The invention relates to a turbomachine comprising a device for ventilating and pressurising a turbine rotor of a turbomachine of axis (A), the device comprising at least one collection pipe suitable for collecting a fraction of the air circulating in a high-pressure compressor of the turbomachine and conveying it to a first inner chamber (39) inside the turbomachine that communicates with a second inner chamber (40) delimited by the turbine (24) rotor (23), the first and second chambers (39, 40) being at least partially separated by a stationary shroud (56) of axis (A), characterised in that it comprises at least one injector (58) passing through the stationary shroud (56) and having a cross-section that varies in response to a pressure difference between said first and second chambers (39, 40).

A sleeve valve includes an inlet port and an outlet port. A sleeve is movable to close flow from the inlet port to the outlet port. The sleeve valve has a sleeve biased to an open position at which it allows flow from the inlet port to the outlet port by a spring. Pressure in a pressure chamber urges the sleeve to a closed position at which it blocks flow from the inlet port to the outlet port. A line pressure conduit communicates the fluid chamber into the pressure chamber. Pressurized air is supplied to the pressure chamber through a selectively closed valve. The selectively closed valve is opened to allow the flow of high pressure air from a pressure source into the pressure chamber to move the sleeve to a closed position. A bleed air system for a gas turbine engine is also disclosed.

A pressure regulating valve assembly includes: a valve having an upstream side receiving an input flow and a downstream side providing an output flow, an actuator for opening and closing the valve, including partially opening the valve, and a regulator controlling the actuator to open, close or partially open the valve. The regulator includes a sense pressure port, wherein pressure at the port is maintained constant by the regulator. A chamber has a first entry orifice, a second entry orifice and an exit orifice. The first entry orifice is connected to the upstream side, the second entry orifice is connected to the downstream side, and the exit orifice is connected to the port. The exit orifice provides that the pressure at the exit orifice lies between the pressure at the first entry orifice and the pressure at the second entry orifice.

A pin member is proposed for a turbo-machine having a shroud arranged to rotate within a turbine housing. The pin member is configured to limit this rotation. It is a one-piece element comprising a cylindrical body and a limit surface for opposing motion of the shroud.

A valve assembly for a turbine engine includes a valve arranged in an air flow path. The valve has a shaft. The valve is movable between an open position and a closed position. An electric actuator is coupled to the shaft and is configured to move the valve between the open position and the closed position. A thermal barrier is arranged between the valve and the electric actuator.

A compressed air-driven tool having an electromagnetically operated control element (27) for controlling a pneumatic control circuit in order to maintain a load-independent torque at a constant rotational speed. The tool includes a principal valve (5), which arranged in a drive housing (1) in a manner displaceable by the supplied compressed air against the force of a helical spring (13), and a generator (43), which is mounted on the shaft (49) of a turbine wheel (51). The rotational speed of the shaft (49) is measured with a speed sensor (75) and the supply of compressed air to the principal valve (5) is controlled in the event of a drop in rotational speed as a consequence of a load.

A turbomachine module with a longitudinal axis comprising an unducted propeller rotated about the longitudinal axis and at least one straightener. The module includes a plurality of unducted variable-pitch stator blades extending along a radial axis, perpendicular to the longitudinal axis, from a fixed casing. The module includes a first stator blade pitch-changing system. The pitch-changing system includes at least one first control that includes a first fixed body connected to the fixed casing and a first body which is axially mobile in relation to the first fixed body and at least one first joining mechanism joining each stator blade to the first mobile body of the first control. The first joining mechanism includes: a joining ring centered on the longitudinal axis, joined to the feet of each stator blade and at least one lever joined, on one hand, to the joining ring and, on the other hand, to the first mobile body of the first control.

An aircraft turbomachine module comprising a ventilation device configured to have a cooling air flow circulate in the turbomachine module, the ventilation device comprising an air outlet, blocking means fixed to the air outlet and mobile between a blocking position of the air outlet and an opening position of the air outlet, and locking means configured to maintain the blocking means in one of the blocking position and the opening position when the temperature within the module is less than a predetermined threshold value, the blocking means being configured to adopt the other of the blocking position and the opening position when the temperature within the module is greater than said predetermined threshold value.

A turbofan engine has a primary duct , in which there flows a primary flow at a primary pressure and a secondary duct, which radially surrounds the primary duct and in which there flows a secondary flow at a secondary pressure. The primary duct includes at least one compressor configured to compress the primary flow , a turbine driving the compressor in rotation and a combustion chamber designed to receive, at an inlet, the primary air flow compressed by the compressor The turbomachine further includes a cooling circuit extending between the compressor and the turbine.The cooling circuit has an air flow rate regulating device arranged upstream of the turbine and having at least one valve that is configured to move between an open position and a closed position, located between the compressor and the combustion chamber in the primary duct and the pressure (PS) in the secondary duct.

A sleeve valve includes an inlet port and an outlet port. A sleeve is movable to close flow from the inlet port to the outlet port. The sleeve valve has a sleeve biased to an open position at which it allows flow from the inlet port to the outlet port by a spring. Pressure in a pressure chamber urges the sleeve to a closed position at which it blocks flow from the inlet port to the outlet port. A line pressure conduit communicates the fluid chamber into the pressure chamber. Pressurized air is supplied to the pressure chamber through a selectively closed valve. The selectively closed valve is opened to allow the flow of high pressure air from a pressure source into the pressure chamber to move the sleeve to a closed position. A bleed air system for a gas turbine engine is also disclosed.