layer (22) and the third dense non-porous layer (26) to prevent defects propagating between the layers (22,26) and to prevent fuel and oxidant leaking through the electrolyte (16).

Abstract: A blade arrangement 31 includes an array of radially extending blades 20, which may for example comprise a fan of a gas turbine engine for an aircraft. The blades 20 are mounted for rotation about a central axis X-X. The blade arrangement 31 further includes a damping arrangement 32 comprising means 34 for inducing an axi-symmetric magnetic field whose axis of symmetry coincides with the central axis X-X of rotation of the blades 20. The damping arrangement 32 is configured such that when the magnetic field is induced, any movement of the blade 20 other than pure rotation about the central axis results in the magnetic field causing a force to be exerted on the blade 20, the force resisting such movement. The damping arrangement may be provided with means for inducing the magnetic field only when there is an increased likelihood of vibration of the blades, for example when a foreign body has entered the air intake of the engine.

Abstract: A device (10) for use in the verification of handwriting, comprising: a body (12) having a surface (11) over which a writing instrument (8) is moved during the generation of a piece of handwriting; a transducer (14) for transducing stress-wave activity in the body (12) to an analogue time varying signal (15); and digitizing means (22) for converting the analogue time varying signal (15) into a digital signal (27, 31, 11), the digitizing means (22) comprising a sampler (22) arranged to under-sample the analogue time varying signal (15).

Abstract: A nozzle guide vane arrangement comprising a vane member having a platform portion extending forwards of a leading edge of the vane member, the platform portion having a first securing member and a second securing member to provide at least part of the means to retain the vane member in use, the arrangement characterised in that the first securing member and the second securing member are staggered with an axial displacement relative to each other upon the platform portion in the direction from the leading edge to a trailing edge of the vane member.

Abstract: Varying the fan nozzle flow area in a gas turbine engine allows adjustment of the bypass flow for varying operational conditions such as cruise and take off. However, care must be taken with regard to variation in order not to introduce drag or operational susceptibility to failure. By provision of a deformable member having a contiguous surface, which is deformed laterally from a splitter such as a pylori variation in flow area is achieved. A deformable member will be secured through seals to ensure a smooth surface. Actuation may be through a shape memory alloy material or provision of mechanical actuators to cause deformation of the contiguous surface.

Abstract: A combustor for a gas turbine engine comprising at least one combustor air intake chute wherein at least one of the air intake chutes is configured to enhance the heat transfer relationship between the chute material and the air flowing over it. The air intake chutes have at least one raised feature formed on their inner surface which extends into the airflow passing through the chute. The raised features may take the form of a circumferential rib, an axial rib or a pedestal, or any combination of the same.

Abstract: A spacer arrangement 1, 40 is provided in which wedges 5, 6; 45, 46 are arranged to have an interface 7, 47 between them such that a thermally variable member 8, 48 can cause relative motion between the wedges 5, 6; 45, 46 to adjust an arrangement lateral dimension dependent upon temperature. In such circumstances with the arrangement 1, 40 positioned within a gap 3 between a casing 14 and unison ring 13, retention of position of that unison ring 13 can be maintained. The unison ring is arranged to adjust position of variable vanes.

Abstract: A method for joining first and second components, using brazing material to enable the formation of a brazed joint by heating the brazing material when the first and second components are in a juxtaposed position, comprises bringing the first and second components into a juxtaposed position so that the brazing material is in contact with the first and second components and plastically deforming the brazing material to interlock the first and second components.

Abstract: An injection-moulded thermoplastic mini-platform (42) is adhesively bonded, in use, to the aerofoil surfaces of a fan blade (312) in a gas turbine engine. The mini-platform (42) is divided into a number of leaves (46), to increase its flexibility, and ribs (48) beneath the leaves (46) provide additional stiffness in the radial direction. In the event that a fan blade is released in operation, the mini-platform (42) is designed to detach from the blade (312) and/or to break apart, so that damage to other components of the engine is minimised.

Abstract: A wall structure for a gas turbine engine combustor has an inner wall and an outer wall defining a duct, the wall structure including an outer wall having a radial step and an inner wall overlapping the radial step, a duct being defined between the inner and outer walls for the passage of cooling air; the wall structure being characterised in that the inner wall has a local thickening opposing the radial step. The velocity of cooling air through the duct is maintained and heat transfer subsequently improved.

Abstract: Monitoring of clearance gaps between a rotating component and a surrounding cowling surface is difficult in view of the general packaging constraints. Furthermore, when such operation occurs at high temperature there may be distortion in view of natural expansion and contraction over thermal gradients of the monitoring arrangement. By provision of a diffractive optical element with light guided for reflection against an aperture end and a part of a rotating component, it is possible through shift in the reflective wavelength frequencies to monitor and determine clearance gaps between that aperture end and incident parts of the rotating component.

Abstract: A bearing housing 1 is designed to accommodate a bearing 4 within its outer walls 3. The bearing 4 upon rotation generates a centrifugally dispersed oil spray from its peripheral edge 7 and this spray is collected upon a facing surface of the wall 3. An out-take 6 has a relatively wide chordal arc opening across which a baffle 8 is presented such that there is a spaced opening 10 between a leading edge 9 of the baffle and a portion 3a of the housing 1. In such circumstances oil is scavenged from adjacent to the inner surface of the wall 3 in order to facilitate oil flow through the bearing 4 and out of the housing 1 such that it has a reduced residence time within the bearing 4/housing 1 and so is less susceptible to temperature induced degradation.

Abstract: A wall structure for a gas turbine engine combustor has an inner wall and an outer wall defining a duct. The duct diverges as it extends in the general direction of fluid flow within the combustor. Cooling air is fed into the duct through angled cooling holes which provide a film of fluid over the outer wall of the combustor should the inner wall be eroded because of the high temperatures in the combustor.

Abstract: A core 14, for use in a casting mould to form a cavity in a cast component such as a blade or vane of a gas turbine engine, has a relatively fragile thin-walled region 22. A bead 38 is formed along a lateral edge 26 of the thin-walled portion 22 in order to reduce cracking or other damage in the thin-walled portion 22.

Abstract: An engine mounting arrangement is provided in which a mounting structure is created through fins (21, 42) extended between a core (22, 46) and a mounting ring (23, 48). The fins (21, 42) have a tangential lean and substantive planar aspect in order to create an appropriate load transfer path for torque and thrust loads in an engine when secured upon a hanger mounting (20) and through utilizing further struts (25, 26) extending from spaced locations upon the mounting structure to rearward anchor positions on a pylon (27) which also has the hanger mounting (20) attached.

Abstract: A combustor assembly comprising a combustor liner having an opening and a combustor chute, which is formed of a sheet material which is bent to form the desired chute. The chute allows the passage of cooling and dilution air into the combustor.

Abstract: A transition duct for a gas turbine engine typically contains one or more non-turning fairings. These fairings disturb the air flow through the duct, leading to flow separation and aerodynamic inefficiency. The invention proposes non-axisymmetric perturbations in the duct end walls to minimise these undesirable aerodynamic effects. This permits the construction of shorter and lighter transition ducts, with more pronounced curvature.