Abstract: The invention relates to a method for producing a continuous driving force by providing kinetic energy of a liquid medium by means of bringing about differences in pressure in a closed system that is filled with liquid medium, in particular water, and gaseous medium, in particular air, and relates to a device for implementing the method, wherein the device consists of a vessel (1), which is enclosed on all sides, in which there is inserted an insert (2) that is open on its underside and in which a hollow body (3) with an outlet opening (4) is arranged on the upper side of the insert (2). Within the insert (2), a rotor (8) is arranged on a vertical shaft (7), said rotor (8) being driven by a motor (9). Fitted in the vessel (1) outside the insert (2) are one or more riser pipes (10), which are open at their lower ends and are inserted with their upper ends in the hollow body (3) above the insert (2) in a sealed-off manner.

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including an engine case, a retention block attached to the engine case, and a blade outer air seal (BOAS). The BOAS includes a plurality of layers formed of a ceramic matrix composite (CMC) material. At least one of the plurality of layers provides a slot receiving a portion of the retention block.

Abstract: A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine.

Abstract: An assembly for a turbine engine includes an inner platform, and outer platform and a plurality of structural inlet guide vanes. The outer platform circumscribes the inner platform. The structural inlet guide vanes are arranged around an axis, and extend radially between and are connected to the inner platform and the outer platform. A first of the structural inlet guide vanes includes a structural vane body that is configured from or otherwise includes an organic matrix composite.

Abstract: A turbine-generator device for use in electricity generation using heat from industrial processes, renewable energy sources and other sources. The generator may be cooled by introducing into the gap between the rotor and stator liquid that is vaporized or atomized prior to introduction, which liquid is condensed from gases exhausted from the turbine. 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.

Abstract: A centrifugal fan includes: a casing having an upper casing with an air suction opening, a lower casing, and a plurality of support members disposed between the lower casing and the upper casing with air discharge openings provided between the support members; an impeller disposed between the upper and lower casings, and including an annular upper shroud provided on an upper casing side, a base plate integrally formed with the annular upper shroud, and a plurality of blades arranged along a circumferential direction between the annular upper shroud and the base plate; and a fan motor which rotates the impeller. A plurality of recesses are provided on the upper surface of the upper casing, and formed to surround the air suction opening, and a plurality of ribs are radially provided around the air suction opening and between the adjacent recesses.

Abstract: A pump having a cutting wheel and a pre-cutter (26) for cutting chippings that are contained in the medium pumped by the pump, the pre-cutter being driven by a shaft portion that projects axially from the cutting wheel and having a plurality of wings (28), the pre-cutter being surrounded by a crest of anvil blocks (32) at which the free ends of the wings (28) move past in a little distance when the pre-cutter rotates, wherein the anvil blocks are configured as counter-blades (32) that are held exchangeably at a blade carrier (34) that surrounds the pre-cutter (26) at least on a part of its periphery.

Abstract: An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.

Abstract: A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.

Abstract: A thermal inspection system is provided for a gas turbine engine hot section component with a cooling passage. This thermal inspection system includes a fluid subsystem operable to supply a fluid into the cooling passage. The thermal inspection system also includes a thermal camera subsystem operable to monitor a fluid temperature difference of the fluid exiting the cooling passage relative to the input temperature of the fluid supplied to the cooling passage.

Abstract: An airflow assembly includes a fan, a shroud, a plurality of ribs, and a fan support. The fan has a number of fan blades. The shroud includes (i) a plenum defining a plenum opening located adjacent to the number of fan blades, and (ii) a barrel extending from the plenum so as to surround the plenum opening. The plenum further defines at least one airflow opening spaced apart from the plenum opening. Each of the plurality of ribs extends inwardly from the barrel. The fan support is attached to the plurality of ribs and is configured to support the fan. The at least one airflow opening is not an attachment structure or a guiding structure, is not configured to receive a fastening member, and does not function as a water drain.

Abstract: An exhaust-gas turbocharger (1) having a compressor housing (2) in which a compressor wheel (2?) is arranged; a bearing housing (3); and a turbine housing (4) in which a turbine wheel (4?) is arranged. The axial abutment surfaces (5, 6) are provided between the bearing housing (3) and the turbine housing (4). The axial abutment surfaces (5, 6) have at least one notch (9).

Abstract: An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.

Abstract: A blade for use in a wind turbine comprises a pressure side and suction side meeting at a trailing edge and leading edge. The pressure side and suction side provide lift to the turbine blade upon the flow of air from the leading edge to the trailing edge and over the pressure side and suction side. The blade includes one or more openings at the suction side, in some cases between the leading edge and the trailing edge. The one or more openings are configured to provide a pressurized fluid towards the leading edge of the blade, in some cases at an angle between about 0° and 70° with respect to an axis oriented from a centerline of the blade toward the leading edge.

Abstract: The present disclosure is directed to a component for a gas turbine. The component includes a component wall having a radially inner surface, a radially outer surface, a first circumferential surface, and a second circumferential surface. A first boss extends radially outwardly from the radially outer surface, includes a first circumferentially outer surface, and defines a first aperture extending axially therethrough. A second boss extends radially outwardly from the radially outer surface and is circumferentially spaced apart from the first boss. The second boss includes a second circumferentially outer surface and defines a second aperture extending axially therethrough. The first circumferentially outer surface of the first boss and the second circumferentially outer surface of the second boss form a pair of angles with respect to the radially inner surface.

Abstract: A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure. Various configurations of the fan track liner assembly are provided along with various mounting methodologies for securing the track liner assembly to the fan case of a gas turbine engine.

Abstract: A method of designing a common preform for providing a plurality of preforms for turbine engine outlet guide vanes of different geometrical profiles and made out of composite material, the method including 3D geometrical modeling of the geometrical profiles of the different outlet guide vane preforms, flattening out each of the geometrical profiles of the different outlet guide vane preforms, superposing the geometrical profiles of the different flattened outlet guide vane preforms, and converging towards a single geometrical profile for an outlet guide vane preform common to all of the outlet guide vane preforms while guaranteeing identical positioning for the top and bottom regions of non-interlinking for all of the outlet guide vane preforms.

Abstract: A wind-powered machine system includes a base station including a fluid-powered machine for performing work and a crankshaft operatively coupled to the machine. The rotation of the crankshaft drives the machine to perform work. The system further includes a first and a second airfoil operatively coupled to the crankshaft and a system controller configured to selectively alter at least one of the altitude and in-flight orientation of the first and second airfoils. In a first stage, a wind-driven movement of the first airfoil in a first direction away from the base station causes the crankshaft to rotate. The rotation of the crankshaft causes a movement of the second airfoil in a second direction generally opposite to the first direction and toward the base station. In a second stage, a wind-driven movement of the second airfoil in the first direction away from the base station causes the crankshaft to rotate.

Abstract: The invention relates to a method for producing a rotor blade by arranging foam (23, 24) in a semi-finished product, introducing resin into the foam-containing semi-finished product, and curing the introduced resin while heat is dissipated and a curing temperature distribution is obtained, a first foam (23) being arranged in regions of the semi-finished product with a higher curing temperature, and a second foam (24) in regions with a lower curing temperature, and a foam with a higher temperature resistance than the second foam (24) being chosen as the first foam (23).

Abstract: A method and a blade for a turbine or, more generally a turbomachine, are described with the blade having at a top end a shroud segment designed to engage with shroud segments of adjacent blades in an ring-shaped assembly at least partly by means of assembling the blades with the shroud segment having a central indentation along an engaging face.