Abstract: A method for simulating the distribution of blades on a turbomachine disc includes: providing blade configurations, each being associated with a blade and including at least one measurement of a balancing parameter measured on the associated blade; and searching for and selecting a bladed-disc distribution combining the configurations of blades supplied with positions on the disc, the bladed disc distribution encouraging the attainment of at least one criterion defined according to a predetermined cost function dependent on the balancing parameter measurements, and the searching and selecting being performed by successive iterations.

Abstract: The invention relates to a method (100) for manufacturing a turbomachine fan comprising a plurality of blades mounted on a disc extending along a longitudinal axis, said method comprising the following steps of: —measuring (102) at least one structural parameter of each of the blades in the cold state, and, for each of the blades, estimating (103) at least one structural parameter in operation relating to a blade from the structural parameter(s) measured on said blade in the cold state, —determining (104) an optimal sequence of the blades around the disc from the structural parameters estimated in operation for each of the blades, and —mounting (105) the blades on the disc in the optimal sequence thus determined.

Abstract: An aircraft propulsion unit including two distinct fan spools, and including a first duct and a second duct extending downstream of the two fan spools, the propulsion unit including a control ring disposed on one of the ducts, downstream of one of the fan spools, with at least one annular internal wall extending in an interior space of the duct, the control unit of the control ring being configured to modify the shape of the internal wall, and to cause an air passage cross section in the duct to vary at the ring, a device for acquiring acoustic signals generated by acoustic waves propagating downstream of the fan spools, and a device for processing the acoustic signals, configured to measure a dephasing between the acoustic waves and to control the control ring depending on the dephasing.

Abstract: A method for simulating the distribution of blades on a turbomachine disc, including providing blade configurations, each being associated with a blade and including at least one measurement of a balancing parameter measured on the associated blade, search for and selection of a bladed-disc distribution combining the configurations of blades supplied with positions on the disc, the bladed disc distribution encouraging the attainment of at least one criterion defined according to a predetermined cost function dependent on the balancing parameter measurements, the search and selection being performed by successive iterations.

Abstract: An aircraft propulsion unit including two distinct fan spools, and including a first duct and a second duct extending downstream of the two fan spools, the propulsion unit including a control ring disposed on one of the ducts, downstream of one of the fan spools, with at least one annular internal wall extending in an interior space of the duct, the control unit of the control ring being configured to modify the shape of the internal wall, and to cause an air passage cross section in the duct to vary at the ring, a device for acquiring acoustic signals generated by acoustic waves propagating downstream of the fan spools, and a device for processing the acoustic signals, configured to measure a dephasing between the acoustic waves and to control the control ring depending on the dephasing.

Abstract: A method for reducing the noise level generated by a fan of a turbomachine including a plurality of vanes, said method further including, when the turbomachine is operating and under given flight conditions, the following steps measuring an operational pitch angle for each of the vanes, calculating an offset between the operational pitch angle of each of the vanes and a predetermined reference pitch angle for the given flight conditions so as to produce a controlled noise level at multiple rotation frequencies of the fan, correcting the orientation of the vanes so as to compensate their operational pitch angles depending on the offsets thus calculated.

Abstract: The invention relates to a method (100) for manufacturing a turbomachine fan comprising a plurality of blades mounted on a disc extending along a longitudinal axis, said method comprising the following steps of: —measuring (102) at least one structural parameter of each of the blades in the cold state, and, for each of the blades, estimating (103) at least one structural parameter in operation relating to a blade from the structural parameter(s) measured on said blade in the cold state, —determining (104) an optimal sequence of the blades around the disc from the structural parameters estimated in operation for each of the blades, and —mounting (105) the blades on the disc in the optimal sequence thus determined.

Abstract: A turbojet fan blade in which a leading edge presents a sweep angle greater than or equal to +28° in a portion of the blade that is situated at a radial height lying in a range of 60% to 90% of a total radial height of the blade measured from its root towards its tip, and the leading-edge sweep angle presents a difference of less than 10° between a minimum sweep angle measured at a radial height of minimum sweep angle situated in the portion of the blade lying in a range of 20% to 90% of the radial height of the blade, and a sweep angle measured at a radial height that is 10% greater than the radial height of minimum sweep angle.

Abstract: A method of controlling a turbine engine, including: measuring a first temperature by a first temperature sensor; measuring a second temperature by a second temperature sensor; estimating a third temperature modeling the first temperature; and determining at least one control setpoint for at least one piece of variable-geometry equipment of the engine, as a function of the measured first temperature. The first sensor presents a time constant longer than a time constant of the second sensor. The method further detects ingestion of water or hail as a function of a drop in the measured second temperature; and when water or hail ingestion is detected, determines the control setpoint as a function of the estimated third temperature.

Abstract: A method for reducing the noise level generated by a fan of a turbomachine including a plurality of vanes, said method further including, when the turbomachine is operating and under given flight conditions, the following steps measuring an operational pitch angle for each of the vanes, calculating an offset between the operational pitch angle of each of the vanes and a predetermined reference pitch angle for the given flight conditions so as to produce a controlled noise level at multiple rotation frequencies of the fan, correcting the orientation of the vanes so as to compensate their operational pitch angles depending on the offsets thus calculated.

Abstract: A combined device for windrowing and for baling by pressing, particularly of hay, intended to be connected to a tractor equipped with a three-point hitch and with a power takeoff, includes hitching elements (10), a single frame (12) on wheels (54-1, 54-2) including windrowing elements (14) and elements (16) for receiving and supporting a baler (18). The device also includes a second variant.

Abstract: A turbojet fan blade in which a leading edge presents a sweep angle greater than or equal to +28° in a portion of the blade that is situated at a radial height lying in a range of 60% to 90% of a total radial height of the blade measured from its root towards its tip, and the leading-edge sweep angle presents a difference of less than 10° between a minimum sweep angle measured at a radial height of minimum sweep angle situated in the portion of the blade lying in a range of 20% to 90% of the radial height of the blade, and a sweep angle measured at a radial height that is 10% greater than the radial height of minimum sweep angle.

Abstract: A method of controlling a turbine engine, including: measuring a first temperature by a first temperature sensor; measuring a second temperature by a second temperature sensor; estimating a third temperature modeling the first temperature; and determining at least one control setpoint for at least one piece of variable-geometry equipment of the engine, as a function of the measured first temperature. The first sensor presents a time constant longer than a time constant of the second sensor. The method further detects ingestion of water or hail as a function of a drop in the measured second temperature; and when water or hail ingestion is detected, determines the control setpoint as a function of the estimated third temperature.