The turbine efficiency is improved by allowing water droplets being moved on a rotor blade surface to be released from the blade surface, while suppressing an influence on the aerodynamic performance of the rotor blade. Provided is a steam turbine rotor blade having, at an intermediate position in a blade length direction thereof, a tie boss for connection to an adjacent blade, wherein the steam turbine rotor blade includes a leading edge side protrusion that is extending in an embankment shape in a blade chord length direction at an intermediate position in the blade length direction, a start end and a terminal end of the leading edge side protrusion are located on a suction side surface and a pressure side surface, respectively, and the leading edge side protrusion continues from the start end to the terminal end via a blade leading edge and arrangement thereof in the blade length direction overlaps with the tie boss as viewed from the upstream side.

A thermal management system for a gas turbine engine includes a heat exchanger including first and second sides, with the first side in contact with flow path air flowing through a flow path of the engine. Furthermore, the system includes a housing positioned relative to the heat exchanger such that the housing and the second side of the heat exchanger define a plenum configured to receive bleed air from the engine. Moreover, the system includes and at least one of a plurality of fins extending outward from the second side of the heat exchanger in a radial direction into the plenum and along the second surface of the heat exchanger in the circumferential direction or an impingement plate defining a plurality of impingement apertures, with each impingement aperture configured to direct an impingement jet of the bleed air within the plenum onto the second side of the heat exchanger.

A system 100 for increasing the efficiency of an axial ducted fan 105 includes, a duct 110 for enclosing the axial ducted fan 105, wherein the axial ducted fan 105 is operationally mounted inside the duct 110. In use, the system 100 further includes, a shaft 115 operably connected to the axial ducted fan 105 for facilitating rotation of the axial ducted fan 105 inside the duct 110; and, a static fan 120 operably positioned parallel to the axial ducted fan 105. In use, the static fan 120 includes same number of blades as the axial ducted fan 105. The system 100 further includes a propulsion efficiency improvement mechanism 125 operably positioned inside the duct 110 for controlling, (a) a position of the static fan 120, and, (b) speed of rotation of the axial ducted fan 105.

Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.

A steam turbine exhaust chamber for guiding steam after passing through a rotor blade of a final stage of a steam turbine to outside of the steam turbine includes: a casing; a bearing cone; and a flow guide. An inner surface of the casing includes an inner circumferential surface extending along an axial direction of the rotor at a radially outer side of the flow guide and a side wall surface connecting the inner circumferential surface and the bearing cone. A first protruding portion is formed on the side wall surface along the circumferential direction above a horizontal plane including a rotational axis of the rotor. The first protruding portion is positioned at an outer side, in the radial direction of the rotor, of a downstream end of an inner circumferential surface of the flow guide in at least a partial range in the circumferential direction.

The present invention concerns an adjustment mechanism (200) for variable adjustment of an inlet cross-section (321) of a compressor inlet (322). The adjustment mechanism comprises a plurality of rotatably mounted baffle elements (210) which are arranged in a circumferential direction (26) and are adjustable between a first position and a second position. At least one baffle element (210) of the plurality of baffle elements (210) comprises an eddy-reducing feature (220).

An example gas turbine engine includes a compressor including a casing defining a passageway and a shaft extending through the passageway. The shaft drivingly coupling the compressor and a turbine of the gas turbine engine. The shaft has an opening to receive airflow from the passageway. The gas turbine engine also includes an inner shroud, stator vanes coupled to and extending radially between the casing and the inner shroud, and an offtake scoop disposed on a downstream side of the inner shroud. The offtake scoop has a channel to direct the airflow radially inward toward the opening in the shaft.

A component includes a component body. The component further includes a first passage disposed in the component body. The first passage includes a first end and a second end opposite the first end. The component further includes a second passage. The second passage extends from the second end of the first passage. The second passage includes a turn. The component further includes a third passage. The third passage extends from the second end of the first passage. The component further includes a first projection extending from a passage surface of the component body within the first passage. The first projection is disposed between the first and the second end of the first passage and is configured to direct debris transiting the first passage away from the second passage and into the third passage.

A rotating machine includes a hollow casing; a rotating body rotatably supported in the casing; a stator blade fixed to an inner peripheral portion of the casing; a rotor blade fixed to an outer peripheral portion of the rotating body to be offset to the stator blade in an axial direction of the rotating body; a sealing device arranged between the inner peripheral portion and a tip of the rotor blade; a swirling flow generation chamber provided in the casing on a downstream side in a fluid flow direction from the sealing device along a circumferential direction of the rotating body; first guiding members provided in the swirling flow generation chamber along a radial direction and in a circumferential direction of the rotating body at predetermined intervals; and a second guiding member provided in the chamber along the circumferential direction while intersecting the first guiding members.

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. The first rotor disk is configured to rotate about a rotational axis. The first rotor disk is configured from or otherwise includes disk material. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis and axially between the first rotor disk and the second rotor disk. The vanes include a first vane, which first vane is configured from or otherwise includes vane material that is different than the disk material.