The invention relates to an exhaust case (15) for a turbomachine extending along a longitudinal axis (X), comprising: an annular shroud (23) having a wall (24) extending along the longitudinal axis (X) from a first flange (25), a plurality of openings (27) being provided through the wall (24); a plurality of mouths (28) each forming a channel (29) extending upstream to downstream between a respective inlet (30) and one of the openings (27), each mouth (28) having: a docking flange (31) at the inlet (30) having a radially inner edge (32) which is in contact with the first flange (25) of the annular shroud (23), a mouth wall (34) delimiting the channel (29) and comprising a radially inner wall portion (35) which is formed by a thickened section made on the wall (24) of the shroud (23).

A regulating flap arrangement (1) of an exhaust-gas turbocharger (3) having a flap shaft (5), which is guided by means of a bushing (10) in the turbine housing (2). A shaped sealing ring (13), as viewed in cross section, has at least one cavity (14). The shaped sealing ring (13) bears simultaneously against the first sealing surface (11) and against the second sealing surface (12), and in order to impart its sealing action, is compressed and deformed in the axial direction (15) of the flap shaft (5).

A turbocharger actuator arrangement for a turbocharger includes a movable actuator operating lever, a control rod, and a wave spring. More specifically, the control rod is couplable to a setting element of the turbocharger and is connected to the actuator operating lever by means of a bolt such that the control rod is arranged to be rotatable relative to the actuator operating lever. The bolt extends from the actuator operating lever through an opening in an end region of the control rod and through the wave spring. As such, the control rod and the wave spring are arranged between the actuator operating lever and a bolt securing means, which is arranged at an end region of the bolt that is averted from the actuator operating lever.

A turbocharger for a motor vehicle has a housing and a valve seat in the housing. The valve seat is retained in an interlocking manner in the housing by at least one elastic securing element.

An in-line shutoff valve includes a valve body with an inlet chamber, an outlet chamber, and a poppet seat disposed between the inlet and outlet chambers. A poppet is movably disposed within the valve body and has an open and closed position. The poppet seats against the poppet seat in the closed position, fluidly separating the inlet chamber from the outlet chamber. The poppet is unseated from the poppet seat in the open position, fluidly coupling the inlet and outlet chambers. A manifold with a servo port and a vent port is disposed within the valve body between the inlet and outlet chambers, the vent port being in fluid communication with the servo port to cool valve internal structures when the poppet is in the closed position.

An air conditioning system for an aircraft is provided. The air conditioning system includes a first rotating component and a second rotating component. The first rotating component includes a compressor and a turbine. The compressor pressurizes a first medium. The first turbine receives a mixture of a second medium and a pressurized form of the first medium. The second rotating component includes a fan.

An airplane is provided. The airplane includes a first medium, a second medium, and an air conditioning. The air conditioning system includes a first turbine, a compressor, and a mixing point. The compressor is located upstream of the turbine in a flow path of the first medium. The mixing point is a location at which the first medium mixes with the second medium. The mixing point is downstream of the compressor and upstream of the turbine.

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

A gas turbine engine includes a blade track, a support assembly, and a seal system. The blade track is arranged around a central axis of the gas turbine engine to direct gasses through the gas turbine engine. The support assembly is arranged around the blade track to support the blade track relative to the central axis. The seal system is configured to block fluid communication between pressurized cavities formed in the support assembly.

A bleed valve has a valve body enclosing a valve chamber defining a passageway between an inlet port and an outlet port. A panel is mounted into the valve body. The panel is deflectable under fluid pressure between a sealing position blocking the passageway when the bleed valve is in a close state, and a bleeding position allowing fluid flow communication between the inlet port and the outlet port when the bleed valve is an open state. A pressure control device is provided to vary a fluid pressure differential between opposite sides of the panel within the valve chamber and selectively open or close the bleed valve.