A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

Aspects of the disclosure generally relate to a turbine engine and method of operating, wherein a change in sealing status can be determined within a cavity between an outer casing and a rotor within the turbine engine. Aspects of the disclosure further relate to a supply of air to the cavity within the turbine engine.

A turbo generator rotor assembly is provided and includes a generator, first and second bearings on a compressor-side and a turbine-side of the generator and a combination seal configuration in which leakage from the compressor cools the first bearing, the generator and the second bearing. The combination seal configuration leads to minimal leakage past the turbine with the generator and the first and second bearings being cooled with leakage flow from the compressor.

The gas turbine engine can have a rotary shaft mounted to a casing via a bearing housed in a bearing housing, for rotation around a rotation axis, a gas path provided radially externally to the bearing housing, a feed pipe having a radial portion extending from an inlet end, radially inwardly across the gas path and then turning axially to an axial portion leading to an outlet configured to feed the bearing housing, the axial portion of the feed pipe broadening laterally toward the outlet.

The gas turbine engine can have a rotary shaft mounted to a casing via a bearing housed in a bearing housing, for rotation around a rotation axis, a gas path provided radially externally to the bearing housing, a feed pipe having a radial portion extending from an inlet end, radially inwardly across the gas path and then turning axially to an axial portion leading to an outlet configured to feed the bearing housing, the axial portion of the feed pipe broadening laterally toward the outlet.

A stator vane (3) for a turbine (50c) of a turbomachine (50), the stator vane having a stator vane airfoil (3c), an inner shroud (3a) and an outer shroud (3b), the inner shroud (3a) and the outer shroud (3b) bounding an annular space (2), in which working gas (51) is conveyed during operation, radially with respect to a longitudinal axis (52) of the turbomachine (50), and the stator vane airfoil (3c) having a stator vane airfoil channel (3d) extending through its interior between a radially inner inlet (6) and a radially outer outlet (7). A characteristic features is that the inlet (6) is disposed in such a manner that a gas (8) flowing through the stator vane airfoil channel (3d) during operation is at least partially formed of the working gas (51) conveyed in the annular space (2), and thus the working gas is redistributed from radially inward to radially outward.

Sealing gas systems and related methods are provided. The sealing gas system includes a machine having a first end, a bearing carrier, and a shaft seal vent, wherein the machine receives a sealing gas flow; and at least one processor, wherein the at least one processor includes or is in communication with a temperature controller for detecting a temperature of a vent gas flow at the shaft seal vent; wherein the at least one processor and/or the temperature controller are configured to detect a process gas flow through the shaft seal vent based on the detected temperature of the vent gas flow at the shaft seal vent.

Sealing gas systems and related methods are provided. The sealing gas system includes a machine having a first end, a bearing carrier, and a shaft seal vent, wherein the machine receives a sealing gas flow; and at least one processor, wherein the at least one processor includes or is in communication with a temperature controller for detecting a temperature of a vent gas flow at the shaft seal vent; wherein the at least one processor and/or the temperature controller are configured to detect a process gas flow through the shaft seal vent based on the detected temperature of the vent gas flow at the shaft seal vent.

A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.

A seal gas supply control method according to the present invention comprises a step for detecting a pressure difference between an internal pressure of a rotary machine and a supply pressure of a seal gas with respect to a dry gas seal portion, a step for adjusting an opening degree of a seal gas supply valve on the basis of the detected pressure difference between the internal pressure and the supply pressure, and a step for detecting a vent pressure for discharging the seal gas evacuated from the dry gas seal portion to the outside. The seal gas supply control method fully opens the seal gas supply valve when the detected vent pressure satisfies a predetermined condition.