A small aero gas turbine engine with an axial thrust limiter device that uses compressed air acting on a rotating disk extending from a rotor of the engine in which a forward pressure chamber and an aft pressure chamber applies a pressure to both sides of the rotating disk. When rotor is shifted, one side of the rotating disk has an increase in pressure acting on it to shift the rotor in an axial direction. Each pressure chamber includes an upper variable restriction and a lower variable restriction in which the restriction varies due to axial movement of the rotor. A forward and an aft foil bearing can also be used in addition to axial balance the rotor when not enough pressure is available such as at engine startup.

Aspects of the invention disclosed herein generally provide a heat engine system, a turbopump system, and methods for lubricating a turbopump while generating energy. The systems and methods provide proper lubrication and cooling to turbomachinery components by controlling pressures applied to a thrust bearing in the turbopump. The applied pressure on the thrust bearing may be controlled by a turbopump back-pressure regulator valve adjusted to maintain proper pressures within bearing pockets disposed on two opposing surfaces of the thrust bearing. Pocket pressure ratios, such as a turbine-side pocket pressure ratio (P1) and a pump-side pocket pressure ratio (P2), may be monitored and adjusted by a process control system. In order to prevent damage to the thrust bearing, the systems and methods may utilize advanced control theory of sliding mode, the multi-variables of the pocket pressure ratios P1 and P2, and regulating the bearing fluid to maintain a supercritical state.

Aspects of the invention disclosed herein generally provide a heat engine system, a turbopump system, and methods for lubricating a turbopump while generating energy. The systems and methods provide proper lubrication and cooling to turbomachinery components by controlling pressures applied to a thrust bearing in the turbopump. The applied pressure on the thrust bearing may be controlled by a turbopump back-pressure regulator valve adjusted to maintain proper pressures within bearing pockets disposed on two opposing surfaces of the thrust bearing. Pocket pressure ratios, such as a turbine-side pocket pressure ratio (P1) and a pump-side pocket pressure ratio (P2), may be monitored and adjusted by a process control system. In order to prevent damage to the thrust bearing, the systems and methods may utilize advanced control theory of sliding mode, the multi-variables of the pocket pressure ratios P1 and P2, and regulating the bearing fluid to maintain a supercritical state.

An integrated turbomachine is described, comprising: a casing; an electric motor and a driven turbomachine component housed in the casing; a rotating shaft drivingly connecting the electric motor and the driven turbomachine component; a thrust bearing and a radial bearing rotatingly supporting the shaft; an axial locking device housed inside the casing, for applying a thrust to the shaft, parallel to the rotation axis (A-A) of the shaft, and comprised of an actuator member, configured to selectively activate and/or deactivate the axial locking device.

An integrated turbomachine is described, comprising: a casing; an electric motor and a driven turbomachine component housed in the casing; a rotating shaft drivingly connecting the electric motor and the driven turbomachine component; a thrust bearing and a radial bearing rotatingly supporting the shaft; an axial locking device housed inside the casing, for applying a thrust to the shaft, parallel to the rotation axis (A-A) of the shaft, and comprised of an actuator member, configured to selectively activate and/or deactivate the axial locking device.

A rotor rotatably mounted within a turbocharger housing includes a turbine wheel and a shaft. The shaft connects the turbine wheel. The hub defines a turbine-wheel back-disk surface facing the portion of the housing containing the bearings, and the hub defines a blade-side surface. The turbine hub and the housing define a turbine-wheel back-disk cavity. The turbine hub forms a ring-shaped primary axial protrusion extending circularly around the turbine-wheel back-disk surface into a circular channel in the housing. The circular channel leads into a bypass that bypasses the turbine blades. A relief flow valve is placed in the bypass. The relief control valve is controlled to open when the bypass pressure is above a cutoff pressure, and close when it is below the cutoff pressure.

A rotor rotatably mounted within a turbocharger housing includes a turbine wheel and a shaft. The shaft connects the turbine wheel. The hub defines a turbine-wheel back-disk surface facing the portion of the housing containing the bearings, and the hub defines a blade-side surface. The turbine hub and the housing define a turbine-wheel back-disk cavity. The turbine hub forms a ring-shaped primary axial protrusion extending circularly around the turbine-wheel back-disk surface into a circular channel in the housing. The circular channel leads into a bypass that bypasses the turbine blades. A relief flow valve is placed in the bypass. The relief control valve is controlled to open when the bypass pressure is above a cutoff pressure, and close when it is below the cutoff pressure.

The invention relates to a turbine (20) having an impeller (23) arranged in a housing (26). The turbine (20) has an inflow region (21) and an outflow region (22) and a working medium flows through said turbine during operation. The working medium flows into the inflow region (21), along a front side (23a) formed on the impeller (23) and subsequently out of the outflow region (22). There is a pressure drop at the front side (23a) between the inflow region (21) and the outflow region (22). A pressure distributer (9) is arranged on the rear side (23b) of the impeller (23), opposite the front side (23a). The pressure distributer (9) comprises a slide ring (31), which cooperates with the rear side (23b) of the impeller (23) and thereby forms a vapour-lubricated throttle. A first flow path (51) runs through the throttle, wherein the throttle hydraulically divides the rear side (23b) into a first region (231) and a second region (232). The first region (231) borders the inflow region (21), and the second region borders a pressure chamber (11). During operation, the inflow region (21) is applied with a higher pressure than the pressure chamber (11). The slide ring (31) is axially moveable. A sealing ring (33) arranged in a groove (41) cooperates with the slide ring (31). A second flow path (52) runs from the inflow region (21) to the pressure chamber (11) between the groove (41) and the slide ring (31). The second flow path (52) can be closed by the sealing ring (33). The sealing ring (33) can be moved in the groove (41) in a defined manner.

The invention relates to a turbine (20) having an impeller (23) arranged in a housing (26). The turbine (20) has an inflow region (21) and an outflow region (22) and a working medium flows through said turbine during operation. The working medium flows into the inflow region (21), along a front side (23a) formed on the impeller (23) and subsequently out of the outflow region (22). There is a pressure drop at the front side (23a) between the inflow region (21) and the outflow region (22). A pressure distributer (9) is arranged on the rear side (23b) of the impeller (23), opposite the front side (23a). The pressure distributer (9) comprises a slide ring (31), which cooperates with the rear side (23b) of the impeller (23) and thereby forms a vapour-lubricated throttle. A first flow path (51) runs through the throttle, wherein the throttle hydraulically divides the rear side (23b) into a first region (231) and a second region (232). The first region (231) borders the inflow region (21), and the second region borders a pressure chamber (11). During operation, the inflow region (21) is applied with a higher pressure than the pressure chamber (11). The slide ring (31) is axially moveable. A sealing ring (33) arranged in a groove (41) cooperates with the slide ring (31). A second flow path (52) runs from the inflow region (21) to the pressure chamber (11) between the groove (41) and the slide ring (31). The second flow path (52) can be closed by the sealing ring (33). The sealing ring (33) can be moved in the groove (41) in a defined manner.

A rotary machine, including: a rotor (2) extending in an axial direction, the rotor including a first thrust collar (35) and a second thrust collar (36) projecting radially outward; a first thrust bearing device (31) configured to receive load acting in the axial direction via the first thrust collar (35); a second thrust bearing device (32) configured to receive load acting in the axial direction via the second thrust collar (36); and a load control device (16) configured to control load acting on at least one of the first thrust bearing device (31) and the second thrust bearing device (32).