Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement an integrated stator-fan frame assembly. An integrated fan exit stator-fan frame strut assembly for a gas turbine engine includes a fan exit stator portion having an airfoil including a leading edge and a trailing edge, and a fan frame strut portion including a leading edge and a trailing edge, the leading edge of the fan frame strut portion aerodynamically integrated with the trailing edge of the fan exit stator portion.

Abstract: Disclosed herein is a seal comprising an annular ring comprising: an outer diameter surface having an outer diameter, an inner diameter surface, a first height measured from the outer diameter surface to the inner diameter surface, wherein a first ratio of the outer diameter to the first height is greater than 10:1; and a cross-sectional shape comprising: a central beam extending from an inner end to an outer end, the central beam including a central axis that defines an angle with a neutral axis of the cross-sectional shape, the angle being between 5 degrees and 25 degrees; a first flange extending axially from the inner end of the central beam in a first axial direction; and a second flange extending axially from the outer end of the central beam in a second axial direction, the second axial direction being opposite the first axial direction.

Abstract: A nozzle includes an endwall connected to an airfoil at one of a tip and root of the airfoil. The endwall includes a first and second side slash faces at respective circumferential edges thereof. The endwall also includes an inner surface extending between the first and second side slash faces. The inner surface includes a first planar surface portion adjacent to the first side slash face, a second planar surface portion adjacent to the second side slash face, and an arcuate surface portion extending between the first and second planar surface portions. The planar surface portions reduce a chute height by reducing hot gas path curvature locally along the side slash faces, which reduces working fluid ingestion between endwalls of the adjacent nozzles. The planar surface portions can be applied to an inner and/or an outer endwall of a nozzle.

Abstract: A turbine shroud assembly includes a carrier assembly, a blade track segment, a retainer, and a clip shim. The carrier assembly is arranged circumferentially at least partway around an axis. The blade track segment is supported by the carrier assembly to locate the blade track segment radially outward of the axis and define a portion of a gas path of the turbine shroud assembly. The retainer extends into the carrier assembly and the blade track segment. The clip shim is located between the carrier assembly and the blade track and configured to urge the blade track segment axially toward the carrier assembly.

Abstract: A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud.

Abstract: Exhaust frequency mitigation apparatus, exhaust diffusers, and turbomachines are provided. An exhaust frequency mitigation apparatus includes a main body extending along an axial centerline from a base to a tip. the base defines a first diameter and the tip defining a second diameter. the main body converges from the first diameter to the second diameter with respect to the axial centerline. The base is configured to extend from an inner shell of a turbomachine exhaust diffuser. The exhaust frequency mitigation apparatus further includes at least one rib extending from a root coupled to the main body to a free end.

Abstract: A method for producing an integrally bladed rotor includes providing imaginary front and rear lattice points on the ridges of the front and rear edges; providing a first imaginary line on positive-pressure and negative-pressure surfaces to connect a first imaginary front lattice point and a first imaginary rear lattice point; providing a second imaginary line on the positive-pressure and negative-pressure surfaces to connect a second imaginary front lattice point next to the first imaginary front lattice point and a second imaginary rear lattice point next to the first imaginary rear lattice point; providing a spiral path on the positive-pressure and negative-pressure surfaces by connecting the first and second imaginary lines with a spiral curve; and cutting the positive-pressure and negative-pressure surfaces by moving a cutting point corresponding to a cutting edge of a turning tool along the spiral path. point around the blade.

Abstract: An acoustic attenuation structure for a gas turbine engine includes a periodic structure having a first unit cell, the first unit cell having a first central body and a first axial tube disposed on the first central body and a second axial tube disposed on the first central body, opposite the first axial tube, each of the first axial tube and the second axial tube being in fluid communication with one another through the first central body.

Abstract: This steam turbine comprises: a rotating shaft that extends along an axis; a plurality of rotor blades that are arranged in the circumferential direction and that extend in a radial direction from the outer circumferential surface of the rotating shaft; a casing body that covers the rotating shaft and the rotor blades from the outer circumference side; and a plurality of stationary blades that extend in the radial direction from a position on the inner circumferential surface of the casing body on the upstream side of the rotor blades and that are arranged in the circumferential direction. A plurality of microgrooves that extend in the steam flow direction are formed on the surface of the rotor blades and/or the stationary blades.

Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.

Abstract: A vertical rotating system that includes a first vertical shaft that rotates. The first vertical shaft is oriented such that the gravitational force is substantially parallel to the first vertical shaft. A radial bearing extends about a first portion of the first vertical shaft. A first impeller sectioned couples to the first vertical shaft and rotates in a first direction to pump a first fluid. A first stator surrounds the first vertical shaft. The first stator defines a first groove that extends about a second portion of the first vertical shaft. The first groove receives a second fluid. A pressure of the second fluid drives the first vertical shaft away from the first groove.

Abstract: A multi-material vane is provided for a gas turbine engine. This vane includes an airfoil extending along a chamber line between a leading edge and a trailing edge. The airfoil extends along a span line 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 and a second side section. The base section defines at least a portion of the trailing edge of the airfoil. The base section is laterally between and connected to the first side section and the second side section. The first side section defines at least a portion of the first side of the airfoil. The second side section defines at least a portion of the second side of the airfoil.

Abstract: A machine support for a wind power installation, in particular a gearless wind power installation, wherein the machine support is designed to be rotated about a tower axis by means of an azimuth drive, and has a supporting structure which has a first mechanical interface for connecting the machine support indirectly or directly to an azimuth bearing and a second mechanical interface for assembling a generator or an axle journal on the machine support. It is proposed in particular that the supporting structure has one or a plurality of lateral through openings as access to the azimuth drive and/or the azimuth bearing.

Abstract: An integrated nozzle set for injecting a substance into a turbine is provided. The nozzle set includes an outer nozzle container arranged around a part of a circle and an inner nozzle container having a first part arranged around a remaining part of the circle and a second part concentric with the outer nozzle container. The nozzle set further includes a diaphragm connected to the inner nozzle container and configured to seal a cavity of the turbine, a flange having spokes connected to the inner nozzle container, a set of nozzles, and collectors inserted into the outer nozzle container and configured to collect a substance. The nozzles include a first group of nozzles disposed in the outer nozzle container, a second group of nozzles disposed in the first part of the inner nozzle container, and a third group of nozzles disposed in the second part of the inner nozzle container.

Abstract: A turbomachine includes a rotating group with a turbine wheel. The turbomachine also includes a housing that houses the rotating group, wherein the housing defines a turbine outlet passage for exhaust from the turbine wheel. The turbine outlet passage is directed in a downstream direction along an axis of the turbine outlet passage. The turbomachine includes an air bearing system with at least one bearing component that supports the rotating group for rotation relative to the housing. The air bearing system includes a bearing cooling path that is fluidly connected to the at least one bearing component and that has a bearing air line outlet. The bearing air line outlet is fluidly connected to the turbine outlet passage and is directed in the downstream direction along the axis.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.

Abstract: A rotor (10) for a hydro-powered electricity generator. The rotor (10) includes a hub (12) and a plurality of blades (16). The hub (12) has a circular cross sectional shape and a longitudinal rotational axis (14). The plurality of blades (16) each have proximal root (16a) and a distal tip (16b). Each of the blade roots (16a) are mounted to the hub (12) at the widest part thereof (D1). The ratio between the diameter of the tips (16b) of the blades to the diameter of the widest part (D1) of the hub (12) is less than about 2:1.

Abstract: An airfoil for use in a gas turbine engine is formed to define a cavity formed in the airfoil. The airfoil further includes at least one obstructing member arranged within the cavity and a shear-thickening fluid disposed in the cavity. A viscosity of the shear-thickening fluid increases in response to the airfoil experiencing an aeromechanic response or vibrations such that the obstruction of the movement of the thicker fluid by the obstructing member dampens the vibrations of the airfoil and reduces negative effects of a dynamic response of the airfoil.

Abstract: A steam turbine and a method for internally cooling the same. The steam turbine includes an outer casing and an inner casing; a rotor having a balancing piston, the rotor being rotatably mounted inside the inner casing; and a steam flow channel formed between the inner casing and the rotor. Moving blades fitted with the rotor and stationary blades fitted with the inner casing are alternately arranged to form multiple stages of blade groups, and an interlayer for steam to circulate is formed between the inner casing and the outer casing. The multiple stages of blade groups include a first set blade staging and a second set blade staging; and the top of the balancing piston is provided with a first chamber and a second chamber.

Abstract: A fan wheel includes a pair of opposing parallel plates that rotate about an axis, one of the plates moves toward and away from the other of the plates along the axis. The fan wheel also includes a plurality of telescoping fan blades having opposite ends respectively mounted to the plates such that the one of the plates moves away from the other of the plates as the telescoping fan blades extend and the one of the plates moves toward the other of the plates as the telescoping fan blades retract.