Abstract: A fibrous preform obtained by three-dimensional weaving, comprising a first skin, a second skin, and a central portion connecting them and forming a stiffening element. In a transverse plane, transverse threads of the first skin and the second skin are woven in pairs in the first skin and the second skin on either side of the central portion; the threads of a first pair of the first skin and of a second pair of the second skin are separated into two unitary threads at the central portion by being woven with longitudinal threads, and a thread of the first pair crosses a thread of the second pair at least twice in the central portion.

Abstract: A method of operating a wind energy installation wherein a rotor has a first rotor blade which can be angularly adjusted, a first adjustment drive for adjusting the rotor blade, and a safety control system. In a normal mode of operation, the first adjustment drive is supplied with energy from a source and is controlled by a first pitch control system. In a failure mode of operation, the supply of energy to the first adjustment drive is switched from the source to an energy storage device and the safety control system monitors a position and/or movement of the first rotor blade. The first rotor blade is adjusted by the first adjustment drive in a direction of a predetermined stopping position, while the safety control system, as a function of the monitored position and/or movement, enables or effects a deactivation of a first power supply shut-off device.

Abstract: In the turbine of a gas turbine engine, disk cavities exist between rotor and stator assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the rotor and stator assemblies with detrimental effects to the durability of the turbine. Thus, a flow discourager is disclosed that can be integrated into the platform of a stator assembly that is downstream from a rotor assembly. The flow discourager comprises a continuous external surface that defines a recirculation zone within a disk cavity that is aft to a rotor assembly to circulate the hot gas back out into the hot gas flow path.

Abstract: An airfoil assembly for a gas turbine engine includes an airfoil extending radially relative to a central reference axis. A spar is located within the airfoil and spaced from the airfoil at all radial locations along the airfoil such that a gap is maintained between the airfoil and the spar. A foam is located between the airfoil and the spar.

Abstract: A three-dimensional fibrous preform of a fan blade includes a blade root and a blade airfoil between the blade root and a free end of the preform. The airfoil has an area with two skins and a longitudinal stiffener between the skins and, in a transverse plane, transverse yarns of the skins woven in pairs in the first and in the second skin either side of the stiffener, the yarns of a first pair of the first skin are separated into two unit yarns at the stiffener, the unit yarns being woven separately with longitudinal yarns, the yarns of a second pair of the second skin are separated into two unit yarns at the stiffener, the yarns being woven separately with longitudinal yarns, and a yarn of each pair cross over each other twice in the stiffener.

Abstract: A steam turbine hollow stationary blade is able to reduce the amount of water droplets captured on a blade surface. The steam turbine hollow stationary blade, which has a cavity therein, includes a partition wall dividing the cavity into a pressure chamber on a leading edge side and an exhaust chamber on a trailing edge side, at least one steam inlet hole connecting the pressure chamber and an outside of the stationary blade to each other, and at least one pressure conditioning hole connecting the pressure chamber and the exhaust chamber. Total opening area of the pressure conditioning hole is smaller than total opening area of the steam inlet hole.

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly. A spar system couples the inner vane support with the outer vane support.

Abstract: A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.

Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

Abstract: A gas turbine engine includes a propulsor and a fan drive turbine. The fan drive turbine drives the propulsor through a geared architecture. The geared architecture includes a sun gear, a ring gear, and intermediate gears supported on journal support pins. The sun gear engages the intermediate gears and the intermediate gears engages the ring gear. The journal support pins include a titanium body and an outer surface outside of the titanium body that has a surface hardness that is harder than the titanium body. The outer surface is provided by a steel sleeve. Oil supply holes extend from a central bore in the titanium body through the steel sleeve. At least one pin extends through the steel sleeve to secure the steel sleeve to the titanium body.

Abstract: A seal includes a mating ring that rotates relative to a carbon primary ring at a seal interface. A buffer gas is provided into the seal and passes from the back of the primary ring to the seal interface. The seal can be used as a separation seal or in combination with another seal.

Abstract: A gas turbine compressor has a flow duct wall disposed radially opposite to an airfoil tip and has a circumferential groove having an upstream groove edge and a downstream groove edge, the circumferential groove having a web having a radial cutback.

Abstract: An acoustic panel with a cellular core includes cells that are provided with one or more obstacles, each of the obstacles extending transversely in relation to the main axis of the associated cell so as to increase the length of the path (F) that sound waves travel through the cell. Methods enabling the production of such a panel implements steps of cutting, folding and bonding that are suitable for creating cells provided with such obstacles.

Abstract: A quick buckle structure of a fan blade of a ceiling fan comprises a base fixed on a rotor of a ceiling fan motor, wherein the base is provided with a bottom wall and a front wall, the front wall is provided with an insertion opening, the bottom wall is provided with a guide rail part adjacent to the insertion opening, and the bottom wall is provided with a fixing frame located above the guide rail part. The fan blade is inserted into the insertion opening with a tongue part, wherein the tongue part extends along the guide rail part. The tongue part is provided with a base area located behind the fixing frame, a stop block is integrally erected on the base area, and the stop block abuts against the fixing frame so that the fan blade cannot exit from the insertion port.

Abstract: A method of manufacturing a composite guide vane with a metallic leading edge includes receiving a layup of fiber-reinforced composite sheets of continuous, substantially parallel and non-interlaced fibers impregnated with a resin. A vane body is formed from the layup of sheets. The vane body includes a body mid portion for interacting with a fluid and a body end portion. The method includes applying a metallic sheath on part of the vane body. The metallic sheath defines a leading edge of the guide vane. The method includes overmolding a head or a foot of the guide vane onto part of the vane body and onto part of the metallic sheath.

Abstract: A ceiling fan having a dual redundant motor mounting assembly for suspending a motor comprising a downrod, a hollow motor shaft suspending the motor from the downrod, a retaining pin extending through the hollow motor shaft, and a retaining rod coupled to the retainer pin for redundantly suspending the motor.

Abstract: A blade structure with multiple blade angles and a heat dissipation device include: the blade structure consisting of a plurality of blades with different blade angles. The blade angles of the blades decrease from an inner side to an outer side along a longitudinal direction of the blade structure. The blades have top portions on the same surface and are integrally formed in one piece. A joint between the blades has a transition part. The blade structures are evenly mounted on the hub and are connected to an outer frame. The hub and the blade structures are integrally formed in one piece, or the hub, the blade structures, and the outer frame are integrally formed in one piece. The blade structures can guide air flow to reduce air shedding, suppress backflows, reduce vortex turbulence, increase air volume, improve heat dissipation efficiency, and reduce vortex noise and vibration.

Abstract: An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.

Abstract: A turbine housing for a two-wheel air cycle machine includes a first side of the turbine housing, a second side of the turbine housing, a central axis, an outer housing portion, an inner housing portion, a plurality of struts between the inner housing portion and the outer housing portion and a plurality of cooling slots between the plurality of supports. The outer housing portion includes an inner surface, an outer surface, a cooling inlet extending from the outer surface of the outer housing portion and a cooling outlet opposite the cooling inlet and extending from the outer surface of the outer housing portion. The inner housing portion includes a thrust bearing support surface substantially parallel to the second side of the turbine housing and a journal bearing bore extending between the first side of the turbine housing and the thrust bearing support surface.

Abstract: A propeller having a plurality of blades extending radially outward from a hub, the blades forming a loop. Each loop having an intake portion, an exhaust portion and a tip portion extending radially outward from the hub and a gap between the intake root and the exhaust root. The tip portion of each of the blades is 30%-75% of the blade, the tip portion beginning at a first deviation from zero of the roll value and extending to 90 degrees, wherein roll value is zero in a plane parallel to the hub axis, and wherein the blades have a vertical angle between ?45 degrees and 45 degrees throughout.