Abstract: A rotor assembly for a turbomachine having a permanent magnet electric motor that defines an axis of rotation includes a jacket member. The rotor assembly also includes a magnet member that is received within the jacket member. The magnet member has a first longitudinal end and a second longitudinal end that are separated along the axis of rotation. The rotor assembly also includes a first shaft structure that is attached to the first longitudinal end and a second shaft structure that is attached to the second longitudinal end.

Abstract: A rotor assembly for an electric motor for a turbomachine defines an axis of rotation. The rotor assembly includes a jacket member that is hollow and that defines an inner radial surface facing inwardly toward the axis of rotation. Furthermore, the rotor assembly includes a magnet member that is received within the jacket member. The magnet member includes an outer radial surface facing outwardly from the axis of rotation. The jacket member is made of a sintered composite material having carbon filament and a sintered matrix. Additionally, the inner radial surface of the jacket member abuts against the outer radial surface of the magnet member to retain the magnet member in a radial position relative to the axis.

Abstract: A turbine section of a turbomachine includes a housing that houses and supports the rotating group for rotation about an axis. The housing defines a circumferential inlet passage that extends about the axis. The housing defines a turbine wheel upstream area that is disposed downstream of the circumferential inlet passage and upstream of the turbine wheel. The housing defines an outlet that is downstream of the turbine wheel. Furthermore, the turbine section includes a first flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, across the turbine wheel, to the outlet. Moreover, the turbine section includes a recirculation flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, and back to the circumferential inlet passage.

Abstract: A compressor device includes a housing and a shaft supported for rotation within the housing. The compressor device includes a compressor section with a compressor wheel. Also, the compressor device includes a thrust suppression section with a chamber and a thrust balance body disposed within the chamber. Moreover, the compressor device includes a motor configured to drivingly rotate the shaft, the compressor wheel, and the thrust balance body. The thrust balance body divides the chamber into a first sub-chamber and a second sub-chamber. Additionally, the compressor device includes a bleed air system that fluidly connects the compressor section and the thrust suppression section. The bleed air system is configured to bleed air from the compressor section, through the first sub-chamber, to the second sub-chamber, pressurizing the first sub-chamber and generating a counterbalancing thrust load that counterbalances a compressor thrust load on the shaft.

Abstract: A rotor assembly for a permanent magnet electric motor defines an axis of rotation and includes a jacket member and a magnet member. The magnet member is received within the jacket member. The magnet member defines a central aperture with a first end and a second end. The axis of rotation extends through the first end and the second end. The rotor assembly further includes a shaft arrangement with a first shaft structure and a second shaft structure. The first shaft structure is received in the first end of the magnet member, and the second shaft structure is received in the second end of the magnet member. The first shaft structure and the second shaft structure are attached within the magnet member at an internal coupling. The shaft arrangement and the jacket member cooperate to compress the magnet member radially with respect to the axis of rotation.

Abstract: A rotor assembly for an electric motor for a turbomachine defines an axis of rotation. The rotor assembly includes a jacket member that is hollow and that defines an inner radial surface facing inwardly toward the axis of rotation. Furthermore, the rotor assembly includes a magnet member that is received within the jacket member. The magnet member includes an outer radial surface facing outwardly from the axis of rotation. The jacket member is made of a sintered composite material having carbon filament and a sintered matrix. Additionally, the inner radial surface of the jacket member abuts against the outer radial surface of the magnet member to retain the magnet member in a radial position relative to the axis.

Abstract: A turbine section of a turbomachine includes a housing that houses and supports the rotating group for rotation about an axis. The housing defines a circumferential inlet passage that extends about the axis. The housing defines a turbine wheel upstream area that is disposed downstream of the circumferential inlet passage and upstream of the turbine wheel. The housing defines an outlet that is downstream of the turbine wheel. Furthermore, the turbine section includes a first flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, across the turbine wheel, to the outlet. Moreover, the turbine section includes a recirculation flow path that extends from the circumferential inlet passage, through the turbine wheel upstream area, and back to the circumferential inlet passage.

Abstract: A rotor assembly for a permanent magnet electric motor defines an axis of rotation and includes a jacket member and a magnet member that is received within the jacket member. The magnet member defines a central aperture. The rotor assembly also includes a shaft structure with a base member and a biasing projection that projects from the base member. The biasing projection is received within the central aperture of the magnet member. The biasing projection biases the magnet member toward the jacket member in an outward radial direction away from the axis of rotation for retaining the magnet member and the jacket member together.

Abstract: A single-stage compressor device includes a housing and a rotating group with a shaft and a compressor wheel. The compressor wheel includes a front face and a back face. The front face cooperates with the housing to define a compressor flow path. A motor drives rotation of the rotating group within the housing. Furthermore, the compressor device includes a bleed system fluidly connected to the compressor flow path and configured to receive bleed fluid from the compressor flow path. The bleed system includes a bleed passage. At least a portion of the bleed passage is cooperatively defined by the back face of the compressor wheel and an opposing surface of the housing. The bleed system is configured to pass bleed air from the bleed passage, thereby alleviating thrust loading of the compressor wheel on the rotating group.

Abstract: A rotor assembly for a permanent magnet electric motor defines an axis of rotation and includes a jacket member and a magnet member. The magnet member is received within the jacket member. The magnet member defines a central aperture with a first end and a second end. The axis of rotation extends through the first end and the second end. The rotor assembly further includes a shaft arrangement with a first shaft structure and a second shaft structure. The first shaft structure is received in the first end of the magnet member, and the second shaft structure is received in the second end of the magnet member. The first shaft structure and the second shaft structure are attached within the magnet member at an internal coupling. The shaft arrangement and the jacket member cooperate to compress the magnet member radially with respect to the axis of rotation.

Abstract: A rotor assembly for a permanent magnet electric motor defines an axis of rotation and includes a jacket member and a magnet member that is received within the jacket member. The magnet member defines a central aperture. The rotor assembly also includes a shaft structure with a base member and a biasing projection that projects from the base member. The biasing projection is received within the central aperture of the magnet member. The biasing projection biases the magnet member toward the jacket member in an outward radial direction away from the axis of rotation for retaining the magnet member and the jacket member together.

Abstract: A single-stage compressor device includes a housing and a rotating group with a shaft and a compressor wheel. The compressor wheel includes a front face and a back face. The front face cooperates with the housing to define a compressor flow path. A motor drives rotation of the rotating group within the housing. Furthermore, the compressor device includes a bleed system fluidly connected to the compressor flow path and configured to receive bleed fluid from the compressor flow path. The bleed system includes a bleed passage. At least a portion of the bleed passage is cooperatively defined by the back face of the compressor wheel and an opposing surface of the housing. The bleed system is configured to pass bleed air from the bleed passage, thereby alleviating thrust loading of the compressor wheel on the rotating group.

Abstract: A compressor device includes a housing and a shaft supported for rotation within the housing. The compressor device includes a compressor section with a compressor wheel. Also, the compressor device includes a thrust suppression section with a chamber and a thrust balance body disposed within the chamber. Moreover, the compressor device includes a motor configured to drivingly rotate the shaft, the compressor wheel, and the thrust balance body. The thrust balance body divides the chamber into a first sub-chamber and a second sub-chamber. Additionally, the compressor device includes a bleed air system that fluidly connects the compressor section and the thrust suppression section. The bleed air system is configured to bleed air from the compressor section, through the first sub-chamber, to the second sub-chamber, pressurizing the first sub-chamber and generating a counterbalancing thrust load that counterbalances a compressor thrust load on the shaft.

Abstract: A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.

Abstract: A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming a pair of inwardly spiraling primary-scroll passageways that significantly converge to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.

Abstract: A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.

Abstract: A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.

Abstract: A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.

Abstract: A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.

Abstract: A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.