Abstract: A method of locating code image zones in an output image of a code bearing object (14), wherein first candidates for code image zones are determined in a first segmentation process using a process of classical image processing without machine learning and second candidates for code image zones are determined in a second segmentation process using machine learning, with the first and second candidates being fused to locate the code image zones.

Abstract: A method for reading optical codes (12) with distortions caused by an uneven background of the code (12), the method comprising the steps of acquiring image data including the code (12), locating a region including the code (12) in the image data, and reading the code content of the code (12) from image data in the region, wherein the code (12) is read from image data at sampling points arranged in a sampling pattern corresponding to the distortions.

Abstract: A method for reading optical codes (12) with distortions caused by an uneven back-ground of the code (12), the method comprising the steps of acquiring image data including the code (12), locating a region including the code (12) in the image data, and reading the code content of the code (12) from image data in the region, wherein the code (12) is read from image data at sampling points arranged in a sampling pattern corresponding to the distortions.

Abstract: An aircraft engine having at least two shafts, each mounted rotatably about a center axis of the aircraft engine. A first shaft is driven, during operation of the aircraft engine, at a lower speed than a second shaft of the aircraft engine. A chamber limited at least in some areas by one of the shafts is provided, inside which is arranged a device for separating oil from an air-oil volume flow, said device being in operative connection with one of the shafts of the aircraft engine. The device for separating oil is in operative connection with the second shaft of the aircraft engine.

Abstract: A device for the extraction of bleed air from flowing air at or in an aircraft engine is provided. The device includes a means for specific adjustment of an inlet cross section of an opening at or in the area of a wall of the aircraft engine and a flow guide means for a boundary layer flow.

Abstract: A turbofan engine includes a core engine, having a high-pressure compressor, a combustion chamber and a high-pressure turbine which are coupled to one another via a high-pressure shaft, at least one fan from which gas is supplied into both a primary flow duct and a secondary flow duct of the turbofan engine, at least one low-pressure turbine arranged behind the core engine, and at least one low-pressure shaft, with each low-pressure shaft coupling a fan to a low-pressure turbine. It has been provided that no low-pressure shaft of the turbofan engine passes through the core engine.

Abstract: An aircraft engine including a fan having a center of mass, a low-pressure shaft that couples the fan directly to a low-pressure turbine of the aircraft engine, and a bearing arrangement for mounting the low-pressure shaft, where the bearing arrangement has at least two front bearings for mounting the low-pressure shaft, a first front bearing and a second front bearing, with the first front bearing being arranged in the axial direction in front of the second front bearing. It has been provided that the first front bearing is arranged substantially in the same plane, extending perpendicular to the longitudinal axis of the aircraft engine, as the center of mass of the fan.

Abstract: An aircraft engine having at least two shafts, each mounted rotatably about a center axis of the aircraft engine. A first shaft is driven, during operation of the aircraft engine, at a lower speed than a second shaft of the aircraft engine. A chamber limited at least in some areas by one of the shafts is provided, inside which is arranged a device for separating oil from an air-oil volume flow, said device being in operative connection with one of the shafts of the aircraft engine. The device for separating oil is in operative connection with the second shaft of the aircraft engine.

Abstract: A detection system for optical codes that are applied to an object that is conveyed through a reading field of a sensor of the detection system, wherein the detection system is configured to record a sequence of images from a respective part of the object which is present in the reading field at the respective time of recording of a respective image by means of the sensor, is characterized in that the detection system is further configured to determine a respective displacement vector between two respective consecutive images of the image sequence by means of the two respective consecutive images, wherein the respective displacement vector reflects how far an image region included in an image is displaced relative to a previous image, and with the image region also being present in the previous image.

Abstract: A device for the extraction of bleed air from flowing air at or in an aircraft engine is provided. The device includes a means for specific adjustment of an inlet cross section of an opening at or in the area of a wall of the aircraft engine and a flow guide means for a boundary layer flow.

Abstract: An optoelectronic device (10) is provided having an image sensor (20) for generating pixel images of a detection area (12) and a brightness correction unit (28) configured to modify brightness values of the pixels with a correction factor (Hmul) to obtain a more homogeneously illuminated image. A respective correction factor (Hmul) is calculated for individual pixels or groups of pixels from a perspective transformation (M) which converts geometries of an object plane (34) in the detection area (12) into geometries of the image plane (32).

Abstract: An optoelectronic apparatus is set forth for measuring structural sizes or object sizes which has a light reception element for converting received light into image data, a reception optics arranged before the light reception element as well as an evaluation unit which is configured to identify structures or objects in the image data, to determine its dimensions in picture elements and to convert the dimensions into absolute, in particular metric, units of length with reference to a scaling factor, wherein the scaling factor can be determined in a calibration procedure. In this respect, the evaluation unit is configured to locate code regions in the image data and to read out code information from the code regions and to calculate the scaling factor during the calibration procedure from dimensions of a calibration code whose code information includes a size indication for the calibration code in the absolute units of length.

Abstract: A device and method for discharging sealing air in a turbofan engine includes a primary flow duct that extends through a core engine of the turbofan engine and a bypass duct. The device has at least one bearing chamber sealed by sealing air of the turbofan engine, said bearing chamber surrounding at least one oil-lubricated bearing element for mounting a mechanical component of the turbofan engine. At least one discharge path for escaping sealing air is provided, which extends up to the bypass duct of the turbofan engine.

Abstract: A turbofan engine includes a core engine, having a high-pressure compressor, a combustion chamber and a high-pressure turbine which are coupled to one another via a high-pressure shaft, at least one fan from which gas is supplied into both a primary flow duct and a secondary flow duct of the turbofan engine, at least one low-pressure turbine arranged behind the core engine, and at least one low-pressure shaft, with each low-pressure shaft coupling a fan to a low-pressure turbine. It has been provided that no low-pressure shaft of the turbofan engine passes through the core engine.

Abstract: An aircraft engine including a fan having a center of mass, a low-pressure shaft that couples the fan directly to a low-pressure turbine of the aircraft engine, and a bearing arrangement for mounting the low-pressure shaft, where the bearing arrangement has at least two front bearings for mounting the low-pressure shaft, a first front bearing and a second front bearing, with the first front bearing being arranged in the axial direction in front of the second front bearing. It has been provided that the first front bearing is arranged substantially in the same plane, extending perpendicular to the longitudinal axis of the aircraft engine, as the center of mass of the fan.

Abstract: A code reader (10) having an image sensor (20) for the generation of images of a detection zone (12) resolved into pixels is provided having a decoding unit (24) in order to identify code regions (14) in the images and to readout their coded information, as well as having a verification unit (28) for evaluating the code quality in accordance with predefined criteria. In this connection the verification (28) is configured to initially generate a normalized verification image of the code from the code regions (14) by means of image processing for the verification.

Abstract: The present invention describes an aircraft gas turbine with a first rotatable shaft and a second shaft arranged coaxially thereto and which at least in an area close to the shaft end is non-rotatably connected to the first shaft. Recesses are provided in shaft areas at a distance from the connecting area between the shafts, said recesses overlapping one another at least in some areas when a defined twist of the first shaft relative to the second shaft is exceeded. The shafts are assigned at least one lever element designed rotatable and engaging in the recesses of the shafts in the radial direction in the area of an end of the shafts and swivelling about a pivot point. A second lever arm of the lever elements is, when the first lever arm is engaged in the recesses, operatively connectable to an electric sensor device, in the area of which a sensor signal equivalent to the defined twist of the first shaft can be generated.

Abstract: A code reader (10) having an image sensor (20) for the generation of images of a detection zone (12) resolved into pixels is provided having a decoding unit (24) in order to identify code regions (14) in the images and to readout their coded information, as well as having a verification unit (28) for evaluating the code quality in accordance with predefined criteria. In this connection the verification (28) is configured to initially generate a normalized verification image of the code from the code regions (14) by means of image processing for the verification.

Abstract: An optoelectronic device (10) is provided having an image sensor (20) for generating pixel images of a detection area (12) and a brightness correction unit (28) configured to modify brightness values of the pixels with a correction factor (Hmul) to obtain a more homogeneously illuminated image. A respective correction factor (Hmul) is calculated for individual pixels or groups of pixels from a perspective transformation (M) which converts geometries of an object plane (34) in the detection area (12) into geometries of the image plane (32).

Abstract: An optoelectronic apparatus is set forth for measuring structural sizes or object sizes which has a light reception element for converting received light into image data, a reception optics arranged before the light reception element as well as an evaluation unit which is configured to identify structures or objects in the image data, to determine its dimensions in picture elements and to convert the dimensions into absolute, in particular metric, units of length with reference to a scaling factor, wherein the scaling factor can be determined in a calibration procedure. In this respect, the evaluation unit is configured to locate code regions in the image data and to read out code information from the code regions and to calculate the scaling factor during the calibration procedure from dimensions of a calibration code whose code information includes a size indication for the calibration code in the absolute units of length.