A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembly further includes a plurality of seals in series, at least one seal of the plurality of seals is coupled between a static support member and a respective rotor stage such that a plurality of turbine cavities in series are defined within the wheelspace. Each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheel space.

A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool is also disclosed.

A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool is also disclosed.

This turbocharger (1A) is provided with: a rotating shaft (4); a turbine wheel (2); a compressor wheel (3); a bearing housing (6) provided with journal bearings (5A, 5B) for rotatably supporting a shaft (4), and a thrust bearing (8) for supporting the rotating shaft (4) in the center axis (C) direction thereof; and a turbine housing (31) in which the turbine wheel (2) is accommodated. A fluid supply section (70A) for supplying a fluid to the turbine wheel (2) is provided within the turbine housing (31) and said fluid presses the turbine wheel (2) toward a first end (4a) side.

The present invention relates to a radial turbomachine with axial thrust compensation, comprising: a fixed casing (3); a plurality of main concentric bladed rings (9,9,9,9) arranged in the fixed casing (3) around a central axis (X-X); a plurality of concentric auxiliary bladed rings (15, 15, 15) arranged in the fixed casing (3) around the central axis (X-X) and radially alternated with the main bladed rings (9,9,9,9). A rotor (2, 2) comprising a rotor disc (6, 6) and a rotation shaft (4, 4, 4) integral with the rotor disc (6, 6) is rotatable in the fixed casing (3) around the central axis (X-X) and carries, on a front face (7, 7), the main bladed rings (9,9,9,9). The main (9,9,9,9) and auxiliary (15, 15, 15) bladed rings delimit, with the rotor disc (6, 6), a plurality of concentric front main chambers (30, 33, 35, 36) at different pressures. A plurality of concentric rear annular main chambers (41,41,41,41), each in fluid communication with a respective front main chamber (30, 33, 35, 36) and at the same pressure as the respective front main chamber (30, 33, 35, 36), is delimited between a rear face (8, 8) of the rotor disc (6, 6) and the fixed casing (3). A rear annular area (A_1p, A_2p, A_3p, A_4p, A_4p) of the rotor disc (6, 6) delimiting one of the rear annular main chambers (41,41,41,41) is equal to or substantially equal to a front area (A_1f, A_2f, A_3f, A_4f) of the rotor disc (6, 6) delimiting a respective front main chamber (30, 33, 35, 36), so that the force exerted by the pressure of the working fluid in each rear annular main chamber (41,41,41,41) substantially balances the force exerted by the pressure of the working fluid in the respective front main chamber (30, 33, 35, 36).

An impeller for used in a fluid pump device includes a shaft controlled to revolve in a first direction; an impeller body coupled to the shaft and driven by the revolving shaft to rotate, the impeller body having a top surface, a bottom surface and a circumferential surface; a first set of fluid-guiding members disposed on the top surface of the impeller body for driving a fluid to flow along a centrifugal direction of the revolving shaft; and a second set of fluid-guiding members disposed on the circumferential surface of the impeller body. Each or at least one of the second set of fluid-guiding members has a titling structure for driving the fluid to flow from the top to the bottom of the impeller along a designated path on the circumferential surface.

A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter.

A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section, a shaft including a bearing system, a turbine section in communication with the shaft, a speed change mechanism coupling the fan section to the turbine section and a biasing device configured to apply a biasing force against the shaft.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section, a shaft including a bearing system, a turbine section in communication with the shaft, a speed change mechanism coupling the fan section to the turbine section and a biasing device configured to apply a biasing force against the shaft.