A seal system includes a ceramic component that has a non-core-gaspath surface region that defines a first surface roughness and a core gaspath surface region. A metallic component is situated adjacent the non-core-gaspath surface region. A coating system is disposed on the ceramic component. The coating system includes a silicon-containing layer on the non-core-gaspath surface region and a barrier layer that has a first section on the silicon-containing layer and a second section on the core-gaspath region and that is connected to the first section. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The first section is in contact with the metallic component and the second section serves as an environmental barrier on the core-gaspath region.

A turbine and a turbine-generator device for use in electricity generation. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.

A seal segment has an arcuate body having: a first end; a second end circumferentially opposite the first end; a first face; a second face axially opposite the first face; an inner diameter (ID) face; and an outer diameter (OD) face. The seal segment is shaped to interfit with a plurality of identical seal segments first end to second end to form a seal surrounding a central longitudinal axis. The first face has: a circumferential channel closer to the ID face than the OD face; and a plurality of channels extending from the circumferential channel to the OD face. The ID face has: a circumferential channel closer to the first face than the second face; and a plurality of channels extending from the circumferential channel to the second face. The ID face circumferential channel has an open end.

An annular intermediate casing for a turbomachine through which an aerodynamic airstream circulates, including a radially internal shroud (31), a radially external shroud, at least one stator blade including a vane with a leading edge, and at least one aero-dynamic member which is formed of a structural arm extending radially at least in part between the radially internal shroud and the radially external shroud. The aerodynamic member includes a leading edge which is aligned with the leading edge of the stator blade in one plane and which is borne by a profiled portion positioned upstream of the structural arm in the direction of circulation of the aerodynamic airstream, the profiled portion, the structural arm, the radially internal shroud and the radially external shroud being monobloc.

Methods, apparatus, systems, and articles of manufacture are disclosed to implement a stator plenum with collet seal. The stator plenum for a gas turbine engine includes an outer shell circumscribing a centerline axis, a first end of the outer shell coupled to an engine casing at a first coupling, the first coupling to form a first seal, a second end of the outer shell coupled to the engine casing at a second coupling, the second end formed by a thickened portion of the outer shell, the second coupling to form a second seal, and a cavity formed by the outer shell, the cavity to contain cooling flow to reduce a temperature of a turbine.

A seal system includes a ceramic component, a metallic component, a silicon-containing layer, and a barrier layer. The ceramic component has a first surface region that defines a first surface roughness. The metallic component is situated adjacent to the first surface region and has a second surface region facing the first surface region. The silicon-containing layer is on the first surface region of the ceramic component and has a contact surface that defines a second surface roughness which is less than the first surface roughness. The barrier layer is on the metallic component and in contact with the silicon-containing layer and serves to limit interaction between silicon of the silicon-containing layer and the metallic component. The barrier layer includes at least one of alumina or MCrAlY.

A seal system includes a ceramic component, a metallic component, a coating system. The ceramic component has a first surface region that defines a first surface roughness. The metallic component is situated adjacent to the first surface region and has a second surface region facing the first surface region. The coating system includes a silicon-containing layer on the surface region of the ceramic component and barrier layer on the silicon-containing layer. The silicon containing layer has a surface in contact with the barrier layer and the barrier layer has a surface in contact with the metallic component. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The barrier layer serves to limit interaction between silicon of the silicon-containing layer and elements of the metallic component. The barrier layer includes at least one of mullite, zircon, or hafnon.

A turbine section has: a rotor rotatable about a central axis, the rotor having blades each protruding radially outwardly from a platform relative to the central axis; a stator having vanes each protruding radially outwardly from a shroud; a rim seal between the platform and the shroud, the rim seal having: an axial overlap between the platform and the shroud, and a lip protruding in a direction having a radial component relative to the central axis from one of the platform and the shroud toward the other of the platform and the shroud, the lip axially overlapping the other of the platform and the shroud, the lip having a radial height such that a radial gap remains between the lip and the other of the platform and the shroud when the turbine section is in operation.

A brush seal is provided that includes a top plate, a back plate, and a bristle pack. The bristle pack is secured at a joint between the top plate and the back plate. The bristle pack includes a first bristle set extending from the joint, a second bristle set extending from the joint, and a sliding backing plate. The sliding backing plate includes a sliding portion and a support portion. The sliding portion is disposed contiguous with the second bristle set. The support portion has an inner face and a support face. The inner face is in contact with a distal end of the second bristle set. The support face is configured to support at least a portion of the first bristle set. The sliding backing plate is configured to slide relative to the second bristle set.

A labyrinth sealing joint for a turbomachine, for example of an aircraft, includes a rotor element extending about an axis (A), and a stator element extending around the rotor element, the rotor element having two annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element. A plurality of gas passage cavities are arranged circumferentially next to one another between the two lips which are interconnected by connecting partitions, wherein at least one of the lips has at least one axial gas passage opening that leads into at least some of the cavities, wherein the partitions extend substantially axially between the lips and define sectors of gas passage spaces between them, the sectors of spaces being divided by separation walls for forming the cavities.