A drive system may include an internal combustion engine and an expander operated via a working medium. A force transmission device may be disposed between a crankcase and the expander. A first seal may be disposed between the expander and the force transmission device and/or a second seal may be disposed between the force transmission device and the crankcase. A crankcase ventilation line may lead from the crankcase into an intake pipe of the internal combustion engine. An air mass sensor may be disposed in the intake pipe. An engine control unit may be in communication with the air mass sensor, the expander, and the internal combustion engine and may be configured to detect a power of the internal combustion engine and an air mass flow of the air mass sensor and may switch off the expander if a power suddenly rises with the air mass flow remaining constant.

A drive system may include an internal combustion engine and an expander operated via a working medium. A force transmission device may be disposed between a crankcase and the expander. A first seal may be disposed between the expander and the force transmission device and/or a second seal may be disposed between the force transmission device and the crankcase. A crankcase ventilation line may lead from the crankcase into an intake pipe of the internal combustion engine. An air mass sensor may be disposed in the intake pipe. An engine control unit may be in communication with the air mass sensor, the expander, and the internal combustion engine and may be configured to detect a power of the internal combustion engine and an air mass flow of the air mass sensor and may switch off the expander if a power suddenly rises with the air mass flow remaining constant.

An oxidizing reactor apparatus having a heat exchange reactor having an input port, an entry channel in fluid communication with the input port, an exit channel in fluid communication with the entry channel via a plurality of pores and an output port in fluid communication with the exit channel, wherein the exit channel is in thermal communication with the entry channel, an engine in fluid communication with the heat exchange reactor and a heater engaged with the heat exchange reactor to initiate and maintain the oxidation of fuel within the heat exchange reactor. The disclosed heat exchange reactor may be configured to receive engine exhaust from the engine and oxidize fuel within the engine exhaust prior to expelling the engine exhaust. The heat exchange reactor may be further configured to utilize heat released by the oxidation of un-combusted fuel to increase the temperature of the engine exhaust leaving the engine.

An oxidizing reactor apparatus having a heat exchange reactor having an input port, an entry channel in fluid communication with the input port, an exit channel in fluid communication with the entry channel via a plurality of pores and an output port in fluid communication with the exit channel, wherein the exit channel is in thermal communication with the entry channel, an engine in fluid communication with the heat exchange reactor and a heater engaged with the heat exchange reactor to initiate and maintain the oxidation of fuel within the heat exchange reactor. The disclosed heat exchange reactor may be configured to receive engine exhaust from the engine and oxidize fuel within the engine exhaust prior to expelling the engine exhaust. The heat exchange reactor may be further configured to utilize heat released by the oxidation of un-combusted fuel to increase the temperature of the engine exhaust leaving the engine.

A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust.

A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust.

The present invention includes: a turbine wheel 24 that is attached to a rotating shaft 14 and that has a plurality of turbine blades in the circumferential direction; scroll passages 15Aa, 15Ab that are formed in a spiral shape on the outside of the turbine wheel 24, and that are formed by being divided into a plurality of sections in the circumferential direction, the passages communicating with each other at the position of the turbine wheel 24 disposed between respective tongue sections 15Ac, 15Ad; and threads 51 that are provided on an back facing surface 41 disposed so as to oppose the back surface of the turbine wheel 24, the back surface being on the axially opposite side from the turbine blade side, and the linear parts extending from starting points 51a near the tongue sections 15Ac, 15Ad toward the rotating shaft 14 side so as to control the passage of fluid between the back surface and the back facing surface 41.

A turbo-compressor comprises a compressor wheel having an attachment arrangement for attaching the wheel to a drive shaft. The attachment arrangement includes an axially extending spigot internally radially located in a bore in the drive shaft and secured to the drive shaft by fastening means into the rear of the compressor wheel. Thus the compressor wheel expands and tightens into the shaft at speed. Furthermore, the nose of the compressor wheel is free to accept an aerodynamic profile.

A turbo-compressor comprises a compressor wheel having an attachment arrangement for attaching the wheel to a drive shaft. The attachment arrangement includes an axially extending spigot internally radially located in a bore in the drive shaft and secured to the drive shaft by fastening means into the rear of the compressor wheel. Thus the compressor wheel expands and tightens into the shaft at speed. Furthermore, the nose of the compressor wheel is free to accept an aerodynamic profile.

A supercharger system for an engine having a turbocharger is provided. The supercharger system includes a supercharger driver and an air inlet. The supercharger system also includes a supercharger compressor mechanically coupled to the supercharger driver. The supercharger compressor includes a supercharger compressor inlet and a supercharger compressor outlet. The supercharger compressor inlet is in fluid communication with the air inlet. The supercharger compressor outlet is in fluid communication with a turbine inlet associated with the turbocharger.