Abstract: A turbomachine including at least two unducted propellers, one of which is an upstream propeller and one a downstream propeller, the upstream propeller including a plurality of blades, at least one first blade of which has a different length from that of a second blade.

Abstract: A variable-pitch bladed disc including a plurality of blades, each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each having a root and a tip, each root being mounted at the tip of a corresponding rotor connecting shaft by way of a pivot so as to allow each blade to rotate about the blade rotation axis, the first blade having a first blade inclination, such that the first blade is inclined in a fixed manner with respect to the blade rotation axis of the first blade, and the second blade having a second blade inclination different from the first blade inclination.

Abstract: A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.

Abstract: A propulsion assembly for an aircraft, the assembly including a turbojet having at least one unducted propulsive propeller, and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having a streamlined profile defined by two opposite side faces extending transversely between a leading edge and a trailing edge. The pylon includes a plurality of blow nozzles situated in the vicinity of its trailing edge and configured to blow air taken from a pressurized portion of the turbojet, the blow nozzles being positioned over at least a fraction of the trailing edge of the pylon that extends longitudinally facing at least a portion of the propeller. A method of reducing the noise generated by a pylon attaching a turbojet to an aircraft is presented.

Abstract: The present invention pertains to engineered immune cells, method for their preparation and their use as medicament, particularly for immunotherapy. The engineered immune cells of the present invention are characterized in that at least one gene selected from a gene encoding GCN2 and a gene encoding PRDM1 is inactivated or repressed. Such modified Immune cells are resistant to an arginine and/or tryptophan depleted microenvironment caused by, e.g., tumor cells, which makes the immune cells of the invention particularly suitable for immunotherapy. The invention opens the way to standard and affordable adoptive immunotherapy strategies using immune cells for treating different types of malignancies.

Abstract: A process for producing a purified synthesis gas stream from a feed synthesis gas stream comprising besides the main constituents carbon monoxide and hydrogen also hydrogen sulphide, HCN and/or COS, the process comprising the steps of: (a) removing HCN and/or COS by contacting the feed synthesis gas stream with a catalyst in a HCN/COS reactor in the presence of steam/water, to obtain a synthesis gas stream depleted in HCN and/or in COS; (b) converting hydrogen sulphide in the synthesis gas stream depleted in HCN and/or in COS to elemental sulphur, by contacting the synthesis gas stream with an aqueous reactant solution containing solubilized Fe(III) chelate of an organic acid, at a temperature below the melting point of sulphur, and at a sufficient solution to gas ratio and conditions effective to convert H2S to sulphur and inhibit sulphur deposition, to obtain a synthesis gas stream depleted in hydrogen sulphide; (c) removing carbon dioxide from the synthesis gas stream depleted in hydrogen sulphide, to obta