An aspect of the present disclosure is directed to a seal assembly for a turbo machine. The seal assembly includes a fluid bearing wall including a bearing face in which the bearing face defines a fluid opening through the fluid bearing wall. The seal assembly further includes a seal body extended circumferentially relative to a centerline axis. The seal body defines a cavity extended at least partially circumferentially through the seal body. A fluid passage is defined through the seal body in fluid communication with the fluid opening through the fluid bearing wall.

Provided is a stationary nozzle assembly of a gas turbine including a plurality of vane segments converting hot gas energy into a kinetic form, a fixed seal disposed between two adjacent vane segments, and honeycomb seal elements disposed between the two adjacent vane segments to prevent hot gases from escaping through a gap between the two adjacent vane segments. Here, the fixed seal and the honeycomb seal elements face each other. In addition, the vane segments each include airfoil shaped vanes, an outer wall and an inner wall that are disposed at opposite sides of the airfoil shaped vanes, and the fixed seal and the honeycomb seal elements are installed in at least one of the outer wall or the inner wall.

A method for reducing the leakage of an organic working fluid operating within a turbine (10) of an Organic Rankine Cycle system, the method comprising the injection of a fluid flow rate (Q) into a volume (I) at a static pressure lower than the total pressure (P1) upstream of the turbine and located near of at least one labyrinth seal (L1, L11) of at least one stage of the turbine (10), said fluid flow rate (Q) having an initial exergetic content lower than the initial exergetic content of the organic working fluid located inside the turbine and flowing through said labyrinth seal (L1, L11).

A method for reducing the leakage of an organic working fluid operating within a turbine (10) of an Organic Rankine Cycle system, the method comprising the injection of a fluid flow rate (Q) into a volume (I) at a static pressure lower than the total pressure (P1) upstream of the turbine and located near of at least one labyrinth seal (L1, L11) of at least one stage of the turbine (10), said fluid flow rate (Q) having an initial exergetic content lower than the initial exergetic content of the organic working fluid located inside the turbine and flowing through said labyrinth seal (L1, L11).

This disclosure relates to a buffer system for a gas turbine engine. An exemplary gas turbine engine includes, among other features, a buffer manifold in an intershaft region. The buffer manifold is configured to direct a flow of air between a first air seal and a first oil seal, and to direct another flow of air between a second air seal and a second oil seal.

A turbine interstage structure for a gas turbine engine that includes a first stage disk and a second stage disk. A central plenum is defined by a an inner band for supporting nozzle vanes, a forward stator plate and an aft stator plate wherein the forward stator plate is spaced-apart from the aft stator plate, and an inner boundary. A forward mid-seal positioned between the inner boundary and the forward stator plate. An aft mid-seal positioned between the inner boundary and the aft stator plate; and wherein the inner boundary is a solid annular component.

A turbine interstage structure for a gas turbine engine that includes a first stage disk and a second stage disk. A central plenum is defined by a an inner band for supporting nozzle vanes, a forward stator plate and an aft stator plate wherein the forward stator plate is spaced-apart from the aft stator plate, and an inner boundary. A forward mid-seal positioned between the inner boundary and the forward stator plate. An aft mid-seal positioned between the inner boundary and the aft stator plate; and wherein the inner boundary is a solid annular component.

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 gas turbine unit having a combustor having a liner, a turbine, arranged downstream of the liner along a main flow gas direction and including a plurality of first stage vanes, a rotor cover support located inwardly of the vanes, and a sealing arrangement at a combustor to turbine interface, wherein the sealing arrangement includes a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner or between the rotor cover support and a bulkhead located at the inner downstream end of the liner.