Abstract: A thermal spraying method and device that includes a device (1,2) which generates a flame and a device (3) which injects a powder into the flame. The flame-generating device (1,2) includes an end piece (1) out of which the flame is directed towards a substrate subjected to spraying. The powder-injection device (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). The frame element (6) has a plurality of through-holes (9) extending through it and distributed circumferentially about the frame element (6) as well as at least two powder injection ports distributed about the frame element (6).

Abstract: The present invention relates to a support structure and a method for assembling a support structure in a turbine or compressor engine for rotatably supporting a rotor member in a stator member. The support structure includes an inner ring, an outer ring and a plurality of struts which extend radially between the inner ring and the outer ring. The inner ring has integrated portions projecting in the direction of the struts and forming end connections for the struts. The integrated end connecting portions of the inner ring are together with the ring made by a metal alloy having initially oversized cross sectional dimensions relative to the cross sectional dimensions of corresponding strut, followed by working at least one lateral surface for removing material. The purpose is to achieve final dimensions and position to conform to the cross sectional dimensions and correct position of each corresponding strut.

Abstract: In an annular torsional rigid static component for an aircraft engine, the component includes at least one arrangement for mounting the engine to an aircraft. The mounting arrangement comprises a body formed in a composite material.

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: A static gas turbine component includes an inner and an outer annular support member and a plurality of circumferentially spaced radial struts arranged between the support members for transmitting structural loads. Each of a plurality of the struts includes a load carrying core rigidly fixed to both the inner and the outer support member forming a unitary carcass with the support members, an impact resistant shell surrounding the core, and an energy absorbing material arranged between the core and the shell.

Abstract: An afterburner fuel-feed arrangement including an elongate fuel spraybar for distributing fuel to the afterburner section of a turbo-combustion engine. The spraybar includes a fuel-receiving spray head in fluid communication with a plurality of elongate fuel pipes, which are surrounded by an elongate, aerodynamic-shaped shroud. The surrounded fuel pipes project into an interior through-core of the engine. The shroud has an interior lateral sidewall that includes a pipe-receiving portion configured to abuttingly engage a corresponding shroud-engaging portion of an exterior surface of one of the fuel pipes. The pipe-receiving portion is configured to substantially radially fix a fuel pipe received therein relative to the shroud, thus supporting and bracing the pipe and raising the eigenfrequencies of the assembly into ranges higher than those of the incorporating engine.

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 turbine or compressor device having a rotor (1), that includes a first rotor section (2) having at least one disc-shaped or annular element (3) which has a multiplicity of blades (4) arranged in series on a circumferential path for guiding a gas flow, and a second, elongate rotor section (5) which projects at right-angles from the rotor disc (3) and which has a rotor shaft (6) connected to the rotor disc. A first and second bearing (8, 9) are fitted at a distance from one another along the rotor shaft (6), and the first bearing (8) is arranged closer to the rotor disc (3) than the second bearing (9). The bearing holder (25) of the first bearing (8) has a greater outside width than other than other components (9, 14, 15, 31) arranged on the rotor shaft (6) between the first bearing (8) and the free end of the rotor shaft (7).

Abstract: An engine wall structure includes an inner wall to which hot gas is admitted during engine operation, an outer wall, which is colder than the inner wall during engine operation, and at least two webs that connect the inner wall with the outer wall and delimit a cooling duct between the walls. The webs are mainly formed by a first material and the inner wall is mainly formed by a second material of other composition and other heat conductivity than the first material.

Abstract: In a method for controlling a tool during machining a work piece using the tool, a first measuring arrangement which has a first ultrasonic probe for emitting ultrasonic waves is used, the first measuring arrangement being arranged ahead of the tool with respect to the relative tool movement direction and being moved relative to the work piece in the relative tool movement direction. The ultrasonic waves emitted by the first ultrasonic probe are transmitted to the work piece, and are transmitted back to the first ultrasonic probe, by a first column of liquid which is created by the first measuring arrangement and situated between the first ultrasonic probe and the work piece for measurement. The measurements are used for automatically adjusting the position of the tool relative to the work piece during machining the work piece.

Abstract: A cooling system for an aircraft includes a cooling circuit for transporting a coolant, with the cooling circuit running to a component in the aircraft that is heated up during flying in order to take up heat from the heated-up component via the coolant. The cooling circuit runs to a jet engine for propulsion of the aircraft in order to release heat to a flow of gas in the jet engine via the coolant.

Abstract: The invention relates to an arrangement for propelling an aircraft comprising a jet engine and an outlet nozzle arranged downstream of the jet engine. The jet engine is of a type which generates an internal core flow and an external fan flow. A part of the outlet nozzle has an internal surface which defines a gas duct for the fan flow. The aforementioned part of the outlet nozzle includes a wall structure that is arranged at a distance from the internal surface such that it separates the gas duct for the fan flow from an internal gas duct for the core flow.

Abstract: A method is provided for producing an engine wall structure that includes an inner wall, to which hot gas is admitted during engine operation, an outer wall, which is colder than the inner wall during engine operation, and at least two webs that connect the inner wall with the outer wall and delimit a cooling duct between the walls. The engine wall structure is produced by wire-electro discharge machining the duct out of a solid sheet forming the entire engine wall structure including the inner wall, the outer wall and the webs.

Abstract: A stator for installation in a rear section of a jet engine includes a plurality of guide vanes which extend in the radial direction of the stator and between them define ducts for leading a gas. A first side of the stator in its axial direction defines an inlet for the gas and a second side, opposite the first side, defines an outlet for the gas. The guide vanes have such a shape that together they at least substantially cover the gas inlet viewed in the axial direction of the stator from the outlet side thereof.

Abstract: In a method for training a person while operating a vehicle, the vehicle has a control system for receiving vehicle operating commands from the person for controlling the vehicle. A calculation unit is provided for simulating a state of the vehicle and/or the environment to which the vehicle is subjected, the simulated state being a possible real state of the vehicle and/or the environment which is different from the actual state of the vehicle and/or the environment. The vehicle operating commands and the calculation unit are used for calculating vehicle command signals. The vehicle command signals are used for controlling the vehicle so as to cause the vehicle to respond to the vehicle operating commands in a way that corresponds to the state simulated by the calculation unit instead of the actual state of the vehicle and/or the environment.

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: In a method for measuring the size or shape of an edge of a machined work piece or of a cutting edge of a tool, the surface of the edge is illuminated by diffused radiation from several positions in the vicinity to the edge by an illumination arrangement, and a picture of the edge is reproduced by recording reflected radiation from the illuminated edge by means of a picture reproduction unit.

Abstract: Method and arrangement for providing and controlling a gas turbine (1) at least one turbine (11, 20, 20?), at least one compressor (2, 5) driven by the turbine and a combustion chamber (16) arranged between the compressor and the turbine in the airflow path. The gas turbine includes devices (8) for direct measurement of the air mass flow at a position upstream of the combustion chamber in the airflow path, with the aim of regulating the quantity of fuel that is delivered to the combustion chamber (16) on the basis of the measured air mass flow.

Abstract: Method and arrangement for providing a turbine or compressor device having a rotor (1), that includes a first rotor section (2) having at least one disc-shaped or annular element (3) which has a multiplicity of blades (4) arranged in series on a circumferential path for guiding a gas flow, and a second, elongate rotor section (5) which projects at right-angles from the rotor disc (3) and which has a rotor shaft (6) connected to the rotor disc. A first and second bearing (8, 9) are fitted at a distance from one another along the rotor shaft (6), and the first bearing (8) is arranged closer to the rotor disc (3) than the second bearing (9). The bearing holder (25) of the first bearing (8) has a greater outside width than other than other components (9, 14, 15, 31) arranged on the rotor shaft (6) between the first bearing (8) and the free end of the rotor shaft (7).

Abstract: The invention relates to a method for manufacturing a stator component that is intended in operation to guide a gas flow and to transfer loads. The component is constructed of at least two sectors in the direction of its circumference. The sectors are cast in separate pieces, positioned adjacent to each other and joined together by welding.