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 hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a radially outer beam operatively coupling the shoe to the base. The seal yet further includes a radially inner beam operatively coupling the shoe to the base, wherein one of the radially inner beam and the radially outer beam is oriented to be angled relative to the other of the radially inner and outer beam.

An assembly is provided for a turbine engine. This assembly includes a static structure and an impeller rotor housed within the static structure. The impeller rotor includes a vane structure and a shroud. The vane structure includes a first sidewall, a second sidewall and a plurality of vanes arranged circumferentially about a rotational axis. The vanes include a first vane. The first vane includes a first portion, a second portion and a third portion. The first portion is axially between the first sidewall and the second sidewall. The second portion is radially between the first sidewall and the shroud. The third portion is radially between the second sidewall and the shroud. The shroud circumscribes the vane structure. A gap is formed by and extends between the shroud and the static structure. A dimension of the gap changes as the gap extends along the shroud.

An assembly is provided for a turbine engine. This assembly includes a static structure and an impeller rotor housed within the static structure. The impeller rotor includes a vane structure and a shroud. The vane structure includes a first sidewall, a second sidewall and a plurality of vanes arranged circumferentially about a rotational axis. The vanes include a first vane. The first vane includes a first portion, a second portion and a third portion. The first portion is axially between the first sidewall and the second sidewall. The second portion is radially between the first sidewall and the shroud. The third portion is radially between the second sidewall and the shroud. The shroud circumscribes the vane structure. A gap is formed by and extends between the shroud and the static structure. A dimension of the gap changes as the gap extends along the shroud.

A shroud assembly including a shroud support and an annular shroud is provided. The shroud assembly includes one or more pins for securing the annular shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. A gas turbine engine having a compressor section, a combustion section, a turbine section and a shroud assembly is also provided. The shroud assembly includes one or more pins for securing the continuous shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. Methods for assembling a shroud assembly structure in a gas turbine engine are also provided.

The invention relates to a shaft seal arrangement, comprising a first seal, a second seal and a third seal which are arranged in series between a product side to be sealed and an atmosphere side, wherein the second seal is arranged between the first seal and the third seal, wherein a first pressure is present in a space adjacent to the second seal in the direction towards the product side, and a second pressure is present in a space adjacent to the second seal in the direction towards the atmosphere side, wherein the space that is adjacent to the atmosphere side is connected to a pressure supply line via which a pressure medium can be supplied into the space, and wherein the first pressure is equal or substantially equal to the second pressure, so that the second seal can be operated with a pressure difference of zero between the first pressure and the second pressure.

In the turbine of a gas turbine engine, disk cavities exist between rotor and stator assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the rotor and stator assemblies with detrimental effects to the durability of the turbine. Thus, a flow discourager is disclosed that can be integrated into the platform of a stator assembly that is downstream from a rotor assembly. The flow discourager comprises a continuous external surface that defines a recirculation zone within a disk cavity that is aft to a rotor assembly to circulate the hot gas back out into the hot gas flow path.

The present disclosure generally relates to variable cellular structures, methods of making such cellular structures, and variable cellular flow discouragers for turbine engines for jet aircraft.

A clearance-control-type seal structure including a plurality of arc-shaped grooves (23) formed side by side in the axial direction with respect to an inner circumferential surface of a housing (22) of a turbine; and abradable seal rings (11, 12) having fitting parts (11a, 12a) that are fitted into the grooves so as to leave a prescribed gap, that have extended parts (11b, 12b) that are exposed from the housing in the radial direction toward the inside and expand in the axial direction, and that, during operation, due to back pressure inside the grooves, receive a force that moves in the radial direction toward the inside. One extended part has a protruding part extending even further in the axial direction toward the upstream side, and the other extended part has formed in an outer circumferential surface of a downstream-side end part thereof a recessed part that corresponds to the protruding part.

A bearing housing for a gas turbine engine has first and second housing members axially telescoped into each other at a slip joint. The first and second housing members extend circumferentially around a central axis for circumscribing a bearing cavity. The first housing member has a first bearing support for supporting a first bearing in the bearing cavity. The second housing member has a second bearing support for supporting a second bearing in the same bearing cavity. A seal is provided at the slip joint for sealing the bearing cavity.