Abstract: A method of manufacturing a wall structure includes producing at least one elongated web in a workpiece by feeding a machining tool along the workpiece, wherein the machining tool simultaneously machines a first side surface of the web, a second side surface of the web and a top surface of the web.

Abstract: Method and arrangement for providing a stator component intended during operation to conduct a gas flow. The component is made up of at least two sections (113) in its circumferential direction, which sections each have at least one wall part (101, 102). The sections are placed adjacent to each other and two wall parts, one from each of two adjacent sections, are connected in order together to form a means, extending in the radial direction of the component, for guidance of the gas flow and/or transmission of load during operation of the component.

Abstract: Method for manufacturing a stator component that is intended during operation to conduct a gas flow. The component is made up of at least two sections (113) in its circumferential direction, which sections each have at least one wall part (101,102) The sections are placed adjacent to each other and two wall parts, one from each of two adjacent sections, are connected in order together to form a means, extending in the radial direction of the component, for guidance of said gas flow and/or transmission of load during operation of the component.

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: 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: Method and arrangement for providing a stator component intended during operation to conduct a gas flow. The component is made up of at least two sections (113) in its circumferential direction, which sections each have at least one wall part (101, 102). The sections are placed adjacent to each other and two wall parts, one from each of two adjacent sections, are connected in order together to form a means, extending in the radial direction of the component, for guidance of the gas flow and/or transmission of load during operation of the component.

Abstract: A method for producing rotational-symmetrical sheet metal articles with double-curved shape and varying thickness, particularly rocket nozzles, in which a number of sheet metal part-blanks in flat condition are cut to partially circular ring-like shape, whereupon said part-blanks are bent to the desired curvature and welded together to form a blank of the article for final machining.