A gas turbine engine includes, among other things, a propulsor section including a propulsor hub, the hub including a hub diameter supporting a plurality of propulsor blades. A compressor section includes a first compressor and a second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture interconnects the first turbine and the propulsor hub. The geared architecture includes a gear volume. A compressor inlet passage is disposed annularly about the geared architecture.

A bypass valve assembly for a turbine generator includes a valve body, bypass seats, valve stem, valve cap, bypass valve disc, bypass valves, and pressure seal head. The valve body defines a central bore and a plurality of passageways. Each passageway has an inlet smaller than its outlet. Each bypass seat is within the inlet of a corresponding passageway. The bypass seats have a higher wear resistance than the valve body. The valve stem is within the central bore. The valve cap is secured to the valve body. The bypass valve disc is secured to the valve stem. Each bypass valve has a base portion and a nose portion. Each nose portion defines a contoured surface area with a wear coating and extends into a corresponding passageway. The pressure seal head is disposed around the valve stem and defines steps having a wear coating.

An exhaust gas turbocharger assembly includes a turbocharger, an actuator, and a bolted connection for releasably securing the actuator housing on a housing flange of the turbocharger housing. The bolted connection includes a through opening, an aperture bounded at the circumference by an internal thread made of a metal, and a fit bolt with a bolt body which merges axially into a bolt head. The bolt body has a first axial body section with an external thread formed in a manner complementary to the internal thread of the aperture, and a second axial body section arranged axially between the bolt head and the first body section. The fit bolt engages through the through opening of the actuator housing in the internal thread of the aperture with the external thread to clamp the actuator housing between the housing flange of the turbocharger housing and the bolt head of the fit bolt.

The present invention relates to a valve arrangement (100) for a multi-channel turbine (10), having a housing section (300) with a first volute (320), with a second volute (340) and with a connecting region (360) between the first volute (320) and the second volute (340), and having a valve body (110) for closing off the connecting region (360) in a closed position of the valve body (110). A wall region (370) of the housing section (300), which wall region is arranged in the connecting region (360) and is situated opposite the valve body (110) in the closed position, is configured to be optimized in terms of flow to increase, during operation of the valve arrangement (100), a rate of flow transfer of exhaust gas between the first volute (320) and the second volute (340) in an open position of the valve body (110).

A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.

The invention relates to a bypass turbomachine (2) for an aircraft, comprising a gas generator (5) and a ducted fan (4) comprising variable pitch blades (18) configured to take a reverse thrust position driving a reverse flow (24) of air within a secondary duct (16), the gas generator (5) being connected to a fan casing (3) by a stator blade assembly (40) that passes through the secondary duct, first openings (28) for letting in air from the reverse flow being located on an outer casing (17) at least partially internally delimiting the outer duct, and second openings (29) for letting said air out being located on an inner casing (14) at least partially externally delimiting an inner duct (12). The first openings are located within a plane that is perpendicular to a longitudinal axis (C) of the turbomachine and passes substantially through the middle of the blade assembly.

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 compressor bleed apparatus includes: a compressor comprising one or more rotors mounted for rotation about a central axis and enclosed in a compressor casing; a bleed slot passing through the compressor casing; an outer wall defining, in cooperation with the compressor casing, a plenum surrounding the compressor casing; at least one offtake pipe communicating with the plenum; and wherein at least one of the plenum and the bleed slot has a non-axisymmetric structure.

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.