A gear box assembly for an engine, having a gear box for transmitting a torque, at least one first, static part, at least one second, rotating part, which is mounted so as to be rotatable relative to the first, static part and on which at least one element of the gear box is provided, and a conduit system for conveying a fluid to elements of the gear box,
wherein the conduit system has at least one first supply line and one second supply line for supplying fluid to at least one element of the gear box.

A leakage recovery facility is provided, by means of which at least a proportion of a leakage flow of fluid which originates from a first duct portion of the first supply line and which flows across at least one seal can be conducted to the second supply line.

The proposed solution relates to a gear box assembly for an engine, having a gear box for transmitting a torque, at least one first, static part, at least one second, rotating part, which is mounted so as to be rotatable relative to the first, static part and on which at least one element of the gear box is provided, and a conduit system for conveying a fluid to elements of the gear box.

A feed device of the conduit system on the first, static part has at least two separate fluid guides, of which a first fluid guide is provided for guiding fluid from at least one first feed opening to a first supply line in the second, rotating part and a second fluid guide is provided for guiding fluid from at least one second feed opening to a second supply line in the second, rotating part.

A turbomachine compressor module comprising an annular array of struts provided with pivotable flaps. The struts can define inter-strut spaces between two circumferentially adjacent struts, and variably oriented stator vanes are disposed at least partially in the inter-strut spaces. Also, a turbomachine having such a module and a row of rotor blades directly downstream of the module.

Centrifugal compressors can incorporate a side stream flow of intermediate pressure vapor between stages of that compressor. The side stream flow can be controlled by a side stream injection port controlled by a capacity control valve that has a curved surface facing a flow of refrigerant from the first stage to the second stage. The capacity control valve can allow or obstruct flow through the side stream injection port. The capacity control valve can extend and retract in a direction substantially perpendicular to the direction of flow from the first stage impeller to the second stage impeller. The side stream injection port and the capacity control valve can be ring-shaped. The side stream injection port and the capacity control valve can allow at least some of the side stream to be introduced on a side of the capacity control valve opposite the curved surface.

A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.

A radially flexible connection joint for a gas turbine engine includes an exhaust manifold flange operatively coupling an exhaust cylinder to an exhaust manifold of the gas turbine engine. The exhaust cylinder includes a cylindrical flange that extends radially outwardly from a rotation axis of the gas turbine. The cylindrical flange defines a downstream axial face. The exhaust manifold is positioned downstream from the exhaust cylinder. The exhaust manifold includes an upstream edge. The exhaust cylinder and the exhaust manifold are substantially coaxial with the rotation axis of the gas turbine. The exhaust manifold flange has a bellows portion that extends radially between the cylindrical flange of the exhaust cylinder and the upstream edge of the exhaust manifold. The bellows portion permits relative radial motion of the exhaust cylinder and the exhaust manifold.

An assembly for a fluid circuit of a turbine engineincludes a main branch, a fluid control valve, and a bypass branch which is arranged in parallel to the main branch. The fluid control valve includes a main outlet which is fluidly connected to the main branch and a bypass outlet which is fluidly connected to the bypass branch. The fluid control valve including a shutter, a spring for biasing the shutter, and control members for electrically controlling the shutter to a main open position or a bypass position. The spring for biasing the shutter is configured to bias the displacement of the shutter to the bypass position when a fluid pressure value is lower than a first threshold value.

A turbine nozzle for an aircraft turbine engine, the nozzle including at least one vane and a base having a platform. The nozzle is fitted with a passive system for reintroducing blow-by gas into the primary jet, the passive system including gas extraction ports on the base as well as gas reinjection ports on the radially outer surface of the platform and/or on a suction-side surface of the vanes, the gas reinjection ports being designed to redirect the gas flow in a reinjection direction having a circumferential orientation.

Variable geometry turbines having new configurations of vanes are disclosed. New methods for designing new configurations of vanes for geometry turbines having are also disclosed.

A turbocharger includes a bearing housing, a variable displacement mechanism, and a restricting member. The variable displacement mechanism includes a nozzle ring and a drive ring. The restricting member includes a flange part, a drive ring guide pin part, and a phase determining pin part. The flange part straddles a first surface of the nozzle ring facing the bearing housing and a second surface of the drive ring facing the bearing housing so that a position thereof with respect to the nozzle ring is fixed. The drive ring guide pin part is formed integrally with the flange part and disposed in a first hole formed on the first surface. The phase determining pin part is formed integrally with the flange part and disposed in a second hole formed on a third surface of the bearing housing facing the variable displacement mechanism.