A method and a turbine-compressor assembly of a system having an engine includes an upstream valve coupled with a compressor and a turbine-compressor device, a downstream valve coupled with a turbine and the device, and a controller to control the upstream, downstream, and a control valve. The controller selectively operates the device in a plurality of operating modes. In a turbine mode of operation, the upstream valve directs inlet air to the compressor, the turbine receives engine exhaust, the downstream valve directs first turbine exhaust from the turbine to the device, and the control valve directs second turbine exhaust from the device to an outlet. In a compressor mode of operation, the control valve directs the inlet air to the device, the upstream valve directs first compressed air from the device to the compressor, and the downstream valve directs the first turbine exhaust from the turbine to the outlet.

Methods and systems are provided for improving surge control in a boosted engine system configured with an electric motor to provide electrical boost assistance. Tip-in and tip-out surge are addressed by increasing the opening of a compressor recirculation valve and coordinating the recirculation valve opening with adjustments to an exhaust waste-gate position and a power output by the electric motor. The adjustments enable an intake airflow to be provided that operates the compressor outside a surge region while providing a target boost pressure as operator torque demand increases or decreases.

Methods and systems are provided for improving surge control in a boosted engine system configured with an electric motor to provide electrical boost assistance. Tip-in and tip-out surge are addressed by increasing the opening of a compressor recirculation valve and coordinating the recirculation valve opening with adjustments to an exhaust waste-gate position and a power output by the electric motor. The adjustments enable an intake airflow to be provided that operates the compressor outside a surge region while providing a target boost pressure as operator torque demand increases or decreases.

A rotation adjusting device is controlled such that an engine speed rising rate at the time of acceleration request is made smaller when a turbocharging pressure is lower than the turbocharging pressure is higher. Therefore, an engine speed can be increased at such a low speed that a rising delay in the turbocharging pressure hardly occurs, in a low turbocharging pressure region. Further, when the rotation adjusting device is controlled such that the engine speed rising rate at the time of the acceleration request is set to a value corresponding to the turbocharging pressure, an MG2 torque is controlled to compensate for an insufficient drive torque of an actual engine torque for a request engine torque. Therefore, even when the engine torque is increased slowly by increasing the engine speed at a slow speed, the insufficient drive torque is compensated for by the MG2 torque.

A rotation adjusting device is controlled such that an engine speed rising rate at the time of acceleration request is made smaller when a turbocharging pressure is lower than the turbocharging pressure is higher. Therefore, an engine speed can be increased at such a low speed that a rising delay in the turbocharging pressure hardly occurs, in a low turbocharging pressure region. Further, when the rotation adjusting device is controlled such that the engine speed rising rate at the time of the acceleration request is set to a value corresponding to the turbocharging pressure, an MG2 torque is controlled to compensate for an insufficient drive torque of an actual engine torque for a request engine torque. Therefore, even when the engine torque is increased slowly by increasing the engine speed at a slow speed, the insufficient drive torque is compensated for by the MG2 torque.

A high altitude air start equipment for an aircraft reciprocating engine includes: a compressor configured to suck and compress air, and supply the compressed air to the aircraft reciprocating engine; and a motor configured to supply the compressed air to the reciprocating engine to restart the reciprocating engine or to restore output by outputting rotational power to the compressor when the reciprocating engine stops or malfunctions during flight of the aircraft.

A high altitude air start equipment for an aircraft reciprocating engine includes: a compressor configured to suck and compress air, and supply the compressed air to the aircraft reciprocating engine; and a motor configured to supply the compressed air to the reciprocating engine to restart the reciprocating engine or to restore output by outputting rotational power to the compressor when the reciprocating engine stops or malfunctions during flight of the aircraft.

A method is described for operating an electric media-flow machine for a compressor and/or a turbine, especially for an exhaust-gas turbocharger of an internal combustion engine, having a shaft rotationally mounted in a housing that has an inlet and an outlet for a medium to be conveyed, a rotor being disposed in rotatably fixed manner on the shaft, having a stator that is fixed in the housing and has at least one polyphase drive winding as well as a plurality of stator teeth projecting radially to the inside, having a covering cap that covers the rotor upstream and to which an inner sleeve is joined surrounding the rotor circumferentially. An outer sleeve is disposed coaxially relative to the inner sleeve, the inner sleeve and the outer sleeve being fixed in the housing, and the stator teeth extending through the outer sleeve at least up to the inner sleeve.

A method is described for operating an electric media-flow machine for a compressor and/or a turbine, especially for an exhaust-gas turbocharger of an internal combustion engine, having a shaft rotationally mounted in a housing that has an inlet and an outlet for a medium to be conveyed, a rotor being disposed in rotatably fixed manner on the shaft, having a stator that is fixed in the housing and has at least one polyphase drive winding as well as a plurality of stator teeth projecting radially to the inside, having a covering cap that covers the rotor upstream and to which an inner sleeve is joined surrounding the rotor circumferentially. An outer sleeve is disposed coaxially relative to the inner sleeve, the inner sleeve and the outer sleeve being fixed in the housing, and the stator teeth extending through the outer sleeve at least up to the inner sleeve.

A control valve assembly for an engine system having a turbocharger system. The control valve is configured to control the position of a turbine actuator and a compressor actuator by directing hydraulic fluid into the proper passages. The control valve assembly includes a hydraulic powered bypass valve that, when energized, can reduce flow restriction of the hydraulic fluid, and can increase the speed of actuation of the turbine actuator.