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: Method for removing a front seal plate from an aircraft engine, the method comprising at least the following steps: a) separating a part engine unit from the aircraft engine, the part engine unit comprising the core engine and the low-pressure turbine of the aircraft engine, b) removing a front seal plate nut from the part engine unit, c) removing the front seal plate from the part engine unit.

Abstract: Method for removing a front seal plate (11) from an aircraft engine (1), the method comprising at least the following steps: a) separating a part engine unit (5) from the aircraft engine (1), the part engine unit (5) comprising the core engine (6) and the low-pressure turbine (7) of the aircraft engine (1), b) removing a front seal plate nut (10) from the part engine unit (5), c) removing the front seal plate (11) from the part engine unit (5).