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.

A gas turbine engine with a compressor supplying compressed air. A combustor receives the compressed air and fuel and generates a flow of combusted gas. A turbine receives a core flow of the combusted gas to rotate a turbine rotor. A turbine inlet nozzle directs the combusted gas to the turbine rotor. Vanes are disposed in the turbine inlet nozzle and rotate to vary a flow area through which the core flow passes. The vanes adjust a pressure ratio of the gas turbine engine to compensate for changing operational requirements of the gas turbine engine by rotating to positions matching the changing operational requirements.

A gas turbine engine with a compressor supplying compressed air. A combustor receives the compressed air and fuel and generates a flow of combusted gas. A turbine receives a core flow of the combusted gas to rotate a turbine rotor. A turbine inlet nozzle directs the combusted gas to the turbine rotor. Vanes are disposed in the turbine inlet nozzle and rotate to vary a flow area through which the core flow passes. The vanes adjust a pressure ratio of the gas turbine engine to compensate for changing operational requirements of the gas turbine engine by rotating to positions matching the changing operational requirements.

A gas turbine engine may include a fan, a plurality of inlet pre-swirl features disposed upstream of a fan, and an outlet guide vane assembly disposed downstream of the fan. The outlet guide vane assembly includes a plurality of outlet guide vanes that may define an outlet guide vane solidity profile, wherein the outlet guide vane solidity profile is achieves a minimum solidity at a radial position between an inner boundary and seventy percent of an outlet guide vane span. The fan includes a plurality of fan blades that may define a fan solidity profile, wherein the fan solidity profile maintains a solidity of greater than 1.1 between a radial position at seventy percent of the fan blade span and an outer boundary.

A gas turbine engine may include a fan, a plurality of inlet pre-swirl features disposed upstream of a fan, and an outlet guide vane assembly disposed downstream of the fan. The outlet guide vane assembly includes a plurality of outlet guide vanes that may define an outlet guide vane solidity profile, wherein the outlet guide vane solidity profile is achieves a minimum solidity at a radial position between an inner boundary and seventy percent of an outlet guide vane span. The fan includes a plurality of fan blades that may define a fan solidity profile, wherein the fan solidity profile maintains a solidity of greater than 1.1 between a radial position at seventy percent of the fan blade span and an outer boundary.

A variable geometry turbine comprising: a wheel supported for rotation about an axis; a housing comprising a first volute for receiving gas from a first source and a second volute for receiving gas from a second source; the first and second volutes being separated by a dividing wall; and an inlet passageway surrounding the wheel and fluidly connected to the volutes; the inlet passageway at least partially defined between a first wall and an opposite second wall, the first wall being moveable along the axis to vary the size of the inlet passageway; wherein a tip of the dividing wall defines a first radius relative to the axis, and a radially outermost part of the first wall positioned within the inlet passageway defines a second radius relative to the axis, and wherein the first radius is at least around 1% larger than the second radius.

A control ring for controlling discharge gates for an aircraft turbine engine extends around a casing of the turbine engine and includes a connector for connecting to the gates. The control ring includes metal sectors and composite material sectors. The metal sectors may be connected to one another by the composite material sectors and the connector may be carried by the metal sectors.

A control ring for controlling discharge gates for an aircraft turbine engine extends around a casing of the turbine engine and includes a connector for connecting to the gates. The control ring includes metal sectors and composite material sectors. The metal sectors may be connected to one another by the composite material sectors and the connector may be carried by the metal sectors.

A turbocharger includes a turbine housing including an interior surface defining a turbine housing interior. The interior surface extends between a turbine housing inlet and a turbine housing outlet. The turbine housing also includes a wastegate duct disposed downstream of the turbine housing inlet and defining a wastegate channel. The turbocharger also includes a valve seat disposed about the wastegate channel, with the valve seat having a valve seat plane extending along the valve seat. The turbocharger further includes a wastegate assembly including a valve element engageable with the valve seat. The wastegate channel extends along a channel axis, and the channel axis is obliquely oriented with respect to the valve seat plane such that the wastegate channel and the valve element are configured to direct exhaust gas to a catalytic converter.