Abstract: A method of analyzing an ultrasound image involves assessing the quality of the image in terms of which features of interest have been identified in the image and assessing a segmentation quality relating to the quality of a segmentation of the image. The two quality assessments are combined to derive and output an overall quality assessment for biometry measurements obtained from the image.

Abstract: In some examples, one or more three dimensional (3D) objects may be rendered in relation to a two dimensional (2D) imaging slice. The 3D object may be rendered such that the 3D object casts a colored shadow on the 2D imaging slice. In some examples, the 3D object may be rendered in colors where different colors indicate a distance from the portion of the 3D object from the 2D imaging slice.

Abstract: The invention provides a method for determining a global confidence index for a 2D ultrasound image extracted from a 3D ultrasound volume, wherein the global confidence index indicates the suitability of the 2D ultrasound image for medical measure-ments. The method comprises obtaining a 3D ultrasound volume of a subject and extracting a set of at least one 2D ultrasound image from the 3D ultrasound volume. A set of geometrical indicators are then obtained with a first neural network, wherein each geometrical indicator indicates geometrical features of the anatomy of the subject. The set of 2D ultrasound images are then processed with a second neural network, wherein the output of the second neural network is a set of anatomical indicators and wherein the anatomical indicators indicate at least the presence of anatomical landmarks. A global confidence index is then determined for each one of the set of 2D ultrasound images based on the geometrical indicators and the anatomical indicators.

Abstract: A method for monitoring a locking system includes N locks, each lock being monitored by two locking sensors, each locking sensor being capable of indicating if the lock that it monitors is in a locked or unlocked state, each locking sensor being able to be in a valid or invalid status, the method including determining the state of the locking system on the basis of the state of the locks detected by the locking sensors; determining a reliability level associated with the state of the locking system on the basis of the number of valid locking sensors monitoring the locks that are in the same state as the locking system.

Abstract: A method for monitoring a locking system includes N locks, each lock being monitored by two locking sensors, each locking sensor being capable of indicating if the lock that it monitors is in a locked or unlocked state, each locking sensor being able to be in a valid or invalid status, the method including determining the state of the locking system on the basis of the state of the locks detected by the locking sensors; determining a reliability level associated with the state of the locking system on the basis of the number of valid locking sensors monitoring the locks that are in the same state as the locking system.

Abstract: A method for monitoring at least one locking device of an electrical thrust reversal system for a turbine engine, the method being carried out by a computer prior to the take-off of the turbine engine, the method including sending a command for opening the locking devices; verifying the opening of the locking devices; sending a command for closing the locking devices; and verifying the closing of the locking devices.

Abstract: A method for monitoring at least one locking device of an electrical thrust reversal system for a turbine engine, the method being carried out by a computer prior to the take-off of the turbine engine, the method including sending a command for opening the locking devices; verifying the opening of the locking devices; sending a command for closing the locking devices; and verifying the closing of the locking devices.

Abstract: A turbine engine for aircraft includes a gas generator as well as to a receiver driven by a power turbine, and to an electric power generator, the rotor of which centered on a rotor axis distinct from the longitudinal axis, is driven into rotation by the power turbine, via a mechanical gear transmission, including a toothed drive wheel centered on the axis. Further the receiver includes a first propeller driven by a free power turbine and the toothed drive wheel is attached on an outer case of this power turbine.

Abstract: A twin-spool gas turbine turbojet comprising a high-pressure rotor; a low-pressure rotor; a low-pressure rotor shaft connected to a fan housed in a fan casing; and a fixed cowl element centered on the axis of the engine, upstream of the fan, on which there is mounted an electric current generator designed to take mechanical power off the low-pressure rotor shaft and convert it into electrical power.

Abstract: The present invention relates to a turbine engine for aircraft comprising a gas generator as well as to a receiver driven by a power turbine (34), and to an electric power generator (60), the rotor (62) of which centred on a rotor axis (62?) distinct from the longitudinal axis (2), is driven into rotation by the power turbine, via a mechanical gear transmission (80), comprising a toothed drive wheel (82) centred on the axis (2). Further the receiver comprises a first propeller driven by a free power turbine (34) and the toothed drive wheel (82) is attached on an outer case (40) of this power turbine (34).

Abstract: A device for producing electrical power in a multi-spool gas turbine engine is disclosed. The device includes at least one first rotary spool and a second rotary spool which drives an electrical machine. The electrical machine is of the twin-rotor type with a first rotor and a second rotor. The first rotor is mechanically connected to the first rotary spool and the second rotor is mechanically connected to the second rotary spool.

Abstract: A turbine engine for an aircraft is disclosed. The engine includes a gas generator and a receiver driven by a power turbine. The receiver includes a propeller driven by a free power turbine provided with an outer case. The propeller includes a propeller case located radially outwards relatively to the outer case, and from which blades protrude radially outwards. The engine also includes an electric power generator. The rotor of the generator is centered on the longitudinal axis of the turbine engine, and is driven into rotation by the power turbine while being attached on the propeller case.

Abstract: The present invention relates to a turbine engine (100) for aircraft comprising a gas generator (14) as well as a receiver (30) driven by a power turbine (34, 38), this receiver comprising a propeller (32) driven by a free power turbine (34) provided with an outer case (40), the propeller (32) having a propeller case (46) located radially outwards relatively to the outer case (40), and from which blades (48) protrude radially outwards. According to the invention, it comprises an electric power generator (60), the rotor (62) of which centred on the longitudinal axis (2) of the turbine engine, is driven into rotation by the power turbine (34) while being attached on the propeller case (46).

Abstract: The invention relates to a twin-spool gas turbine turbojet comprising a high-pressure rotor (1) and a low-pressure rotor, the low-pressure rotor shaft (2) being connected, at its upstream end, to a fan (10) housed in a fan casing (14), which turbojet comprises, upstream of the fan (10), a fixed cowl element (12) centered on the axis (X3) of the engine and on which there is mounted an electric current generator (20) designed to take mechanical power off the low-pressure rotor shaft (2) and convert it into electrical power.

Abstract: The invention relates to a device for producing electrical power in a multi-spool gas turbine engine comprising at least one first rotary spool (69), for example a low-pressure spool, and a second rotary spool (24), for example a high-pressure spool, and driving an electrical machine (10). The device is one wherein, with the electrical machine (10) being of the twin-rotor type with a first rotor (13) and a second rotor (14), the first rotor (13) is mechanically connected to the first rotary spool (69) and the second rotor is mechanically connected to the second rotary spool (24).