Abstract: A blade includes a root and an elongate portion extending to a tip, the elongate portion having an aerofoil-shaped cross-section. The aerofoil has leading and trailing edges, and suction and pressure sides. The tip includes a squealer defining a gutter at the tip, the squealer extending from the trailing edge along the entirety of a first of the suction and pressure sides, around the leading edge and partly along a second of the suction and pressure sides leaving a gap between the trailing edge and an end of the wall. A main trailing edge cooling channel extends within the elongate portion in a direction from root to tip adjacent the trailing edge and exits into the gutter. The main trailing edge cooling channel includes a bend just downstream of the exit, the exit displaced from a camber line of the blade elongated portion towards the second side.

Abstract: A blade has a root portion and elongate portion extending from the root portion to a tip. The elongate portion has an aerofoil-shaped cross section having leading and trailing edges and suction and pressure sides. The tip may include a gutter defining squealer. The squealer has a wall extending from the trailing edge and along a substantial portion of the tip perimeter. A main trailing edge cooling channel extends within the elongate portion in a direction from root to tip adjacent the trailing edge and exiting into the gutter. A gallery channel is arranged just behind the gutter and extends from an open end intersecting the main trailing edge cooling channel to a closed end located just behind a trailing edge apogee. Cooling channels extend from the gallery channel and through the squealer wall. The gallery channel diameter is greater at the open end than the closed end.

Abstract: A boundary layer Ingesting (BLI) fan system operates with a highly non-uniform flow field that propagates through the fan stage. The fan stage suffers from hub separations, increased wake thicknesses and casing losses. These loss sources can be reduced or eliminated by varying the inlet metal angles and/or chordal lengths of the downstream fan stators.

Abstract: The novel nickel-base superalloy useful in an additive manufacturing process or a powder-based manufacturing process includes the following composition in wt %: Cr 8.0-8.5; Co 9.0-9.5; Mo 0.4-0.6; W 9.3-9.7; Ta 2.9-3.6; Al 4.9-5.6; Ti 0.2-1.0; Hf 0-0.05; C 0.005-0.03; B 0.005-0.02; Zr 0.005-0.1; Nb 0.2-1; Mn 0-0.6; and S 0-0.002 (?20 ppm); the balance nickel and incidental elements and unavoidable impurities.

Abstract: The present invention provides a method of forming a leading edge for an aerofoil component e.g. an aerofoil blade. The method comprises forming a pre-form having a precursor edge and processing said precursor edge to form the leading edge. The pre-form is formed using metal injection molding. The leading edge may have an elliptical profile.

Abstract: Nozzle for engine has coaxial arrangement of inner pilot and outer mains airblast fuel injectors and intermediate air-swirler passage sandwiched between the outer and inner air-swirler passages of the pilot and mains airblast fuel injectors, respectively. The nozzle has an annular first-splitter wall separating the pilot outer air-swirler passage from the intermediate one. An outer surface profile of the first-splitter wall defines radially inner side of the intermediate air-swirler passage. The nozzle has an annular second-splitter wall separating the intermediate air-swirler passage from mains inner air-swirler passage. An inner surface profile of second-splitter wall defines radially outer side of intermediate air-swirler passage. The outer and inner surface profile of the first and second splitters walls, respectively, have convergent sections facing each other forming convergent portion of the intermediate air-swirler passage.

Abstract: A method of forming a metal matrix composite (MMC). The method comprises providing a fiber (26) comprising a ceramic material coated with a metal, providing a winding head (12) having a plurality of circumferentially spaced radially extending alternate first and second finger members (18, 20), the finger members each defining a winding surface (22, 24), the winding surface of each first finger member facing a first axial direction, and the winding surface of each second finger member facing a generally opposite axial direction, wherein adjacent winding surfaces (22, 24) of the first and second finger members (18, 20) are spaced in a circumferential direction, and define an axial spacing less than the diameter of the fiber (26), and winding the fiber around the winding head (12) between the winding surfaces (22, 24) of the first and second finger members (18, 20).

Abstract: An end-wall component of the mainstream gas annulus of a gas turbine engine having an annular arrangement of vanes, the component including a cooling arrangement having ballistic cooling holes (33) through which, in use, dilution cooling air is jetted into the mainstream gas upstream of the vanes to reduce the mainstream gas temperature adjacent the end-wall, wherein the cooling holes are arranged in one or more circumferentially extending rows and wherein the axial position of the cooling holes in the or each row varies.

Abstract: A gas shield arrangement for a gas turbine engine, the gas shield arrangement comprising: a first gas shield arranged to cover an inlet of a gas flow path of the gas turbine engine; and a second gas shield arranged to cover a first outlet of the gas flow path of the gas turbine engine.

Abstract: A method and apparatus for welding a first component to a second component. A scanning head is positionally calibrated within a localised work envelope including the components, the positional calibration being referenced to at least one datum feature within the work envelope. Profiles of the components are scanned within the localised work envelope using the calibrated scanning head. A cloud point data image of defined coordinate positions of surfaces and edges to be welded within a space envelope is generated from the scanned profiles. A robotic welding torch electrode tip is scanned using the calibrated scanning head to determine a defined coordinate position of the electrode tip within the space envelope. The components are welded using the torch, the torch controlled using the cloud point data image and the defined coordinate position such that the electrode tip is held at pre-determined stand-off positions around the components during the welding.

Abstract: A method of attaching a projection to a thin walled component, the thin walled component having a first surface and an opposite second surface, the method comprises the steps of: (i) providing a thin walled component; (ii) identifying a first position on the first surface of the thin walled component; (iii) building a hollow thin walled lattice structure on the second surface at a second position using a liquid metal deposition process, the second position corresponding to the first position; and (iv) building a projection on the first surface at the first position using a liquid metal deposition process.

Abstract: A fuel flow system comprising a fuel manifold and a fuel nozzle. A fluidic valve having an inlet, a first outlet and a control flow inlet. The inlet is coupled to the fuel manifold. The first outlet is coupled to the fuel nozzle. The control flow inlet is coupled to a source of control fuel. The fluidic valve is configured to selectively couple the inlet to the first outlet dependent on the control flow into the control flow inlet.

Abstract: A gas turbine engine fan stand including a base frame and a fan case frame coupled together at one edge by a hinge. The fan case frame is arranged to: rotate about the hinge between abutting the base frame and substantially perpendicular thereto; and tilt about a yaw axis perpendicular to the hinge and in the plane of the fan case frame. The fan case frame further including a coupling arrangement arranged to rotate about a roll axis and to couple a fan case to the fan case frame. A gas turbine engine stand assembly including a fan stand and a core stand. A method of splitting a gas turbine engine and a method of reassembling a gas turbine engine.

Abstract: A gas turbine engine comprising a stator, wherein the stator comprises laminated oscillating heat pipes.

Abstract: A vane for a gas turbine engine has a pressure surface and a suction surface. The vane comprises an arrangement of internal channels and a plurality of conducting members extends from the channels towards the suction surface and/or the pressure surface.

Abstract: An oil cooling system for an engine includes an oil input line configured to receive heated oil from a component, an oil cooler configured to cool oil and direct oil to an oil return line and a first bypass line configured to selectively bypass oil from the input line to the return line without passing through the oil cooler. The first bypass line includes a first oil pressure actuated valve urged toward a closed position, and configured to move toward an open position where a pressure differential across the valve exceeds first predetermined pressure. The first bypass line further includes a second oil pressure actuated valve urged toward an open position, and configured to move toward a closed position where pressure differential across the valve exceeds a second predetermined pressure. The second predetermined pressure is greater than first predetermined pressure, and the first and second valves are provided in series.

Abstract: A method of detecting a diode fault in an AC signal rectifier circuit, the AC signal rectifier circuit including a plurality of diodes, and being arranged to supply a rectified output voltage to a load, wherein the method includes the steps of deriving an operating value indicative of the ratio of the voltage magnitudes of a first harmonic frequency and another harmonic frequency of the rectified output voltage across the load; and determining whether a fault has occurred in one or more diodes on the basis of the derived operating value. The first harmonic frequency is preferably the fundamental harmonic frequency, and/or the another harmonic frequency is preferably the 6th harmonic frequency.

Abstract: The invention relates to a thermal barrier coating removal method. A metal component (32) having a thermal barrier coating is located in a vessel (12) for containing an inert liquid reservoir. The vessel (12) has a releasably sealable closure (14) so as to allow the vessel interior to be maintained at an elevated pressure in use. The vessel is heated and the liquid therein is maintained at a temperature greater than 100° C. for an extended period of time such that thermal barrier coating breaks up as a result of internal stress caused by a crystal structure change in the thermal barrier coating.

Abstract: A workpiece for use with a friction welding process comprises a weld surface. The weld surface comprises a central ridge surface extending along the weld surface, with the central ridge surface being flanked on either side respectively by a first pyramidal surface and a second pyramidal surface. The first pyramidal surface subtends a first pyramidal angle with the central ridge surface, and the second pyramidal surface subtends a second pyramidal angle with the central ridge surface. The first pyramidal surface is further flanked by a third pyramidal surface, and the second pyramidal surface is further flanked by a fourth pyramidal surface, with the third pyramidal surface subtending a third pyramidal angle with the central ridge surface, and the fourth pyramidal surface subtending a fourth pyramidal angle with the central ridge surface. Each of the third pyramidal angle and the fourth pyramidal angle is less than 90°.

Abstract: An air cooled component for a gas turbine engine including a first wall and a second wall having opposing inner surfaces to define a gap therebetween, and a lattice of intersecting elongate ribs extending longitudinally along the first and second walls and transversely between the inner surfaces of the first and second walls to provide a plurality of cells. One or more portions of the ribs include an aperture to provide a flow path between adjacent cells so that the cells are in fluid communication.