Disclosed is a thermal barrier coating system for components of a turbomachine, especially for high temperature-stressed or hot gas-stressed components of a turbomachine, comprising a ceramic coating of fully or partially stabilized zirconium oxide, and an oxide cover coating which comprises aluminum and at least one element from the group lanthanum, magnesium, silicon, calcium and sodium. The aluminum oxide exists at least partially as free α-Al.sub.2O.sub.3. Also disclosed is a method for producing a corresponding thermal barrier coating system.

A steam turbine includes a rotor; a casing which houses the rotor; a plurality of rotor blades disposed around the rotor; and a plurality of stationary vanes supported on the casing. The stationary vane includes a vane body portion and an inner race positioned on an inner side of the vane body portion in a radial direction of the rotor. The stationary vanes include a first stationary vane having a through hole formed through the vane body portion. The rotor has a cavity having a concave shape and being formed such that at least a part of the inner race of the first stationary vane is housed in the cavity. The steam turbine includes a steam passage to discharge steam extracted from a space upstream of the first stationary vane in the casing to the cavity from the inner race through the through hole of the first stationary vane.

A steam turbine includes a rotor; a casing which houses the rotor; a plurality of rotor blades disposed around the rotor; and a plurality of stationary vanes supported on the casing. The stationary vane includes a vane body portion and an inner race positioned on an inner side of the vane body portion in a radial direction of the rotor. The stationary vanes include a first stationary vane having a through hole formed through the vane body portion. The rotor has a cavity having a concave shape and being formed such that at least a part of the inner race of the first stationary vane is housed in the cavity. The steam turbine includes a steam passage to discharge steam extracted from a space upstream of the first stationary vane in the casing to the cavity from the inner race through the through hole of the first stationary vane.

A vane segment includes a blade ring, a plurality of vanes, and a caulking member. The blade ring includes a blade ring groove and a storage space forming portion. The blade ring groove includes a convex portion projecting from a second groove side surface of the blade ring groove to the first side. The storage space forming portion, in combination with an outer shroud, forms a storage space into which the caulking member enters. The caulking member is accommodated within the storage space, contacts with the blade ring groove and the outer shroud, and is exposed from an inner opening of the storage space.

A diffuser pipe includes a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a first direction from an inlet of the tubular body, a second portion extending in a second direction transverse to the first direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. A stiffening rib extends outwardly from an outer surface of the first portion of the tubular body.

A turbine includes: an inner diameter side exhaust flow path; an outer diameter side exhaust flow path having a flow path cross-sectional area smaller than a flow path cross-sectional area of the inner diameter side exhaust flow path; an inner diameter side bypass flow path connecting the inner diameter side exhaust flow path and a discharge flow path; and an outer diameter side bypass flow path connecting the outer diameter side exhaust flow path and the discharge flow path, the outer diameter side bypass flow path having a flow path cross-sectional area larger than a flow path cross-sectional area of the inner diameter side bypass flow path.

A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face includes a first swept surface extending at a first angle relative to a nominal slash face angle and a second swept surface extending at a second angle relative to the nominal slash face angle. The first and second swept surfaces meet at an arc having a peak that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.

A multi-material vane includes an airfoil extending longitudinally between a leading edge and a trailing edge. The airfoil extends spanwise between an inner end and an outer end. The airfoil extends laterally between a first side and a second side. The airfoil includes a base section, a first side section, a second side section and a sheath. The base section extends along the span line between the inner end and the outer end. The base section is laterally between the first side section and the second side section. The first side section is connected to the base section and partially forms the first side of the airfoil. The second side section is connected to the base section and partially forms the second side of the airfoil. The sheath at least partially forming an edge of the airfoil. The edge is the leading edge or the trailing edge of the airfoil.

A multi-material vane includes an airfoil extending longitudinally between a leading edge and a trailing edge. The airfoil extends spanwise between an inner end and an outer end. The airfoil extends laterally between a first side and a second side. The airfoil includes a base section, a first side section, a second side section and a sheath. The base section extends along the span line between the inner end and the outer end. The base section is laterally between the first side section and the second side section. The first side section is connected to the base section and partially forms the first side of the airfoil. The second side section is connected to the base section and partially forms the second side of the airfoil. The sheath at least partially forming an edge of the airfoil. The edge is the leading edge or the trailing edge of the airfoil.

A turbine housing can include a bearing housing end and a treatment unit end; a volute wall that defines a volute; a wall that defines at least a portion of a turbine wheel space that defines a turbine wheel space axis and a turbine wheel space diameter, where the wall extends to an axial peak to define an extended space with an extended space outlet having an extended space outlet dimension; and an outlet wall that defines an outlet space with a treatment unit end outlet having an outlet dimension, where the extended space is disposed at least in part axially between the turbine wheel space and the outlet space to increase axial velocity uniformity at the treatment unit end outlet.