Abstract: A device of a turbomachine for separating oil from an air-oil volume flow, with a first separation appliance and a second separation appliance, wherein an air-oil volume flow from an oil-loaded area of the turbomachine can be supplied to the first separation appliance, and wherein the air-oil volume flow, the oil loading of which can be reduced in the area of the first separation appliance, can be supplied to the second separation appliance downstream of the first separation appliance by means of a conduit. An appliance for cooling the air-oil volume flow conducted inside the conduit is provided, being arranged downstream of the first separation appliance and upstream of the second separation appliance.

Abstract: A method for manufacturing a metallic component especially configured and designed for a turbomachine includes a) for a precision-casting process, a wax model with a wax structure is produced, subsequently b) the tip of the wax structure is thermally and/or mechanically treated such that a region with an undercut is formed on the wax structure, subsequently c) the metallic component is manufactured from the wax model in the precision-casting process, with a component structural element with an undercut forming on a surface of the component, and d) the component structural element is provided at least partially with a ceramic coating, a plastic-containing coating, in particular a fiber composite layer and/or a plastic component.

Abstract: A method of inspecting a component in an assembled gas turbine engine includes inserting a boroscope and a conduit through an aperture in a casing of the engine. The conduit has an applicator tip. The boroscope and conduit are directed to the component to be inspected. A dye penetrant is supplied through the conduit to the applicator tip. The applicator tip is arranged to contact the surface of the component and dye penetrant is supplied onto the surface of the component from the applicator tip such that the dye penetrant enters any defects in the surface of the component. The applicator tip includes a porous and malleable member. Light is directed onto the component and the surface of the component is viewed through the boroscope to determine if any defects are present in the surface of the component.

Abstract: In a method for beam welding on components with a laser beam or electron beam generated by a beam source, the heat treatment of the welded component required to remove stresses is integrated into the welding process. In a work cycle combined with the welding process, a regulated heat supply to a selected region takes place, according to its residual heat resulting from the welding process and the predicted stresses in that region, using the residual heat remaining from the welding process following the welding process from the same or other beam source(s). The welding region is cooled in a controlled manner, so that welded components which are likely to be subject to high stress in use, provided for example for a aircraft engine, can be made available without inherent stresses and with the desired microstructure in a single—combined—work step.

Abstract: A nacelle for a propeller gas turbine engine, the nacelle comprising a forebody upstream of the propellers and an afterbody downstream of the forebody. The forebody comprises a first, upstream region and a second, downstream region. The first region has a convex profile and the second region has a concave profile to cause diffusion of the airflow into the propellers.