Abstract: A supplementary function module is for vehicles for the supplementation of a function module supplied with electrical power via a power supply bus. The supplementary function module is configured to be supplied with electrical power via the power supply bus. The supplementary function module has a controller configured to detect a voltage in the power supply bus, and to deactivate the supplementary function module based upon a first predefined voltage variation being detected.

Abstract: A borescope is for optically inspecting gas turbines of aircraft engines. The borescope having an electronic image capture unit as a borescope objective at an end of a shaft, which is suitable for insertion into a borescope opening and configured for accurate positioning of the borescope objective relative to the borescope opening and through which data lines and supply lines for the image capture unit are guided. The image capture unit has: two spaced apart image capture sensors, recording cones of which overlap in a specified recording plane forming a recording region, in such a way that image data of the two image capture sensors are configured to be processed into 3-D data by way of triangulation.

Abstract: An escape path marking for an aircraft includes a lighting element, which luminesces in a dark environment, and which emits an emitted light which exits at an outer side of the escape path marking. A transparent protective element is arranged between the lighting element and the outer side of the escape path marking. A planar grid element, which comprises regularly alternating pure-color transparent and opaque regions, is arranged between the lighting element and the outer side of the escape path marking. A transparent pigmented element is formed and arranged between lighting element and the outer side of the escape path marking such that in an event of external illumination according to at least one predefined illumination scenario, a predefined first color tone results on the outer side of the escape path marking at the transparent regions of the grid element.

Abstract: A device drives a shaft of a jet engine for inspection purposes. The device has: a drive having a part co-rotating with the shaft. The co-rotating part of the unit is configured to lie against a spinner of the shaft and is secured in a non-rotatable manner to at least one fan blade arranged on the shaft using at least one strap.

Abstract: A method applies a titanium aluminide alloy on a substrate. The titanium aluminide alloy has a gamma phase proportion of at least 50% based on an overall composition of the titanium aluminide. The method includes: pretreating a surface of the substrate; heat treating titanium aluminide powder particles at a temperature range of 600° C. to 1000° C. to increase the proportion of the gamma phase; cold spraying the heat-treated powder particles onto the substrate or a part of the substrate to form a layer of titanium aluminide; and thermally post-treating the layer of titanium aluminide applied to the substrate.

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 borescope includes an electronic image capture unit having two image capture sensors as a borescope lens at an end of a shaft that is designed for being inserted into a borescope opening, a position and alignment of the image capture sensors in relation to one another being suitable for ascertaining three-dimension (3D) information using triangulation; and a pattern projector configured to project a pattern into a common recording region of the image capture sensors. The pattern projector includes: a fundamentally optically imaging light-guide bundle, which is made up of statistically distributed optical fibers having differing transmittances, to whose input surface a light source is coupled and whose output surface is aligned with the region captured by the image capture sensors.

Abstract: A device cleans a core engine of a jet engine. The device has: a nozzle installation which is configured for introducing a cleaning medium into the core engine; a connector configured to connect the device in a rotationally fixed manner to a shaft of a fan of the jet engine; and a line connection configured to supply the cleaning medium, which is connected to the nozzle installation by a rotary coupling. The nozzle installation comprises nozzles, comprising at least one flat jet nozzle, and at least one full cone nozzle or hollow cone nozzle.

Abstract: A device cleans a core engine of a jet engine. The device has: a nozzle installation configured to introduce a cleaning medium into the core engine; a connector configured to connect the device in a rotationally fixed manner to a shaft of a fan of the jet engine; and a line connection configured to supply the cleaning medium, the line connection being connected to the nozzle installation by a rotary coupling. The nozzle installation has first contact faces configured to bear axially on fan blades of the fan, the first contact faces being configured for defined positioning of the nozzle installation relative to the jet engine.

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 plug-in connection box for vehicles has a socket and a return apparatus. The socket, is accessible from an access side and has an insertion direction. The socket is arranged in a pivot body, which is mounted in a movable manner in relation to a receptacle in such a way that the insertion direction of the socket is pivotable at an angle in all directions starting from a stationary state of the pivot body. The return apparatus is configured to return the pivot body to the stationary state.

Abstract: An attachment housing is for fastening to an exterior side of an aircraft. The attachment housing has a functional compartment. The functional compartment is divided in two, and has a ventilation compartment and a protective compartment. A surrounding wall is configured to separate the ventilation compartment from an environment. The surrounding wall has at least one ventilation opening for air exchange between the ventilation compartment and the environment. A dividing wall is arranged between the ventilation compartment and the protective compartment. The dividing wall has at least one passage opening for air exchange between the ventilation compartment and the protective compartment. The passage opening is configured to counter act a penetration of water, moisture, or particles into the protective compartment.

Abstract: A functional enhancement module is for vehicles and for enhancing a functional module which is supplied with electric power via a power supply bus. The functional enhancement module is configured to be supplied with the electric power via the power supply bus. The functional enhancement module includes: a controller having a power specification for a maximum power flow of the functional module and being configured to detect a current power flow at a reference point; and a power controller configured to control a power take-up of the functional enhancement module. The controller is configured to control the power controller in accordance with the detected power flow, such that a combined power take-up of the functional module and the functional enhancement module does not exceed the power specification.

Abstract: A method cleans surfaces in an internal volume of an aircraft component through which a medium flows. The method includes: connecting the internal volume to be cleaned to a steam generator; generating a cleaning steam having a predetermined vapour pressure and temperature by the steam generator; applying the cleaning steam to the surfaces to be cleaned in the internal volume; maintaining the vapour pressure and the temperature within the internal volume for the duration of a predetermined condensation time; generating a pressure drop in the internal volume of the aircraft component, in order to vaporise the portion of the cleaning steam that condensed during the condensation time; and removing the cleaning steam from the internal volume via a discharge device.

Abstract: A method for borescope inspection of a component uses a stereo borescope for recording the component. The method includes: generating two stereoscopic partial images by means of the stereo borescope; calculating 3D triangulation data from the two stereoscopic partial images; registering the 3D triangulation data to a 3D CAD reference model of the component captured by the stereo borescope, while determining a projection point; projecting 2D image data determined from the two stereoscopic partial images onto the 3D CAD reference model from the determined projection point; and determining damage by image analysis of the projected 2D image data and by ascertaining deviations of the registered 3D triangulation data vis-à-vis the 3D CAD reference model.

Abstract: A sandwich structure includes two cover layers and a core arranged therebetween, and at least one connecting element for connection to further components. The connecting element has an insert, which is embedded into the sandwich structure at a cover layer of the two cover layers. An embedding depth of the insert is less than a thickness of the core. The connecting element is finished flush with an outer side of the cover layer via which the connecting element is embedded or protrudes from the cover layer.

Abstract: A method for cleaning a jet engine includes introducing a cleaning medium having solid materials into the engine by way of at least one discharging device, wherein the cleaning medium exits from the discharging device at an exit speed of 80 m/s or less.

Abstract: A device for recontouring a gas turbine blade includes: a holding device having at least one cutting tool; and a guide configured to guide the cutting tool along a leading edge of the gas turbine blade. The cutting tool is configured to remove material from the gas turbine blade using a rotational movement about an axis of rotation. The axis of rotation forms an angle together with a chord of the gas turbine blade in a profile section plane, which extends perpendicularly to a radial extent of the gas turbine blade, and the angle is less than 45°.

Abstract: A device that equalizes an aircraft pressure difference has a separating wall, fixable to the aircraft, and a decompression valve. The wall is for fluidically separating first and second spaces, and has a flow opening that fluidically connects the spaces. The valve closes the flow opening. A securing element on the valve or wall enables a release of the valve when a pressure gradient between the spaces is exceeded, such that there is a fluidic connection between the spaces. The receiving element on the wall or valve is connected to the receiving element. The securing element has a rotary element and fixing elements. The rotary element is rotatably mounted about a rotational shaft. The rotary element is receivable in the receiving element. The fixing elements non-rotatably fix the rotary element beneath the predetermined pressure gradient. At least one of the fixing elements is a spring.

Abstract: A radome wall for communication in a frequency band of from 17 to 31 GHz for use on commercial aircraft includes a multilayer structure having an alternating arrangement of force-absorbing solid cover layers and sheer-rigid core layers. The radome wall includes at least four of the cover layers, of which two form outer sides of the radome wall, the cover layers and the core layers being made of a dielectric material.