Abstract: Methods for manufacturing outlet nozzles for use in rocket motors are disclosed. The methods include providing an inner wall, positioning an outer wall around the inner wall, positioning spacers in the space between the inner and outer walls, and laser welding between the spacers and at least one of the inner and outer walls in order to form cooling ducts between the spacers and to provide T-shaped joints between the spacers and at least one of the inner and outer walls, the T-shaped joints including a rounded shape within the cooling ducts.

Abstract: Method for manufacturing a vane (1) to a gas turbine component intended for guiding a gas flow. The vane (1) is produced by casting, and an internal hole (3) for coolant is then cut out of the cast vane (1). The vane (1) is provided with a starter hole (5), either during casting or once casting is completed, following which the internal hole (3) for coolant is cut out of the vane, proceeding from the starter hole. A method is also disclosed for manufacturing a gas turbine component including a plurality of vanes (1) for guiding a gas flow. The gas turbine component is cast in such a way that it includes the vanes and an internal hole (3) for coolant is then cut out of each of the vanes.

Abstract: A wall structure (2) and components incorporating such a wall structure that are intended to be exposed to high thermal loads. The wall structure (2) includes at least two layers; a first layer (5) and a second layer (6), the second layer (6) being located closer to a source of the thermal load than the first layer (5). The layers (5, 6) are arranged so that heat is allowed to be conducted from the second layer (6) to the first layer (5). Each of the first and second layers (5, 6) are adapted to carry a significant portion of a structural load, and the second layer (6) exhibits a higher thermal conductivity and/or a lower thermal expansion than the first layer (5) which reduces thermal strain in the wall structure (2).

Abstract: Method and arrangement for providing a gas turbine (1) having a first compressor (2), a combustion chamber (16) and a first turbine (11), the turbine being adapted to drive the compressor via a first shaft (10a, 10b). The gas turbine also has a bleed valve (12) arranged upstream of the first turbine for conducting part of a gas compressed by the compressor past it during engine braking. The invention also relates to a method for engine-braking a gas turbine.

Abstract: Method for manufacturing a hollow blade configured to function as a stator or rotor component and having at least one support element positioned between two opposite blade walls, and joined together by welding. The support element is joined together with at least one of the blade walls by means of laser-welding from the outside of the blade in such a way that the joined-together portions of the support element and the blade wall form a T-shaped joint.

Abstract: Method and device (2) for monitoring a welding area of an object (14) in connection with welding, which device includes arrangements (3) for reproduction of the welding area, at least one filter (4) arranged in front of or in the reproduction arrangement (3), and an illumination arrangement (5) of the welding area with ultraviolet radiation. The filter (4) consists of a band-pass filter which is adapted for filtering around a wavelength within the ultraviolet wavelength range.

Abstract: A method and device for inhibiting contamination of a workpiece during the heating of a workpiece by a contaminant. The method includes placing the workpiece in a first container, and, in a first step, filling the first container with a protective gas. The first container is placed in a second container, and in a second step, the second container, and hence the first container contained therein, is evacuated to create a vacuum inside the first and second containers so that during the first and second steps the partial pressure is reduced for the contaminants in the first container before the workpiece is heated.

Abstract: Method for manufacturing a stator component or rotor component (10) including at least one ring element (3). A joining material is provided in contact with at least one of the blade (2) and the ring element (3). The blade and the ring element are arranged in relation to one another in such a way that they are joined together via a butt joint when heated, and when such heat-treatment is subsequently carried out, the joining material forms a melt that joins the parts together upon solidification.

Abstract: A gas turbine arrangement (1) including a gas turbine (2), a generator (3) and a gearbox (4). The gearbox (4) is connected to an output shaft (5) from the gas turbine and an input shaft (6) to the generator. The gas turbine arrangement (1) also has a starter motor (7) that is connected to an output shaft (8) from the generator (3).

Abstract: A tool for the fine-turning of grooves in workpieces including a basic body having a rearwardly extending mounting part, and a forwardly projecting bracket. The bracket includes a narrow neck part and an enlarged support part disposed at an end of the neck part. The support part, which forms an insert seat, extends laterally from the neck part wherein the seat is arranged asymmetrically with respect to an imaginary center line of the basic body. A cutting insert includes a bottom side supported on the insert seat. The insert includes two spaced apart convexly arched side cutting edges arranged so that the imaginary center line passes therebetween. A hole is provided through the insert for receiving a fastening screw. The bottom side and the insert seat include mutually engaging stabilizing structures preventing angular displacement of the insert about an axis of the hole.

Abstract: A wall structure capable of withstanding high thermal load, including a wall structure with an inner wall, an outer wall positioned about the inner wall, and distancing elements located between the inner and outer walls. The distancing elements are joined to at least one of the inner and outer walls by means of laser welding and thereby establishing a plurality of cooling ducts between the inner and outer walls and a weld joint formed by the laser welding and having a cross-section taken through the wall structure that is substantially T-shaped and which displays a rounded shape towards an inside one of the plurality of cooling ducts.

Abstract: Method and arrangement for providing a liquid fuel rocket engine member (10). The member has a load bearing wall structure (14) having a plurality of cooling channels (11). For improving the heat transfer, a material with a higher thermal conductivity than the load bearing wall structure (14) is applied to the wall structure.

Abstract: Method and arrangement for manufacturing a disk-shaped or annular stator component or rotor component with a plurality of blades arranged one after another in a path extending around the component and a cover (15) arranged outside the blades in the radial direction and in contact therewith. According to the method, at least a portion (11) of a first set of channels (12) is spark-eroded simultaneously out of a disk-shaped or annular workpiece (2) intended for forming the component at a distance from the edge (14) of the workpiece in the radial direction, which channels (12) are intended to delimit the blades in the circumferential direction of the workpiece.

Abstract: Method and arrangement for manufacturing an outlet nozzle (10) for use in a liquid fuel rocket engine. The nozzle forms a body of revolution having an axis of revolution and a cross section that varies in diameter along said axis. The nozzle has a wall structure comprising a plurality of mutually adjacent cooling channels extending substantially in parallel from the inlet end (12) of the nozzle to its outlet end (13). The method includes providing a plurality of preprocessed profile members, each having a web and flanges in opposite directions from said web. Each profile member is machined to present a longitudinally gradually tapering width. The member is curved to conform with the wall section of the nozzle, and members are joined by welding the flanges to form a bell-shaped nozzle structure with cooling channels (11) formed by adjacent webs and adjacent pairs of flanges.

Abstract: Method of tying two or more components together using a fastener. Each component is provided with a hole and the components are placed so that the holes overlap one another in order to receive the fastener in the holes. The fastener is placed in the holes and mechanically pressure-loaded and heated in order to deform the fastener to tie the components together. The fastener is heated essentially only during the fastener deformation phase in order to minimize the heat transfer from the fastener to the components being tied.

Abstract: A method for manufacturing a stator or rotor component (8) for a gas turbine in which at least one wall element (3) is joined together with at least one ring element (9). The edges of the wall element (3) are laser-welded firmly on the ring element (9) from an opposite side, in the radial direction, of the ring element in relation to the wall element in such a way that the joined-together portions of the wall element and the ring element form a T-shaped joint.

Abstract: Method and arrangement for providing liquid fuel rocket engine member (10). The member forms a body of revolution having an axis of revolution and a cross section that varies in diameter along said axis. The wall structure includes a plurality of cooling channels (11). The outside of the wall structure includes a continuous sheet metal wall (14). The cooling channels (11) are longitudinally attached to the inside of the sheet metal wall. The method for manufacturing the rocket engine member (10) includes the steps of forming a sheet metal wall (14) having a wall section corresponding to the desired nozzle section, providing a plurality of channel members (15), and attaching the channel members (15) to the inside of the sheet metal wall (14).

Abstract: Thermal spraying method and device that includes a means (1,2) for generating a flame and a means (3) for injecting a powder into the flame. The flame-generating means (1,2) includes an end piece (1) out of which the flame is directed towards a substrate subjected to spraying. The powder-injection means (3) includes a frame element (6) that is adapted to be attached to the end piece (1) and to project in the flame ejection direction from the end piece (1).

Abstract: A fuel injector (1) having a chamber (7) with a fuel inlet (8) and a plurality of fuel outlets (10), and including a fuel distributor (18) that is arranged in the chamber (7) for the purpose of distributing fuel introduced into the chamber (7) via the fuel inlet (8) to the outlets (10). The fuel distributor (18) includes a generally rotary symmetric distributor body (19).

Abstract: Method and arrangement for providing a ceramic thermal barrier coating, TBC, deposited and attached directly to a metallic substrate (2), or an intermediate bond coating (3) deposited on such a substrate (2). The TBC includes at least two layers, wherein a first, inner TBC layer, that is directly attached to the substrate (2) or bond coating (3), presents a different microstructure than a second, outer TBC layer.