Abstract: A system for welding a first component to a second component. The system includes a first laser head configured to emit a first laser beam and be movably disposable on a first side of the first component. The system further includes a second laser head configured to emit a second laser beam and be movably disposable on an opposing second side of the first component. The system further includes a controller configured to independently control a first power of the first laser beam and a second power of the second laser beam. The controller is also configured to independently and simultaneously control movement of the first laser head and movement of the second laser head relative to the first component.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub with a through hole extending therethrough. The method comprises welding the aerofoil to the stub such that the open end of the hollow cavity of the aerofoil is aligned with the through hole of the stub so as to define a hollow region extending through the support member and stub to the cavity of the aerofoil. During welding a tool is positioned within the through hole and cavity and is aligned with an interface between the stub and aerofoil, the tool being configured to prevent weld splatter onto a surface of the cavity or through hole.

Abstract: There is described a method of forming a cooling hole in a component having a wall comprising a first surface and a second surface, the method comprising: directing a first laser beam onto the first surface of the component wall at an oblique angle so as to drill a first hole extending from the first surface towards the second surface; directing a second laser beam onto the second surface of the component wall at an oblique angle so as to drill a second hole extending from the second surface towards the first surface, the first and second holes intersecting to form a cooling hole passing through the component wall between the first and second surfaces.

Abstract: An energy source for an additive manufacturing arrangement comprises a workpiece and a powder delivery device. The energy source is characterised in that it comprises a plurality of discrete energy sources. The plurality of discrete energy sources may be coordinated in use to deliver energy simultaneously to a plurality of regions of the workpiece in a matrix form.

Abstract: A method of laser processing a component within an assembled apparatus using a boroscope, which includes a working head having first and second ends. A first optical fiber extends through the boroscope to a position between the first and second ends. A second optical fiber extends through the boroscope to the second end. A laser optical fiber extends through the boroscope. At least one lens is arranged between the first and second ends of the working head and a mirror is gimballed to the second end. The laser optical fiber directs laser light transmitted through the laser optical fiber onto the lens and then onto the mirror. A first LED is arranged at a position between the first and second ends of the working head and a second LED is arranged at the second end and an actuator device adjust the position of the mirror.

Abstract: A method of welding a first component and a second component together, the method comprising: controlling movement of a first component and/or a second component to form a joint, the first component and the second component defining a first side and a second side; controlling welding of the first component and the second component on the second side using filler to form a seal weld to seal the joint; controlling provision of a vacuum chamber to enclose the joint within a volume; controlling evacuation of the volume defined by the vacuum chamber; and controlling power beam welding of the joint, the power beam being provided from the first side and through the evacuated volume.

Abstract: Method of determining an oxygen level inside a gas shield: providing a surface; positioning a gas shield over a portion of the surface; applying a pressure sensitive paint to the portion of the surface; flowing oxygen through the gas shield onto the portion of the surface; illuminating the portion of the surface; measuring a first fluorescent emission from the portion of the surface while oxygen is flowing through the gas shield; determining an oxygen saturation level across the portion of the surface in dependence on the magnitude of the first fluorescent emission; flowing a shield gas through the gas shield; illuminating the portion of the surface; measuring a second fluorescent emission from the portion of the surface while the shield gas is flowing through the gas shield; and determining an oxygen level across the portion of the surface in dependence on the relative magnitudes of first and second fluorescent emission.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub with a through hole extending therethrough. The method comprises welding the aerofoil to the stub such that the open end of the hollow cavity of the aerofoil is aligned with the through hole of the stub so as to define a hollow region extending through the support member and stub to the cavity of the aerofoil. During welding a tool is positioned within the through hole and cavity and is aligned with an interface between the stub and aerofoil, the tool being configured to prevent weld splatter onto a surface of the cavity or through hole.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body. This ensures that the outer surface of the capping panel is located as accurately as possible. This means that the capping panel can be made to be as thin as possible, which in turn reduces weight and material wastage. Once the capping panel has been located in position, it may be welded to the aerofoil body in order to produce the hollow aerofoil component.

Abstract: A method of laser processing a component within an assembled apparatus using a boroscope, which includes a working head having first and second ends. A first optical fibre extends through the boroscope to a position between the first and second ends. A second optical fibre extends through the boroscope to the second end. A laser optical fibre extends through the boroscope. At least one lens is arranged between the first and second ends of the working head and a mirror is gimballed to the second end. The laser optical fibre directs laser light transmitted through the laser optical fibre onto the lens and then onto the mirror. A first LED is arranged at a position between the first and second ends of the working head and a second LED is arranged at the second end and an actuator device adjust the position of the mirror.

Abstract: A boroscope includes a working head having first and second ends. A first optical fiber extends through the boroscope to a position between the first and second ends. A second optical fiber extends through the boroscope to the second end of the working head. A laser optical fiber extends through the boroscope. At least one lens is arranged between the first end and the second end of the working head and a mirror is gimballed to the second end of the working head. The laser optical fiber directs laser light transmitted through the laser optical fiber onto the lens and then onto the mirror. A first LED is arranged at a position between the first end and the second end of the working head and a second LED is arranged at the second end of the working head and an actuator devices adjust the position of the mirror.

Abstract: An apparatus and method for performing an ALM process is described. A first energy beam source (1) provides an energy beam (1b) which selectively melts a substrate powder (3) into a melt pool. A second energy beam source (2) provides an energy beam (2b) to heat condition substrate powder proximate to the melt pool. The path of the second energy beam (2b) is controlled by a controller (6) to oscillate independently of the path followed by the first energy beam (1b). The method may be applied to control and optimise heating and cooling rates of the sintered substrate during the ALM process enabling its microstructure to be controlled to suit the end use of the product and reduce the occurrence of residual stresses and consequent crack propagation.

Abstract: A pressure vessel having a diameter greater than or equal to 1 m and made by laser cladding an inner surface of the vessel, the laser cladding following a helical path.

Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body. This ensures that the outer surface of the capping panel is located as accurately as possible. This means that the capping panel can be made to be as thin as possible, which in turn reduces weight and material wastage. Once the capping panel has been located in position, it may be welded to the aerofoil body in order to produce the hollow aerofoil component.

Abstract: A method of cleaning a surface includes the steps of directing a laser beam to the surface at a predetermined location and capturing for the predetermined location a) data relating to an acoustic response induced by interaction of the laser with the surface, b) data relating to the optical reflectivity of the surface at the predetermined location, and c) data relating to the spectrographic response of a plume generated by interaction of the laser with the surface.

Abstract: A boroscope includes a working head having first and second ends. A first optical fibre extends through the boroscope to a position between the first and second ends. A second optical fibre extends through the boroscope to the second end of the working head. A laser optical fibre extends through the boroscope. At least one lens is arranged between the first end and the second end of the working head and a mirror is gimballed to the second end of the working head. The laser optical fibre directs laser light transmitted through the laser optical fibre onto the lens and then onto the mirror. A first LED is arranged at a position between the first end and the second end of the working head and a second LED is arranged at the second end of the working head and an actuator devices adjust the position of the mirror.

Abstract: Apparatus for manufacturing a component and a method of manufacturing a component. The method comprises the steps of directing a beam of energy to heat a working region of a substrate and adjusting the cross sectional shape of the beam to thereby generate a variety of predetermined cross sectional shapes of working region while the beam is being directed onto the substrate. Thus the distribution of energy delivered to the substrate is controlled during the manufacturing process. The cross sectional shape and area of the beam is repeatedly monitored and compared to a library of predetermined cross sectional shape(s) and area(s).

Abstract: A system for laser processing a work piece surface with a laser processing beam includes a processing beam delivery source (205) optics (210, 230) for focusing the processing beam at a surface of the work piece, a viewing camera (250) configured coaxially and coincidently focused with the processing beam (207) at beam impinge point (245) on the work piece (100). The system further includes a computer (510) and processor (512) for displaying an image of the work piece (100) and a cursor (600) superimposed thereon on a monitor (560). One or more movable mirrors (320, 325) are provided movably mounted on galvanometers (335, 340) controlled by the processor (512) to direct the processing beam to selected points on the work surface for processing, (e.g. by laser spot welding). The system further includes an input device such as a mouse (520) for positioning a movable cursor (600) on image points of the work piece image and for selecting the image point for laser processing.