Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a case structure and an air conduit. The case structure extends circumferentially about and axially along an axis. The air conduit has a conduit centerline, a conduit first end and a conduit second end. The air conduit extends longitudinally along the conduit centerline between the conduit first end and the conduit second end. The conduit first end is connected to the case structure at a first location. The conduit second end is connected to the case structure at a second location. The air conduit is displaced from the case structure longitudinally between the conduit first end and the conduit second end. At least a majority of the conduit centerline follows a non-straight trajectory.

Abstract: An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a stationary engine structure. The stationary engine structure includes a diffuser, a combustor, an engine case and a plenum. The combustor is disposed within the plenum. The engine case forms a peripheral boundary of the plenum. A gas path extends sequentially through the diffuser, the plenum and the combustor. A first section of the stationary engine structure is formed as a first monolithic body. The first section includes the diffuser and the combustor. A second section of the stationary structure is formed as a second monolithic body. The second section is configured as or otherwise includes the engine case.

Abstract: A dual walled component includes a spar comprising a plurality of pedestals; a coversheet attached to a first set of pedestals from the plurality of pedestals; and a repaired coversheet portion attached to a second set of pedestals from the plurality of pedestals and to the coversheet, where the repaired coversheet portion includes a braze material.

Abstract: Exhaust outlets (e.g., in a gas turbine engine) are generally made from sections of thin-walled materials (e.g., sheet metal) that are joined by flanges. Due to the length of the exhaust outlet and differing thermal expansion coefficients exhibited by the flanges and the thin-walled materials, these joints are subjected to high mechanical, as well as thermal, stresses. A long-arm flange is disclosed that decouples the mechanical stress from the thermal stress in the flange and distributes the stress, to thereby reduce the stress at the flange interface. Additionally, the long-arm flange can be easily adapted to the specific geometry of any exhaust outlet.

Abstract: An energy generation system, has a roof that is configured to rest upon a structure. A frame is joined to the roof with a mounting bracket. A turbine arranged in the frame with a first turbine shaft and a second turbine shaft. A first alternator is joined to the first turbine shaft with a first drive gear. A second alternator is joined to the second turbine shaft with a second drive gear. A switching system is joined to the first alternator and the second alternator. The switching system is programmed with a loop of instructions to determine a turbine rotational speed. Then, engage the first alternator. After that, monitor the turbine rotational speed. Following that, engage the second alternator.

Abstract: A rotor blade of a wind turbine, wherein the rotor blade has in particular a splitter plate, which is arranged on the blunt trailing edge of the rotor blade. The splitter plate comprises: a root edge, wherein the root edge is arranged on, in particular along, the trailing edge below a transition from the suction side into the trailing edge, an end edge, wherein the end edge forms a free edge, and a surface between the root edge and the end edge, wherein the surface has at least one curved part between the root edge and the end edge, and at least one part of the surface lies in the shear layer generated by the suction side. A rotor blade of a wind turbine, wherein the rotor blade has in particular a splitter plate, which is arranged on the blunt trailing edge of the rotor blade.

Abstract: An outlet guide vane for a turbofan engine, which results in reduced noise. The outlet guide vane may comprise an aerofoil, the aerofoil comprising at least porous section, wherein the at least one channel or porous section is positioned near the leading edge of the aerofoil.

Abstract: Provided is a lightning protection system for a carbon pultruded blade including a stack of carbon pultruded layers having at least a bottom layer and a top layer, each layer having a first end and a second end; the stack defining a tip-region, a root-region, and a mid-region; at least one lightning conductor extending along the stack from the tip-region to the root-region; and a plurality of electrical connections connecting the stack of layers with the lightning conductor, each end of each layer is electrically connected with the lightning conductor by one of the electrical connections; and each electrical connection that connects one of the ends of the top layer with the lightning conductor is electrically connected with the bottom layer. A carbon pultruded blade is also provided.

Abstract: A convertible ducted fan engine and mounting system. The convertible ducted fan engine has a shroud encircling a mechanical fan. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

Abstract: A rotary machine is provided. The rotary machine includes a rotor disk including a plurality of slots, a plurality of blades mounted on an outer circumferential surface of the rotor disk, each of the blades having a root part inserted into an associated one of the slots, and a retainer restraining axial movement of the plurality of blades, wherein the retainer includes an inner fixing member inserted into a bottom of the slot, an outer fixing member inserted into a lower surface of the root part to abut against the inner fixing member, and a spacer inserted between the outer fixing member and the bottom of the slot to prevent the outer fixing member from being separated.

Abstract: A tool for performing inspection and/or maintenance operations on an engine defines a longitudinal direction and a tangential direction. The tool includes a base extending along the longitudinal direction and including a body, a first extension member extending from the body in the tangential direction at a first location, and a second extension member extending from the body in the tangential direction at a second location. The second location is spaced from the first location along the longitudinal direction. The tool also includes a pivot member rotatably coupled to the base and moveable between an insertion position in which the pivot member is oriented generally along the longitudinal direction and a deployed position in which the pivot member is oriented away from the longitudinal direction.

Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

Abstract: Disclosed are pumps designed to make priming more efficient and therefore reduce priming time. The disclosed pumps include one or more deflection structures that prevent fluid moving through a diffuser of the pump from continuing in a circular path and instead divert the fluid in a different direction that leads directly to an outlet of the pump. This deflection reduces air bubble accumulation inside the pump while priming and makes it easier for air to escape through the pump outlet. Making it easier for air to escape the pump outlet ultimately allows air to escape the pump faster during priming, reducing back pressure caused by trapped air pockets inside the pump and improving priming performance.

Abstract: A sealing system includes: a double mechanical seal having a pump-side sealing mechanism (10, 12) and an atmospheric-side sealing mechanism (11, 13); a pump mechanism (19) driven by a rotational shaft (1); a first medium circulation line (30) for circulating a fluid barrier-and-cooling medium between a first chamber (22a) and a second chamber (22b), the first medium circulation line (30) being coupled to the first chamber (22a) and the second chamber (22b), the fluid barrier-and-cooling medium being different from a fluid handled by the centrifugal pump; a heat exchanger (21) and a shut-off valve (28) attached to the first medium circulation line (30); a second medium circulation line (31) bypassing the shut-off valve (28); and a medium pressurizing pump (45) and an on-off valve (23) attached to the second medium circulation line (31).

Abstract: A boundary layer turbomachine can include a housing (10) defining an interior space and having an inlet opening and an outlet opening to facilitate movement of a fluid through the housing (10). The boundary layer turbomachine can also include a rotor assembly (20) disposed in the rotor chamber and configured to rotate about an axis of rotation (1). The rotor assembly (20) can have a plurality of disks (21) spaced apart along the axis of rotation (1) to provide gaps (54) between the disks (21). The plurality of disks (21) can also define an interior opening (26) along the axis of rotation (1). The rotor assembly (20) can have a disk carrier (46) disposed at least partially in the interior opening (26) in support of the plurality of disks (21). The disk carrier (46) can have a fluid passageway (47) exposed to two or more of the gaps (54) between the disks (21). The fluid can pass through gaps (54) between the disks (21) and the interior opening (26) as the fluid moves through the housing (10).

Abstract: An inner shroud block component for a gas turbine. The inner shroud block has a radially inward facing surface with an abradable material applied thereto. The abradable material includes a zone of ridges that extend radially inwardly from the radially inward facing surface to minimize the clearance between the inner shroud block and the blade tip of a turbine blade. The abradable material may be ceramic and may be abraded by the blade tip if contact occurs between the blade tip and the inner shroud block. The zone of ridges extend along the radially inward facing surface in parallel to a direction of rotation of the turbine blade.

Abstract: A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan forces fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and adjusts a direction of the fan exit air, and includes a plurality of outlet guide vanes and a plurality of actuation assemblies that control rotation of the outlet guide vanes about a pitch axis. The outlet guide vanes include a leading edge portion and a trailing edge portion rotatably coupled to an axially aft edge of the leading edge portion. The actuation assembly rotates the leading edge portion and the trailing edge portion to minimize losses created by distortions in fan inlet air and created by the leading edge portion redirecting the fan exit air in the first direction.

Abstract: The rotor of a hybrid aerodyne for producing lift by rotating during a stage of vertical flight and then for being held stationary and stored longitudinally during a stage of cruising flight has at least one single-blade with a counterweight. The length of the active blade that generates lift of the rotor while rotating is significantly shorter than the length of the radius of the rotor. The portion that carries the active blade that makes the connection between the active blade and rotor mast is structurally rigid. The rigid portion that carries the active blade presents a cross-section optimized to provide zero or almost zero lift and very little aerodynamic drag while the rotor is rotating. The assembly is hinged about a transverse axis perpendicular to the vertical axis of the rotor and substantially on the vertical axis of the rotor mast.

Abstract: A wind turbine is provided. The turbine includes a support having an axis of rotation, a generator, a plurality of blades rotatably mounted on the support about the axis of rotation, the blades being moveable between a retracted position generally parallel with the axis of rotation and a fully deployed position generally perpendicular with the axis of rotation, the blades being connected to the generator such that rotation of the blades in a direction induced by wind causes the generator to produce electricity, and the provision of electricity to the generator rotates the blades, and a controller connected to the generator and configured to deliver a flow of current to the generator that is sufficient to move the blades from the retracted position toward the fully deployed position and insufficient to move the blades all the way to the fully deployed position.

Abstract: Described herein are various systems and techniques for deterring wildlife from an area proximate a windmill. A flying wildlife emitter may be utilized for such techniques. The flying wildlife emitter may output soundwaves to deter wildlife, such as birds or bats, from entering an area around the windmill. The flying wildlife emitter may include a speaker for producing sounds as well as a controller and sensors for determining conditions around the windmill and for controlling the sound produced by the speaker. An ultraviolet emitter may, additionally or alternatively, be utilized for such techniques. The ultraviolet emitter may be configured to emit ultraviolet light that may attract wildlife away from such areas proximate to the windmill.