Abstract: A turbomachine including: a combustion chamber, with a fuel injection device in the combustion chamber; a supply mechanism supplying fuel to the fuel injection device; a mechanism determining instantaneous variation of fuel flow rate of the supply mechanism; and a regulation mechanism regulating the fuel flow rate of the injection device according to the instantaneous variation of the fuel flow rate of the supply mechanism determined by the determination mechanism.

Abstract: This method of calibration comprising the reconstruction of a 3D mapping of 3D landmarks of an environment on the basis of digital images of the environment captured by the computer-based vision system (10) during the movement of the craft (2) along a trajectory. It comprises the optimization of at least one 3D mapping corresponding to a first sequence of images by considering at least one extrinsic parameter and/or at least one intrinsic parameter and/or at least one parameter of poses and/or one parameter of 3D landmarks as constant and the optimization of at least one 3D mapping corresponding to a second sequence of images, longer than the first image sequence and including the first image sequence, by considering said at least one extrinsic parameter and/or said at least one intrinsic parameter and/or said at least one parameter of poses and/or said at least one parameter of 3D landmarks as variable so as to estimate it.

Abstract: This method of calibration comprising the reconstruction of a 3D mapping of 3D landmarks of an environment on the basis of digital images of the environment captured by the computer-based vision system (10) during the movement of the craft (2) along a trajectory. It comprises the optimization of at least one 3D mapping corresponding to a first sequence of images by considering at least one extrinsic parameter and/or at least one intrinsic parameter and/or at least one parameter of poses and/or one parameter of 3D landmarks as constant and the optimization of at least one 3D mapping corresponding to a second sequence of images, longer than the first image sequence and including the first image sequence, by considering said at least one extrinsic parameter and/or said at least one intrinsic parameter and/or said at least one parameter of poses and/or said at least one parameter of 3D landmarks as variable so as to estimate it.

Abstract: A turbomachine including: a combustion chamber, with a fuel injection device in the combustion chamber; a supply mechanism supplying fuel to the fuel injection device; a mechanism determining instantaneous variation of fuel flow rate of the supply mechanism; and a regulation mechanism regulating the fuel flow rate of the injection device according to the instantaneous variation of the fuel flow rate of the supply mechanism determined by the determination mechanism.

Abstract: A monitoring device for monitoring rotors of turbines, including: an acoustic sensor; and a sound waveguide for connecting the acoustic sensor to a sensing point close to the rotor of the turbine. The acoustic sensor is configured to detect, as soundwaves, pressure fluctuations due to pressure differences between suction and pressure sides of blades of the rotor as they move past in proximity of a sensing point. A method of monitoring a rotor of a turbine transmits pressure fluctuations due to pressure differences between suction sides and pressure sides of blades of the rotor going past the proximity of a sensing point by a sound waveguide to an acoustic sensor to be picked up as soundwaves.

Abstract: A de-icer device for de-icing an air inlet of a gas turbine, such as a helicopter turbine engine. The de-icer device includes an essentially metallic enclosure for admitting air into the engine, the enclosure including a first opening for admitting air into the enclosure, the first opening including a first essentially metallic grid, the enclosure further including a second opening for directing the air towards a compression stage of the gas turbine. The de-icer device further includes a wave generator for generating electromagnetic waves in the enclosure at a frequency suitable for causing ice to melt.

Abstract: A de-icer device for de-icing an air inlet of a gas turbine, such as a helicopter turbine engine. The de-icer device includes an essentially metallic enclosure for admitting air into the engine, the enclosure including a first opening for admitting air into the enclosure, the first opening including a first essentially metallic grid, the enclosure further including a second opening for directing the air towards a compression stage of the gas turbine. The de-icer device further includes a wave generator for generating electromagnetic waves in the enclosure at a frequency suitable for causing ice to melt.