Abstract: A propeller for an aircraft turbine engine, comprising means for adjusting the pitch of the blades comprising a hydraulic actuator borne by the rotor and including a cavity and a piston displaceable in said cavity and dividing said cavity into two chambers, as well as means for limiting the stroke of the piston in order to prevent displacement of said blades in a predetermined direction beyond a predetermined limiting pitch angle, and comprising hydraulic connection means with which both chambers may be put into communication with each other as soon as the pitch angle of the blades becomes equal to said predetermined limiting pitch angle during the displacement of said blades in said predetermined direction, these hydraulic connection means being borne by said rotor of the propeller.

Abstract: Turbomachine blade incidence control system including a fluidic cylinder with a first and a second chamber and having a pressurized fluid network adapted to selectively supply pressurized fluid to the first and/or the second chamber, the fluid network having one fluid routing device having a first normal position and a second protection position. The fluidic cylinder includes a fluid inlet positioned to be in fluid communication with the first chamber when the fluidic cylinder is in the blocked position, the routing device being adapted to set up a fluid communication between the inlet and the second chamber when it is in the protection position and to inhibit the fluid supply to the inlet when it is in the normal position.

Abstract: A propeller for an aircraft turbine engine, comprising means for adjusting the pitch of the blades comprising a hydraulic actuator borne by the rotor and including a cavity and a piston displaceable in said cavity and dividing said cavity into two chambers, as well as means for limiting the stroke of the piston in order to prevent displacement of said blades in a predetermined direction beyond a predetermined limiting pitch angle, and comprising hydraulic connection means with which both chambers may be put into communication with each other as soon as the pitch angle of the blades becomes equal to said predetermined limiting pitch angle during the displacement of said blades in said predetermined direction, these hydraulic connection means being borne by said rotor of the propeller.

Abstract: The actuator (50) comprises a slide (52) carrying at least two stages (54, 56) and being capable of sliding in a cylinder and two control chambers (62, 64) connected to respective use holes (U1, U2) of an electrically controlled servo-valve hydraulic distributor (20). The control chambers (62, 64) are each situated on one side of a respective stage and an intermediate chamber connected to high or low pressure is situated between the other sides of the stages. In the event of electrical control failure, the distributor (20) slide is taken to a safety position in which the control chambers (62, 64) of the actuator (50) are at the same low or high pressure opposed to that applying in the intermediate chamber (66) so that each stage of the actuator slide is then subjected to high pressure on one side and to low pressure on the other side.

Abstract: The actuator (50) comprises a slide (52) carrying at least two stages (54, 56) and being capable of sliding in a cylinder and two control chambers (62, 64) connected to respective use holes (U1, U2) of an electrically controlled servo-valve hydraulic distributor (20). The control chambers (62, 64) are each situated on one side of a respective stage and an intermediate chamber connected to high or low pressure is situated between the other sides of the stages. In the event of electrical control failure, the distributor (20) slide is taken to a safety position in which the control chambers (62, 64) of the actuator (50) are at the same low or high pressure opposed to that applying in the intermediate chamber (66) so that each stage of the actuator slide is then subjected to high pressure on one side and to low pressure on the other side.

Abstract: A system for injecting fuel into a turbomachine comprising N fuel injectors placed in a combustion chamber of the turbomachine and fed from a fuel tank, the injection system further comprising, interposed between the N injectors and the tank, a single pumping means for taking fuel from the tank and delivering N metered flow rates of fuel to the injectors.

Abstract: A system for injecting fuel into a turbomachine comprising N fuel injectors placed in a combustion chamber of the turbomachine and fed from a fuel tank, the injection system further comprising, interposed between the N injectors and the tank, a single pumping means for taking fuel from the tank and delivering N metered flow rates of fuel to the injectors.