A steam turbine having a cooling option, in which steam is taken from the flow channel, the steam cooling the thrust-compensating intermediate floor, being mixed with a small amount of live steam and being returned to the flow channel. A method cools the steam turbine, wherein steam is extracted from the high-pressure region and is fed to a space between the thrust-compensating partition wall and inner casing, wherein steam from the space between the thrust-compensating partition wall and the inner casing is fed via a first cross feedback passage to the high-pressure region.

A steam turbine having a cooling option, in which steam is taken from the flow channel, the steam cooling the thrust-compensating intermediate floor, being mixed with a small amount of live steam and being returned to the flow channel. A method cools the steam turbine, wherein steam is extracted from the high-pressure region and is fed to a space between the thrust-compensating partition wall and inner casing, wherein steam from the space between the thrust-compensating partition wall and the inner casing is fed via a first cross feedback passage to the high-pressure region.

Rotor thrust balancing systems for turbomachines and methods of using the same are generally disclosed. For example, a rotor thrust balancing system for a turbomachine, wherein the turbomachine defines a centerline extending the length of the turbomachine. The system includes a rotating drive shaft, a thrust bearing, and a first waveguide sensor. The rotating drive shaft couples a turbine section and a compressor section of the turbomachine. The thrust bearing supports the rotating drive shaft of the turbomachine. The thrust bearing includes a plurality of ball bearings, an inner race coupled to the rotating drive shaft, and an outer race coupled to a fixed structure. The first waveguide sensor is coupled to the outer race at a first end of the waveguide sensor. The waveguide sensor communicates a vibrational frequency from the thrust bearing to a second end of the waveguide sensor.

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.

The balancing system has a balancing body to be mounted on a rotor of a turbomachine and a sealing ring to be mounted on a stator of the turbomachine; the sealing ring is arranged around the balancing body so that the balancing body can rotate about a rotation axis, thus there is a clearance between the body and the ring; furthermore, there is an arrangement for changing an axial position of the sealing ring during operation of the turbomachine so that the clearance can be adjusted. The possibility of adjusting clearance during operation of the turbomachine, such balancing system provides a good balancing action with a small leakage and a small risk of mechanical interference at any time during operation of the turbomachine.

The balancing system has a balancing body to be mounted on a rotor of a turbomachine and a sealing ring to be mounted on a stator of the turbomachine; the sealing ring is arranged around the balancing body so that the balancing body can rotate about a rotation axis, thus there is a clearance between the body and the ring; furthermore, there is an arrangement for changing an axial position of the sealing ring during operation of the turbomachine so that the clearance can be adjusted. The possibility of adjusting clearance during operation of the turbomachine, such balancing system provides a good balancing action with a small leakage and a small risk of mechanical interference at any time during operation of the turbomachine.

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 gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the other of the aft direction and the forward direction in relation to the static component during a second operating condition of the gas turbine engine. The first operating condition is when a rotating component growth and a static component growth change at different rates. The second operating condition is when the rotating component growth and static component growth normalize.

A gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the other of the aft direction and the forward direction in relation to the static component during a second operating condition of the gas turbine engine. The first operating condition is when a rotating component growth and a static component growth change at different rates. The second operating condition is when the rotating component growth and static component growth normalize.