A turbine stator includes a partition plate including an inner ring that extends along a circumferential direction, an outer ring that is disposed on an outer side of the inner ring in a radial direction, and extends in the circumferential direction, a plurality of nozzles that are disposed in the circumferential direction between the inner ring and the outer ring, and are configured to guide a fluid from an upstream side toward a downstream side in an axial direction, and an annular protruding portion, protrudes from the outer ring to the downstream side in the axial direction, and extends along the outer ring in the circumferential direction, and a casing surrounding the partition plate from the outer side in the radial direction, and having a contact support surface that is in contact with the annular protruding portion from the downstream side in the axial direction.

A nozzle box assembly includes steam inlets, through which working steam is supplied, a torus part connected to the steam inlets so as to form an annular steam path and having an opening portion, in which a part of the front surface of the annular steam path is opened, a bridge ring connected to the front surface of the torus part and having a bridge inside, and a steam path ring connected to the bridge ring so as to provide a path, which is connected to a stage, and provided with a plurality of vanes, wherein the bridge ring and the steam path ring are formed of the coupling of a plurality of divisions, which are divided in the circumferential direction thereof, and the divisions are coupled to the front surface of the torus part.

An airfoil assembly includes first and second fiber-reinforced composite airfoil rings. Each ring is comprised of inner and outer platform sections, a suction side wall that extends between the inner and outer platforms, and a pressure side wall that extends between the inner and outer platforms. the first ring mates at an interface with the second ring such that the suction side wall of the first ring and the pressure side wall of the second ring together form an airfoil that circumscribes an internal cavity. The interface along the airfoil includes a gap that is configured to emit cooling air from the internal cavity.

A turbomachine stator element extends around a longitudinal axis and includes a first stator vane and a second stator vane circumferentially adjacent to the first stator vane. Each of the first and second stator vanes include a platform and a blade extending radially from the platform. The stator element also comprising at least one inter-platform seal, arranged between the platform of the first stator vane and the platform of the second stator vane. The inter-platform seal has a flat support provided with an upper surface on which there extends a fin.

A split case assembly for a gas turbine engine includes an outer diameter case defining a partial case structure for a gas turbine engine and multiple fixed-variable vanes attached to an inner diameter surface of the outer diameter case. Each of the fixed-variable vanes protrudes radially inward from the outer diameter case. Each of the fixed-variable vanes in the plurality of fixed-variable vanes is interfaced with one of a plurality of inner diameter boxes at a radially inward end of the fixed-variable vane, such that the inner diameter boxes define an inner diameter of a flow path and the outer diameter case defines an outer diameter flow path. Each of the fixed-variable vanes are interfaced with the one of the plurality of inner diameter boxes through at least one inner diameter shoe in a plurality of inner diameter shoes.

A turbine engine turbine including a nozzle stage made of ceramic matrix composite material and including a plurality of annular sectors forming an annulus presenting an inner shroud and an outer shroud, each sector having an inner platform forming a portion of the inner shroud, an outer platform forming a portion of the outer shroud, and at least one airfoil extending between the outer and inner platforms and secured thereto. A metal ring includes at least one annular sector, and presents an outer surface in contact with the surface of the inner shroud opposite from the surface from which the airfoils extend, the metal ring presenting an outside diameter at its outer surface that is greater than the diameter of the inner shroud such that the nozzle stage is held in compression between a casing and the metal ring.

A turbine nozzle for a gas turbine engine includes a plurality of nozzle segments that are configured to be assembled into a full ring such that each one of the plurality of nozzle segments is adjacent to another one of the plurality of nozzle segments. Each one of the plurality of nozzle segments includes an endwall segment and a nozzle vane. The turbine nozzle includes a feather seal interface defined by endwall segments of adjacent ones of the plurality of nozzle segments. The feather seal interface is defined along an area of reduced pressure drop through a pressure field defined between adjacent nozzle vanes of the plurality of nozzle segments to reduce leakage through the plurality of nozzle segments. The turbine nozzle includes a feather seal received within the feather seal interface that cooperates with the feather seal interface to reduce leakage through the plurality of nozzle segments.

A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall each 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 a joining line that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.

An air inlet manifold and a gas turbine including the same, capable of preventing transmission of vibration from the gas turbine to the air inlet manifold, while at the same time preventing air leakage, and the air inlet manifold is installed to be spaced apart from the compressor and relatively movable, as the anti-vibration pad in a compressed state is interposed between the air inlet manifold and the compressor.

A turbine nozzle assembly for use in a turbine engine is provided. The assembly includes an inner barrel and a turbine nozzle support ring. The inner barrel has a forward end and an aft end. The turbine nozzle support ring includes an annular body that defines a forward end, an opposite aft end, an inner surface, and an opposite outer portion. The forward end of the annular body is coupled to the aft end of the inner barrel. The annular body includes a first arcuate segment and a second arcuate segment removably coupled to the first arcuate segment. The first arcuate segment has a first arcuate length and the second arcuate segment has a second arcuate length. The second arcuate length is shorter than the first arcuate length.