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 turbine comprising: a turbine housing, a wastegate passage connecting the turbine inlet and the turbine outlet; and a wastegate valve comprising a movable valve member. The wastegate valve has an open state in which a first gas may pass between a turbine inlet a turbine outlet via the wastegate passage and a closed state in which the valve member substantially prevents said first gas from passing between the turbine inlet and the turbine outlet. The valve member is mounted to an actuation member that passes through a bore of the turbine housing. The actuation member is movable to move the wastegate valve between the open and closed states. The turbine comprises a fluid conduit configured to deliver a second gas to the bore to form a fluidic seal between the bore and the actuation member to substantially prevent the passage of said first gas along the bore.

A ram air turbine release system including a turbine defining a rotational axis including at least one notch therein for receiving a plunger to prevent rotation of the turbine mechanically by moving between a first position and a second position, and a first bearing system contacting at least a portion of an outer surface of the plunger configured to reduce friction produced when the plunder moves between the first positon and the second position.

An assembly is provided for an aircraft propulsion system. This assembly includes a thrust reverser system. The thrust reverser system includes a cavity, a sleeve and a turning door. The sleeve is configured to translate along a centerline between a sleeve stowed position and a sleeve deployed position. The turning door is configured to move between a turning door stowed position and a turning door deployed position. The turning door is disposed within the cavity when the sleeve is disposed in the sleeve stowed position. The turning door projects in a radial outward direction away from the sleeve and the centerline when the sleeve is in the sleeve deployed position.

A variable nozzle device includes: a nozzle mount; a plurality of nozzle vanes; a drive ring being having a plurality of receiving portions disposed at different positions along a circumferential direction; and a plurality of lever plates each having a fixed portion to be fixed to corresponding one of the plurality of nozzle vanes and an engaging portion to be engaged with corresponding one of the plurality of receiving portions of the drive ring. The receiving portions include a first-side guide surface and a second-side guide surface. The engaging portions each include a first-side roll surface which is to be in contact with the first-side guide surface and a second-side roll surface which is to be in contact with the second-side guide surface. The first-side roll surface includes a lever-plate-side linear portion extending linearly in at least a part of a range which is to be in contact with the first-side guide surface. The first-side guide surface includes a drive-ring-side protruding curved surface portion extending in a protruding curve shape in at least a part of a range which is to be in contact with the first-side roll surface.

An adjustment lever adjusts a stator vane of a turbomachine. The adjustment lever has: a first connection site, of a plurality of connection sites, the first connection site being configured to join to an adjustment ring; a second connection site, of the connection sites, the second connection stie being configured to join to the stator vane; and a joining member arranged between the first connection site and the second connection site. The joining member is shaped having at least two struts which adjoin at least one of the connection sites.

A cold regulating valve for a heat exchanger system of an aircraft propulsion system, where the cold regulating valve includes an open frame which delimits an opening, two shutters with an external convex shape slidably mounted on the open frame between a closed position and an open position, a mechanism linked to the shutters and mobile between a first position and a second position, and wherein the mechanism moves the shutters from the closed position to the open position when it moves from the first position to the second position and vice versa, and an actuator acting on the mechanism to move it from the first position to the second position and vice versa. The specific embodiment of the cold regulating valve generates a low drag when the shutters are in a closed position.

A thrust reverser may comprise translating sleeve panel. A first articulating slider and a second articulating slider may be located at a circumferential end of the translating sleeve panel. Each of the first articulating slider and the second articulating slider may include a slider bar and a slider ball. The slider ball may be attached to the translating sleeve panel and located in a spherical opening defined by the slider bar.

A variable area nozzle assembly for a gas turbine engine includes a fixed structure including a first fixed ring and a second fixed ring. The second fixed ring is spaced axially aft from the first fixed ring to define a first portion of an ejector passage therebetween. A nozzle defines an inner radial exhaust flow path surface. The nozzle includes a forward ejector door and an aft ejector door. The forward ejector door and the aft ejector door define a first surface portion of the inner radial exhaust flow path surface. Each of the forward ejector door and the aft ejector door are pivotable between respective closed positions and respective open positions. A translating ejector sleeve is mounted within the fixed structure and configured to axially translate within the fixed structure between a first axial position and a second axial position.

A bushing apparatus includes: a housing with first and second ends, the housing having an outer bore passing therethrough from the first end to the second end, wherein the bore includes a reduced-diameter band located between the first and second ends; and a bushing received in the outer bore, the bushing having first and second ends and an inner bore passing therethrough from the first end to the second end of the bushing, wherein the bushing includes an outer surface having a reduced-diameter groove located between the first and second ends, wherein the band is received in the groove in a radially overlapping relationship, so as to block movement of the bushing relative to the housing.