Abstract: A device enables borescope inspection of turbine blades of a high-pressure turbine stage of a jet engine. The device has a bend-free guide pipe for introducing a flexible borescope. The device also has: a guide for the guide pipe, the guide being configured to provide clear and reproducible positioning and orientation of the guide pipe; and a securing device configured to releasably secure the guide to an outer side of the jet engine. The securing device is configured to adjust the guide to a predetermined orientation with respect to the outer side of the jet engine. The guide pipe is rigid and shaped in such a manner that an end of the guide pipe that is introduced into the jet engine when the guide is orientated correctly is orientable so as to be directed between two predetermined guide blades.

Abstract: A tool holds and axially fixes a high-pressure shaft of an aircraft engine in a state where a high-pressure turbine stage is demounted. The tool includes: a shaft end cap having an inner radius, which is adapted to a predetermined shaft diameter, the shaft end cap plugs onto a turbine-side end of the high-pressure shaft; a shaft end cap receptacle receives the shaft end cap in a radially movable manner and in an axially limited manner in a first direction; a connector is fastenable to the shaft end cap receptacle and has a shank, which is insertable into the high-pressure shaft, the connector being configured to axially secure the shaft end cap receptacle; and a spring element, which is positionally fixed with respect to the shaft end cap receptacle, the spring element being configured to apply a predetermined spring force to the shaft end cap in the radial direction.

Abstract: A tool holds and axially fixes a high-pressure shaft of an aircraft engine in a state where a high-pressure turbine stage is demounted. The tool includes: a shaft end cap having an inner radius, which is adapted to a predetermined shaft diameter, the shaft end cap plugs onto a turbine-side end of the high-pressure shaft; a shaft end cap receptacle receives the shaft end cap in a radially movable manner and in an axially limited manner in a first direction; a connector is fastenable to the shaft end cap receptacle and has a shank, which is insertable into the high-pressure shaft, the connector being configured to axially secure the shaft end cap receptacle; and a spring element, which is positionally fixed with respect to the shaft end cap receptacle, the spring element being configured to apply a predetermined spring force to the shaft end cap in the radial direction.

Abstract: A device enables borescope inspection of turbine blades of a high-pressure turbine stage of a jet engine. The device has a bend-free guide pipe for introducing a flexible borescope. The device also has: a guide for the guide pipe, the guide being configured to provide clear and reproducible positioning and orientation of the guide pipe; and a securing device configured to releasably secure the guide to an outer side of the jet engine. The securing device is configured to adjust the guide to a predetermined orientation with respect to the outer side of the jet engine. The guide pipe is rigid and shaped in such a manner that an end of the guide pipe that is introduced into the jet engine when the guide is orientated correctly is orientable so as to be directed between two predetermined guide blades.

Abstract: A device cleans turbine blades of a turbine stage of a jet engine. The device includes a cleaning lance. The cleaning lance is configured to be introduced into the jet engine through a through-opening. The cleaning lance has an outlet opening at one end thereof and a supply connection for supplying cleaning media at an other end thereof. The cleaning lance includes a guide configured to guide the cleaning lance for clear and reproducible positioning and orientation of the cleaning lance; and a securing device configured to releasably secure the guide to an outer side of the jet engine. The securing device is configured to adjustably orient the guide to a predetermined orientation with respect to the outer side of the jet engine.

Abstract: A force introduction fitting for lightweight components comprises two radial force introduction faces, at least one axial force introduction face and at least one receiving means for mounting and force introduction of the force introduction fitting. The radial force introduction face and the axial force introduction face enclose a cavity. The radial force introduction face and the axial force introduction face form a one-piece component. A wall is located between the radial force introduction faces and the axial force introduction face, and extends non-parallel to the axial force introduction face, at least in portions, and comprises a bearing face for fitting a retaining face of an anchor part. A force introduction fitting of this type can be produced by using a selective laser melting method. The force introduction fitting can thus be adapted flexibly to loading conditions and has advantageous material properties and a low weight.

Abstract: A force introduction fitting for lightweight components comprises two radial force introduction faces, at least one axial force introduction face and at least one receiving means for mounting and force introduction of the force introduction fitting. The radial force introduction face and the axial force introduction face enclose a cavity. The radial force introduction face and the axial force introduction face form a one-piece component. The receiving means is formed as a wall between the radial force introduction faces and the axial force introduction face, extends non-parallel to the axial force introduction face, at least in portions, and comprises a bearing face for fitting a retaining face of an anchor part. A force introduction fitting of this type can be produced by using a selective laser melting method. The force introduction fitting can thus be adapted flexibly to loading conditions and has advantageous material properties and a low weight.