Abstract: The invention relates to the field of centrifugal pumps, and in particular it relates to a centrifugal pump (303, 403) comprising at least: an impeller (303a, 403a); a rotary shaft (302, 402) secured to said impeller (303a, 403a); a casing (320, 420) having an axial admission passage (325, 425); at least one first bearing (305, 405) supporting said rotary shaft (302, 402) in said casing (320, 420); and at least one dynamic seal (311, 411) around the rotary shaft (302, 402), the impeller (303a, 403a) being situated between the at least one dynamic seal (311, 411) and the axial admission passage (325, 425) of the pump (303, 403). The centrifugal pump (303, 403) also comprises, between the impeller (303a, 403a) and at least one dynamic seal (311, 411), an axial force compensation disk (330, 430) secured to the shaft (302, 402) and presenting a diameter greater than 70% of a diameter of the impeller (303a, 403a).

Abstract: An emergency start system for a turbine engine of an aircraft including at least one solid propellant gas generator, an electrically controlled ignition device, a computer connected to the ignition device, and at least one starter motor comprising a turbine for driving a shaft which is for coupling to a shaft of the turbine engine The outlet of the gases from the generator are connected to the inlet of the turbine of the starter motor.

Abstract: A turbopump for feeding a low-thrust rocket engine comprises a pump, a turbine, and a common rotary shaft connected to the pump and to the turbine. First and second bearings closer respectively to the pump and to the turbine serve to support the common shaft. The second bearing is a hydrodynamic bearing connected to a gas supply source, and the turbopump also includes at least one dynamic sealing gasket around the shaft and interposed between the first and second bearings.

Abstract: The invention relates to an emergency start system (20) for a turbine engine of an aircraft, characterised in that it comprises at least one solid-propellant gas generator (22), an electrically controlled ignition device (24), a computer (28) connected to the ignition device, and at least one starter motor (18) comprising a turbine (38) for driving a shaft (34) intended for being coupled to a shaft (54) of the turbine engine, the outlet of the gases from the generator being connected to the inlet (44) of the turbine of the starter motor.

Abstract: A device (10A, 10B) for feeding a rocket engine with propellant, the device comprising at least one propellant tank (10, 11), a combustion chamber (18), and a feed pipe (12, 13) extending from the tank (10, 11) to the combustion chamber (18) to feed propellant to the combustion chamber. A valve (14, 15) and a main pump (16, 17) are arranged in succession along the feed pipe. The rocket engine device further comprises at least one branch pump (20, 21, 120, 220) making a branch connection to the tank upstream from the valve in order to feed an auxiliary pipe (22, 23, 122, 222) that serves an auxiliary function of the rocket engine.

Abstract: The invention relates to the field of centrifugal pumps, and in particular it relates to a centrifugal pump (303, 403) comprising at least: an impeller (303a, 403a); a rotary shaft (302, 402) secured to said impeller (303a, 403a); a casing (320, 420) having an axial admission passage (325, 425); at least one first bearing (305, 405) supporting said rotary shaft (302, 402) in said casing (320, 420); and at least one dynamic seal (311, 411) around the rotary shaft (302, 402), the impeller (303a, 403a) being situated between the at least one dynamic seal (311, 411) and the axial admission passage (325, 425) of the pump (303, 403). The centrifugal pump (303, 403) also comprises, between the impeller (303a, 403a) and at least one dynamic seal (311, 411), an axial force compensation disk (330, 430) secured to the shaft (302, 402) and presenting a diameter greater than 70% of a diameter of the impeller (303a, 403a).

Abstract: The invention relates mainly to a test bench (10) for a radial bearing (14) suitable for being interposed between two members (12, 16) that are movable relative to each other in rotation, the test bench being characterized in that it comprises a radial force measurement device (18) for measuring radial forces exerted on said bearing (14), a radial acceleration measurement device (20) for measuring radial accelerations to which said bearing (14) is subjected, and an electronic calculation unit (26) in communication with the radial force measurement device (18) and with the radial acceleration measurement device (20). The invention also relates to a method of establishing a behavior relationship for the radial bearing (14).

Abstract: The invention relates mainly to a test bench (10) for a radial bearing (14) suitable for being interposed between two members (12, 16) that are movable relative to each other in rotation, the test bench being characterized in that it comprises a radial force measurement device (18) for measuring radial forces exerted on said bearing (14), a radial acceleration measurement device (20) for measuring radial accelerations to which said bearing (14) is subjected, and an electronic calculation unit (26) in communication with the radial force measurement device (18) and with the radial acceleration measurement device (20). The invention also relates to a method of establishing a behavior relationship for the radial bearing (14).

Abstract: A turbopump for feeding a low-thrust rocket engine comprises a pump, a turbine, and a common rotary shaft connected to the pump and to the turbine. First and second bearings closer respectively to the pump and to the turbine serve to support the common shaft. The second bearing is a hydrodynamic bearing connected to a gas supply source, and the turbopump also includes at least one dynamic sealing gasket around the shaft and interposed between the first and second bearings.

Abstract: Pump (1) comprising a rotary shaft (30), a bearing housing (80) that is fixed relative to the rotary shaft, at least one rolling bearing (70) the inner ring (71) of which is connected to the said rotary shaft and the outer ring (76) of which is able to slide in this housing along the axis of rotation of the rotary shaft. The bearing housing (80) comprises a shoulder (81) situated on one side of this bearing and able rigidly to prevent translational movement of the outer ring (76) along the axis of rotation, and a deformable elastic device (100) fixed to the housing on the other side of the bearing (70) so that the bearing lies between the shoulder and the elastic device.

Abstract: The invention relates to a centrifugal pump.

Abstract: The invention relates to a rotary machine for passing a main liquid stream, the machine comprising: a shaft mounted to rotate relative to a casing of the rotary machine; and an active axial balancing system suitable for exerting a first axial take-up force on the shaft. The invention further comprising a circuit for a secondary liquid stream taken from the main liquid stream, and a passive axial balancing system suitable for exerting a second axial take-up force on the shaft, said passive axial balancing system being fed by the circuit for the secondary liquid stream.

Abstract: Pump (1) comprising a rotary shaft (30), a bearing housing (80) that is fixed relative to the rotary shaft, at least one rolling bearing (70) the inner ring (71) of which is connected to the said rotary shaft and the outer ring (76) of which is able to slide in this housing along the axis of rotation of the rotary shaft. The bearing housing (80) comprises a shoulder (81) situated on one side of this bearing and able rigidly to prevent translational movement of the outer ring (76) along the axis of rotation, and a deformable elastic device (100) fixed to the housing on the other side of the bearing (70) so that the bearing lies between the shoulder and the elastic device.