Abstract: An assembly including a stack of solid oxide cells of the SOEC/SOFC type and a clamping system for the stack. This assembly furthermore includes at least one heating plate, demountable and interchangeable, inserted in a housing of at least one of the top and bottom clamping plates, the housing being formed in the thickness of the at least one of the top and bottom clamping plates, and comprising first and second opposite ends, at least one of which emerges on the lateral face-of the at least one of the top and bottom clamping plates, being located inside, at a distance from its main top and bottom faces substantially parallel to each other.

Abstract: The invention relates to an electrochemical device that includes an electrochemical unit. The electrochemical unit includes a stack of SOEC/SOFC-type solid oxides operating at high temperatures, a clamping system provided with two clamping plates, referred to as the first clamping plate and second clamping plate, respectively, between which the stack is clamped, one and/or both of the two clamping plates having at least one gas inlet and at least one gas outlet. The unit includes heating means which are designed to ensure the heating of the electrochemical unit and are integrated into said unit. The device includes a containment box, housed in a volume, referred to as internal volume V, the electrochemical unit, the internal volume V being delimited by a surface, referred to as the internal surface S, of the containment box, which follows the shape of the electrochemical assembly.

Abstract: The present invention relates to a single-domain antibody (sdAb) which binds to the G protein alpha, comprising an amino acid sequence consisting of 3 CDR regions (CDR1 to CDR3) and 4 hinge regions (FR1 to FR4) according to the following formula (I): FR1-CDR1-FR2-CDR2-FR3-CDR3-FR4 (I) and advantageously having a dissociation constant (Kd), measured in FRET, of less than 100 nM.

Abstract: The invention relates to a method for determining the ability of a molecule to modulate the activity of a G protein-coupled receptor (GPCR), said method comprising the following steps: a) introducing, into a first container:—a first membrane preparation bearing one or more GPCRs and one or more G protein(s),—a source of GDP or a source of GTP,—a first ligand of the alpha subunit of a G protein (Galpha protein) labelled with a first member of a pair of RET partners, and a second ligand of the Galpha protein labelled with a second member of the pair of RET partners, said ligands being able to specifically bind, either individually or in combination, to the empty Galpha protein or to the full Galpha protein; b) measuring the RET signal emitted in the first container; c) introducing (i) into a second container, the same reactants as in step a) and the molecule to be tested or (ii) into the first container, the molecule to be tested; d) measuring the RET signal emitted in the second container or in the first conta

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 present invention relates to a single-domain antibody (sdAb) which binds to the G protein alpha, comprising an amino acid sequence consisting of 3 CDR regions (CDR1 to CDR3) and 4 hinge regions (FR1 to FR4) according to the following formula (I): FR1-CDR1-FR2-CDR2-FR3-CDR3-FR4 (I) and advantageously having a dissociation constant (Kd), measured in FRET, of less than 100 nM.

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: An artificial retina that includes: (i) a substrate; (ii) a first layer, placed onto said substrate and including photovoltaic material portions separated by at least one insulating material portion; and (iii) a second layer, placed onto said first layer and including conductive material portions separated by at least one insulating material portion. In said artificial retina, the photovoltaic material includes a titanium dioxide semiconductor.

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.

Abstract: An artificial retina that includes: (i) a substrate; (ii) a first layer, placed onto said substrate and including photovoltaic material portions separated by at least one insulating material portion; and (iii) a second layer, placed onto said first layer and including conductive material portions separated by at least one insulating material portion. In said artificial retina, the photovoltaic material includes a titanium dioxide semiconductor.