Abstract: A method of manufacturing a composite fan blade with an outer part and a core includes laying up a plurality of continuous plies to achieve a stack, placing the core on a central portion of the stack of continuous plies to achieve an unfolded preform; folding the contin-uous plies about the core, such that the central portion of the stack folds about the core and the first portion is superimposed to the second portion, to achieve a folded preform; apply-ing pressure to the folded preform to achieve a consolidated curved folded preform; curing the consolidated curved folded preform to achieve the composite fan blade.

Abstract: There is disclosed a variable vane actuation arrangement 100 comprising a unison ring 34 configured to pivot a plurality of variable vanes 26 and a drive assembly 102 for driving rotation of the unison ring 34, comprising a drive 104 and a flexible line 106 extending from a ring anchor point 110 on the unison ring 34 to the drive 104. The ring anchor point 110 is positioned such that a portion of the flexible line 106 extending towards the drive 104 wraps around the unison ring 34, whereby tension in the flexible line 106 is applied to the ring anchor point 110 in a direction tangential to the unison ring 34.

Abstract: A method of detecting defects on a surface or interface of a part is provided. The method includes: providing data from an X-ray scan of the part; processing the scan data to obtain an original 3D or 2D model of a surface or interface topology of the part; and filtering the original 3D or 2D model of the surface or interface topology to identify deviations from the expected surface or interface topology of the part. The identified deviations may be produced by surface or interface defects on the part.

Abstract: A turbine blade having a labyrinth of internal channels for circulation of coolant received through an inlet formed in a terminal portion of a blade root. A labyrinth geometry includes: (i) the inlet arranged on an axially upstream face of the terminal portion leading to an upstream duct portion having a first section adjacent the inlet and a second section having a reduced cross-section compared to the first section, (ii) a leading edge passage intersecting with the first section and extending through a blade body towards a tip of the blade, where a proximal end of the leading edge passage is angled towards a direction of incoming air flow, (iii) a main blade passage intersecting with a downstream duct portion arranged in axial alignment with, and separate from, the upstream duct portion, and (iv) a restrictor passage intersecting with a mid-blade passage and extending towards a mid-blade duct portion.

Abstract: A gear including an inner bearing part; an outer part including a plurality of teeth; an intermediate part between the inner bearing part and the outer part, the intermediate part including a plurality of support members extending radially between the inner bearing part and the outer part, the plurality of support members being distributed along a longitudinal axis of the gear.

Abstract: A combustion staging system includes a splitting unit receiving a metered fuel flow and controllably splitting the received flow into pilot and mains flows. Pilot and mains fuel manifolds distribute fuel. A cooling flow recirculation line provides a cooling flow to the mains manifold during pilot-only operation, and a return section to collect mains manifold cooling flow. The cooling flow enters a delivery section and exits the return section. A fuel recirculating control valve on the delivery section has an open position so that the cooling flow enters the delivery section during pilot-only operation; a shut off position prevents the cooling flow entering the delivery section through the cooling flow orifice during pilot and mains operation. A supplementary valve bleeds or feeds cooling flow. The mains manifold cooling flow pressure is determined by the cooling flow and pressure raising orifices flow numbers, and a control setting of the supplementary valve.

Abstract: A combustion chamber assembly includes a combustion chamber casing, a combustion chamber, a plurality of fuel injectors and respective seals. The axis of each fuel injector head is arranged at an angle to the axis of the combustion chamber casing and parallel to the center line of the combustion chamber. Each seal is positioned between a fuel injector head and an aperture in an upstream wall of the combustion chamber. Each seal has an aperture extending through the seal which is arranged parallel to the axis of the combustion chamber casing or the flange of the fuel injector. Each fuel injector head has a part spherical surface located in a seal. The assembly provides a clearance required to engage, or disengage, a fuel injector head while minimizing the amount of material removed from the between the apertures in the upstream wall of the combustion chamber.

Abstract: An axial piston pump has a rotor rotatable around an axis relative to a swashplate; one or more pistons movable within one or more respective sleeves; a fluid inlet port for the inflow of low pressure fluid, and a fluid outlet port for the outflow of high pressure fluid; and a floating element axially positioned between, on the one side, the inlet and outlet ports and, on the other side, a sealing surface of the rotor. Surfaces of the floating element defining an inlet chamber and the outlet chamber are configured such that, in use, the low pressure fluid and the high pressure fluid act on the defining surfaces to produce a net axial force which the axially slidable floating element applies to the rotor to seal the floating element to the sealing surface of the rotor.

Abstract: A method and apparatus for vibro-treating an object. The method includes the steps of controlling a relative displacement between a vibro-treating media and a surface area of the object to provide a vibro-treating effect; and, controlling movement of the object relative to a surface of the vibro-treating media while controlling relative displacement between the vibro-treating media and the surface area of the object, according to one or more pre-determined conditions, to provide a substantially even vibro-treating condition over the surface area of the object.

Abstract: Inspection apparatus for a gas turbine engine, the inspection apparatus comprising: a sensor configured to generate data; a housing having an exterior surface and configured to house the sensor therein; and one or more foam members coupled to the exterior surface of the housing, the one or more foam members being resilient to enable the inspection apparatus to be inserted into a gas turbine engine and secured between at least two surfaces of the gas turbine engine.

Abstract: The annulus is bound by an inner hub wall and an outer casing and includes a support structure, the support structure bearing the inner hub wall; at least one spigot passing through the hub wall and at least one strut arranged to pass through the spigot of the inner hub wall and across the annulus. The strut has a first end having an abutment arm extending to form an abutment shoulder. Alignable holes pass through the abutment arm and the spigot and these holes are configured to receive a cross pin which is in turn configured to fit snugly through the holes. The configuration is such that, the abutment rim and abutment shoulder are located radially inwardly of the holes and cross pin and outside of the annulus.

Abstract: A method of modelling at least a part of a gas turbine engine, the method comprising: generating a mesh for a feature using at least one data entity of a data structure, the at least one data entity defining a geometrical shape of the feature, wherein the data structure comprises: a set of data entities defining geometrical shapes of features; and modelling attributes associated with the geometrical shapes of the features; and assigning one or more modelling attributes using the modelling attributes associated with the geometrical shapes of the features.

Abstract: In an embodiment of the invention, a dual-wall casing for a combustor comprises an outer wall and an inner wall defining a channel therebetween. The walls are fastened together by a bolt which extends from the inner wall and across the channel. In use, the inner wall is exposed to combustion products. Cooling is provided by a primary inlet hole extending through the outer wall and arranged upstream (with respect to the direction of flow of coolant in the channel) of the bolt and an array of effusion holes extending through the inner wall and positioned with their inlet in line of sight of the primary inlet hole. The primary inlet hole is sized with respect to the array of effusion holes such that it has a flow area which causes locally negligible flow restriction.

Abstract: A method of manufacturing a component comprising forming an identifier internally within the component in a predetermined manner, wherein the identifier can be used to subsequently identify or authenticate the component.

Abstract: A method for diagnosing a fault condition in an electric machine includes measuring at least one physical parameter generated during operation of the electric machine; analyzing the or each measured parameter in a frequency domain; and determining whether the electric machine has a stator or rotor winding fault based on a comparison of an amplitude of the or each analyzed parameter at a first predetermined frequency and a first threshold amplitude for the first frequency. The at least one physical parameter includes a sound generated by the electric machine.

Abstract: A core (300) for an investment casting process in which a component to be cast has an internal passageway, the internal passageway being provided by the core (300), the core (300) comprising: a chimney portion (301); and a core passage (302), the chimney portion (301) extending away from the core passage (302); wherein the chimney portion (301) comprises at least one indent, groove or recess (306).

Abstract: A core for an investment casting process in which a component to be cast has an internal passageway, the internal passageway being provided by the core. A first core passage having a first point and a second point and including no straight path between the first point and the second point; a first core bridge which extends away from the first core passage between the first and second points, and has a first pillar and a second pillar which connect to the first and second points respectively, and a bridge portion which extends between the first and second pillars; wherein the first pillar has a core inlet portion having a thickness at the first point and the second pillar has a thickness at the second point, the thickness of the core inlet portion at the first point being less than the thickness of the second pillar at the second point.

Abstract: A heat exchanger for a ducted fan gas turbine engine has a low temperature side and plural high temperature sides. The heat exchanger is configured such that heat is extracted from respective engine fluids flowing through the high temperature sides and is received by a portion of a bypass airflow of the engine which, on passing through the fan duct, is diverted through the low temperature side of the heat exchanger thereby cooling the engine fluids.

Abstract: There is disclosed a self-heating tool (10) for manufacturing a composite component, comprising: a support structure (24); a mandrel (26) onto which composite material can be applied; a heater (58) for heating the mandrel (26) during a curing operation; and a plurality of extendible support members (28) extending between the support structure (24) and the mandrel (26) to support the mandrel (26). Each extendible support member (28) is configured to change in length in response to thermal expansion of the mandrel (28) during a curing operation. A method of manufacturing a composite component using a self-heating tool is also disclosed.

Abstract: A method includes forming a mold, the mold having at least one mold portion defining the shape of an element to be removed from the component in a subsequent manufacturing step and having a reduced cross-sectional area. The at least one mold portion includes at least one recess which further reduces the cross sectional area of the cavity and increases the surface area of the at least one mold portion or the at least one mold portion includes a plurality of projections which increase the surface area of the least one mold portion thereby increasing radiative heat loss from the at least one mold portion during the process. A mold for use in this method and a turbine blade formed using this method, are also provided.