Abstract: A method of replacing a fan case liner panel in an engine fan case is provided. In one illustrative form, the method may include applying heat to an engine fan case to debond an adhesive layer, removing the first fan case liner panel, and bonding a second fan case liner panel.

Abstract: A method of manufacturing a component (100) having a main part (101) and a projecting feature (104,114), the method comprising providing a shaped void (210) corresponding to the component, locating a pre-formed element (214) in a feature region of the shaped void which corresponds to the projecting feature, locating powder (212) within the shaped void; and forming the element and the powder into the component such that the element creates at least a part of the projecting feature.

Abstract: A fan outlet assembly comprises a fan discharge nozzle having a radially inner platform, a radially outer platform arranged coaxially and in radial alignment with the radially inner platform and a circumferential array of outlet guide vanes (110) spanning an annulus defined by the radially inner platform and radially outer platform. An annular duct extends downstream from the circumferential array, the duct having a radially outer wall (112) contiguous with the radially outer platform and a radially inner wall (111) contiguous with the radially inner platform. In a region extending downstream from the circumferential array, the radially inner and outer platforms and/or the radially inner and outer walls having a non-axisymmetric surface bounding the duct. A non-axisymmetric surface may be applied to either or both of the radially outer and radially inner contiguous surfaces and may extend upstream as well as downstream of the circumferential array of outlet guide vanes.

Abstract: There is disclosed a pressure responsive valve 352 for controlling a cooling flow through an orifice 320 in a gas turbine assembly 300. The valve 352 comprises an attachment point 360, a valve element 358, and a compressible valve body 354 defining a chamber 355 for sealing a volume of compressible gas. The valve body 354 is configured to act between the attachment point 360 and the valve element 358 so that in use expansion or contraction of the valve body 354 in response to external pressure causes the valve element 358 to move relative the orifice 320. A corresponding kit, method of installation and gas turbine assembly are disclosed.

Abstract: Apparatus for determining location of at least a part of a first object, the apparatus comprising: a controller configured to: control an actuator to move an optical arrangement relative to the first object; control the optical arrangement to transmit an electromagnetic wave; receive a signal from the optical arrangement; and determine a location of an edge of the first object by determining whether a change in a parameter of the signal satisfies at least one criterion.

Abstract: An apparatus for damping machining vibrations includes a first dampener having a viscoelastic material, the first dampener to be inserted into an object defining a cavity therein; and a compressor to compress the first dampener in a first dimension to cause the first dampener to expand in a second dimension to engage an interior wall of the object.

Abstract: A gas turbine engine having a fire wall configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone. The gas turbine engine also has: (i) an actuator located in the first zone, (ii) an actuatable device that is located in the second zone, (iii) a bypass duct, (iv) an off-take device to extract cooling air from the bypass duct in the gas turbine engine and to supply the extracted cooling air into the elongate housing/shell, the off-take device having a first passage and a second passage, and (v) a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall. The mechanical force transmitting device is configured to actuate the actuatable device by transmitting a mechanical force to the actuatable device.

Abstract: A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc, the root being mounted in the slot by insertion of a leading end of the root into a proximal end of the slot and then sliding the root towards a distal end of the slot. The device includes a first wedging body having a key portion receivable in a keyway formed at the distal end of the slot. The keyway restrains the first wedging body against movement in the axial direction. The first wedging body further has a first angled surface over which a correspondingly angled leading end surface of the root slides when the root is inserted in the slot to urge the leading end of the root radially outwardly.

Abstract: A fuel injector comprises one or more elongate fuel passages (802) having an elongate axis extending from an upstream inlet end to a downstream outlet end. One or more outlets (803) are provided at the outlet end and extend obliquely with respect to the elongate axis. The elongate fuel passage is defined by an inner skin of a double skinned pipe, the double skinned pipe defining a first annular cavity (804) between the inner skin and outer skin. The inner skin and the outer skin converge adjacent the one or more outlets (803) to form a nose (808). A bridge is arranged within the fuel passage (802) and upstream of the nose (808), the bridge comprising a plurality of arms (811) extending radially from a centre (812) to a wall of the fuel passage (802), the centre (812) arranged in axial alignment with a centre of the nose (808).

Abstract: A fuel injector comprises an elongate fuel passage (38) having an elongate axis extending from an upstream inlet end to a downstream outlet end. One or more outlets (38a) at an end of the passage extend obliquely with respect to the elongate axis. The elongate fuel passage is defined by an inner skin (35a) of a double skinned pipe, the double skinned pipe defining a first annular cavity (39) between the inner skin (35a) and outer skin (35). The inner skin (35a) and the outer skin (35) meet adjacent the one or more outlets (38a) to close an end of the first annular cavity (39). A second annular cavity (40) is defined by an annular outer wall (40a) extending from downstream of the passage end to a position downstream of the one or more outlets (38a). The fuel passage outlets (38a) emerge at a radially outer surface of the annular outer wall (40a). The annular outer wall (40a) is convergent at a downstream end whereby to define an orifice (40b) centred nominally coincident with the elongate axis.

Abstract: The present invention relates to a method of forming a three-dimensional component by additive layer manufacturing. The method comprises scanning a fusing energy beam having a fusing beam focus spot across a layer of powered material in a series of fusing scan lines to fuse the powder material to form a layer of fused material whilst scanning a heating energy beam having a heating beam focus spot in a series of heating scan lines across the material fused by the fusing energy beam. The centre of the fusing beam focus spot and the centre of the heating beam focus spot are off-set from one another and spaced by up to an amount equal to the sum of the radius (y) of the heating beam focus spot and two times the radius (x) of the fusing beam focus spot.

Abstract: An assembly for receiving in a radially extending bucket groove (31) of a turbine disc (22), the assembly including a turbine blade having an elongate body (26) of aerofoil cross-section, a root portion (24) at one end of the elongate body (26) and a tip at the other. The root portion (24) configured to be retained in the bucket groove (31). A heat shield (27) configured to be received between an end of the root portion (24) and a radially inner surface of the bucket groove (31) and to interlock with the root portion (24) in a manner which deters separation in a radial direction.

Abstract: A fuel injector comprises an elongate fuel passage (31) having an elongate axis (31a) extending from an upstream inlet end to a downstream outlet end. A plurality of outlets (33) is arranged at the outlet end, each outlet extends obliquely with respect to the elongate axis (31a). The elongate fuel passage is defined by an inner skin of a double skinned pipe, the double skinned pipe defines a first annular cavity (34) between the inner skin and an outer skin. The inner skin and the outer skin meet adjacently upstream of the one or more outlets to close an end of the first annular cavity (34). The injector has a nose section (32) at a downstream end, the nose section (32) being convergent and fluted. The flutes (38) are arranged between the outlets (33) and extend towards the downstream end of the nose section (32) whereby to guide an air stream (A) passing over the injector (30) to form single jet at the downstream end of the nose section (32).

Abstract: A method of inspecting an object, the method comprising: receiving a first image of a first part of a first surface of the object from a camera arrangement; controlling relative movement between the camera arrangement and the object through a predetermined distance; receiving a second image of a second part of the first surface of the object from the camera arrangement, the second part being different to the first part; generating a third image using at least the first image and the second image; and determining a parameter associated with an abrasive surface coating on the object using the third image.

Abstract: A bladed disc for use in a turbine engine comprises: a central cob portion; a main diaphragm attached to, and extending around, the cob portion; a rim surrounding the main diaphragm; and two rows of blades attached to the rim.

Abstract: A failsafe pin for providing a backup load path for attaching a gas turbine engine to an aircraft structure is provided with a driving element that allows a torque to be provided to the pin in order to check whether the pin has been engaged, and thus whether a primary load path has failed. The pin is provided with anti-tamper arrangements in order to ensure that the pin itself is not compromised when being tested for engagement.

Abstract: A bleed flow discharge device for discharging bleed flow into a main fluid flow. The bleed flow discharge device has an outlet panel that comprises distinct first and second regions, both of which have bleed flow exit passages. The first region is at the downstream end of the bleed flow outlet panel relative to the main flow. The exit passages in the first region are closely aligned to a major axis of the outlet panel, whereas the exit passages in the second region have a component that points towards a perimeter edge of the exit panel. This arrangement results in good mixing of the bleed flow with the bypass flow, delayed attachment of the bleed flow onto the bypass duct surfaces, and low noise.

Abstract: A combustion chamber includes an upstream end wall having an aperture and a fuel injector. An air swirler is mounted such that the air swirler is movable radially with respect to the aperture. An inner wall of the air swirler has a first portion. A fuel injector head of the fuel injector is arranged coaxially within the air swirler. An outer wall of the fuel injector head has a first portion. The inner diameter of the first portion of the air swirler is less than the outer diameter of the first portion of the fuel injector head. One of the first portions is elastically radially deformable to allow the fuel injector head to be installed and removed from the air swirler. The inner wall and the outer wall have inter-engaging radially and axially extending faces to align the fuel injector head axially and radially within the air swirler.

Abstract: A computer-based method of designing a guide vane formation is provided. The vane formation is for use in a gas turbine engine which has a cascade of circumferentially arranged identical guide vane formations. The vane formation has radially inner and radially outer chordal seals. The method allows the elimination of “saw-tooth” leakage gaps between inner chordal seals of neighboring vane formations and between outer chordal seals of neighboring vane formations even when the inner and outer chordal seals are axially offset from each other.

Abstract: A combustion chamber arrangement comprises an annular combustion chamber, an outer casing, an inner casing and a stage of outlet guide vanes arranged at the downstream end of the combustion chamber interconnecting the outer casing and the inner casing. The combustion chamber comprises an upstream wall structure, a radially inner cowl is removably secured to a radially inner axially extending flange by fasteners and a radially outer wall structure and a radially outer cowl are removably secured to a radially outer axially extending flange by fasteners. The flange is slidably mounted on the radially inner wall structure. The flange has at least one recess in its radially inner surface and the fasteners are arranged in the recess in the radially inner surface of the flange. The cowl abuts the radially outer surface of the flange and the radially inner wall structure abuts the radially inner surface of the flange.