At least one of a variable turbine geometry and a variable compressor geometry for an exhaust gas turbocharger may include a housing including a first housing wall and a blade bearing ring having at least one guide blade rotatably mounted thereon. A control lever may be included for adjusting the at least one guide blade between a closing position and an opening position. An actuating shaft may be connected to the control lever in a rotationally fixed manner along a rotation axis. The actuating shaft may be rotatably mounted on the housing via a passage opening disposed in the first housing wall. The actuating shaft may directly support itself on the first housing wall in the passage opening.

An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

A turbocharger turbine having housing walls defining a diffuser. Within the diffuser, a center body within the diffuser is supported by de-swirl vanes extending from the diffuser wall. The center body forms a de-swirl passageway having an increasing mean diameter of flow from an upstream end of the center body to a leading edge of the de-swirl vanes. A trailing edge of the de-swirl vanes is near the downstream end of the center body. Annular-type guide vanes surround the center body within the de-swirl passageway. A wastegate system is configured to vent wastegate flow into the diffuser through injection ports on the de-swirl vanes, annular guide vanes and/or center body.

A turbocharger turbine having housing walls defining a diffuser. Within the diffuser, a center body within the diffuser is supported by de-swirl vanes extending from the diffuser wall. The center body forms a de-swirl passageway having an increasing mean diameter of flow from an upstream end of the center body to a leading edge of the de-swirl vanes. A trailing edge of the de-swirl vanes is near the downstream end of the center body. Annular-type guide vanes surround the center body within the de-swirl passageway. A wastegate system is configured to vent wastegate flow into the diffuser through injection ports on the de-swirl vanes, annular guide vanes and/or center body.

A propulsion assembly for a motor vehicle with an internal combustion engine comprising at least one movable member, a turbocharger comprising a turbine adapted to expand exhaust gases to generate work and a first compressor adapted to compress air by means of the work generated by the turbine, an intake line connecting an outlet of the first compressor to an intake manifold of said engine to supply compressed air from the first compressor to said engine, wherein the intake line comprises a second compressor, which in turn comprises a compressor shaft rotatable about a first axis and is configured to further compress the compressed air from the first compressor via a rotation of the compressor shaft. The propulsion assembly further comprises mechanical transmission means configured to couple the movable member to the compressor shaft, thereby determining a transmission of motion from the movable member to the compressor shaft.

The present invention discloses a two-dimensional engine, including a driving device, a two-dimensional gas compressor, a gas outlet pipe, a refueling device, a safety device, an electric ignition device, an axial-flow gas compressor, and a crank connecting rod mechanism, wherein the electric ignition device is arranged on a left side of the gas outlet pipe; the crank connecting rod mechanism is arranged below the gas outlet pipe; the driving device includes a first motor, a first gear, a first dowel bar and a first rack that is arranged on the first dowel bar; the first rack is meshed with the first gear; and the two-dimensional gas compressor includes an upper pressure plate, a first cylindrical plate, a second cylindrical plate, a fixing rod, a first pressure-bearing plate, a second pressure-bearing plate and a shell. The present invention has the beneficial effects of simple structure and relatively high energy utilization rate.

The present invention relates to a heat shield (100) for a supercharging device (1), comprising a first ring portion (110), which is situated at the outside in a radial direction (24) and which is designed to bear the heat shield (100), and a second ring portion (120), which is situated at the inside in a radial direction (24) and which extends from the first ring portion (110). The second ring portion (120) has at least one structure-stiffening feature (200), the at least one structure-stiffening feature (200) being of bead-like form.

The present invention relates to a heat shield (100) for a supercharging device (1), comprising a first ring portion (110), which is situated at the outside in a radial direction (24) and which is designed to bear the heat shield (100), and a second ring portion (120), which is situated at the inside in a radial direction (24) and which extends from the first ring portion (110). The second ring portion (120) has at least one structure-stiffening feature (200), the at least one structure-stiffening feature (200) being of bead-like form.

A turbomachine includes a fluid compressor section with a compressor wheel supported on a shaft and a compressor housing that houses the compressor wheel for rotation therein about an axis of rotation. The turbomachine also includes an e-machine section with an e-machine operatively connected to the shaft and configured to convert energy between the e-machine and the shaft as the shaft rotates. The e-machine section includes an e-machine housing that houses at least part of the e-machine. The turbomachine further includes a coolant jacket that is defined at least partly in the e-machine housing. The coolant jacket is configured to receive a fluid coolant flow therein for cooling the e-machine. Also, the turbomachine includes a turbulator insert member that is removably received within the coolant jacket and that sub-divides the coolant jacket for directing the fluid coolant flow through the coolant jacket.