Abstract: A device for circulation of air for a turbomachine, the device including an inlet provided to receive incident airflow, air circulation ducts connected to the inlet, a central part including side walls, peripheral walls arranged at a distance from the central part, so as to form the air circulation ducts, each duct being arranged between one of the side walls of the central part and one of the peripheral walls, each peripheral wall including an upstream end portion delimiting with one of the side walls an inlet orifice of one of the ducts and a downstream end portion delimiting with one of the side walls an outlet orifice of one of the ducts, at least one member mobile in translation relative to the peripheral walls, the at least one mobile member being formed in the central part and arranged so that its displacement varies a section of each of the inlet orifices and a section of at least one of the outlet orifices.

Abstract: A turbine blade includes a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides. An airfoil extends radially outwardly from the platform to a free tip end. The airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides. A root extends radially inwardly from the platform. The platform and the airfoil include film cooling holes arranged in substantial conformance with the Cartesian coordinates set forth in Table 1 herein. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).

Abstract: A gas turbine sealing assembly includes a first static gas turbine wall, a second static gas turbine wall, and a leaf seal having a first side and a second side. The first static gas turbine wall contacts the second side at a first position, and the second static gas turbine wall contacts the second side at a second position. A spring exerts force on the first side. The spring includes a first spring wall coupled to the first static gas turbine wall. A second spring wall extends radially outward from the first spring wall. A third spring wall extends axially away from the second spring wall. A fourth spring wall extends radially inward from the third spring wall and includes a radially inner end. The radially inner end of the fourth spring wall contacts the first side of the leaf seal between the first position and the second position.

Abstract: An inner platform structure of a stator vane for a gas turbine engine includes a male circumferential side opposite a female circumferential side, the male circumferential side includes a male wall received at least partially within a female wall of a neighboring stator vane at an interface with a pad at the interface.

Abstract: A gas turbine engine has a fan nacelle and a core nacelle arranged to provide a bypass flow path. A compressor section is provided within the core nacelle. A heat exchanger is arranged within a duct. The heat exchanger is configured to receive bypass flow from the bypass flow path. The duct is in fluid communication with the compressor section and is configured to pass bleed air through the heat exchanger.

Abstract: A vane pack assembly (14) for a variable turbine geometry turbocharger is a stand-alone assembly and can be assembled and transported apart from the turbocharger. The vane pack assembly (14) includes a plurality of guide vanes (16) spaced apart in a circumferential direction and a plurality of pivot centers (38). Each one of the pivot centers (38) corresponds with one of the guide vanes (16). A location of the pivot centers (38) relative to the guide vanes (16) changes as an angular position of the guide vanes (16) is adjusted.

Abstract: An axial fan comprises a hub and a plurality of blades extending from the hub; wherein each blade comprises a main blade portion and a secondary blade portion and the secondary blade portion has a leading edge adjacent to a leading edge of the main blade portion and forms a flap for the main blade portion; wherein a fluid passage is defined between the leading edge of the main blade portion and the leading edge of the secondary blade portion; wherein the main blade portion has a main chord and the secondary blade portion has a secondary chord; and wherein the main chord and the secondary chord form a relative attack angle comprised between 5° and 35°.

Abstract: An example turbomachine bushing a bushing having a wear surface configured to interface directly with a variable vane assembly to limit radially inward movement of the variable vane assembly, wherein the variable vane assembly is moveable axially between a first position contacting the wear surface and a second position spaced from the wear surface.

Abstract: Compliant coupling systems and methods are provided for coupling a shroud to an engine casing. The complaint coupling system includes a retaining ring adapted to be positioned adjacent to the shroud and adapted to be coupled to the engine casing. The retaining ring defines a coupling channel about a circumference of the retaining ring and at least one notch that interrupts the coupling channel. The complaint coupling system also includes a first clip received within the coupling channel. The first clip has a biasing portion that extends into a space defined by the at least one notch, and the biasing portion is adapted to contact the shroud. The complaint coupling system includes a second clip received within the coupling channel. The second clip has a bumper portion that extends into the spaced defined by the at least one notch, and the bumper portion is adapted to contact the shroud.

Abstract: A turbine engine including a turbine shroud for positioning radially outside of blades of the turbine rotor. The turbine shroud includes a carrier, a retention assembly, and a blade track. The blade track is clamped by the retention assembly, and the retention assembly is supported by the carrier.

Abstract: A method of replacing a fan case liner panel in an engine fan case is provided. In one illustrative form, the method may include applying heat to an engine fan case to debond an adhesive layer, removing the first fan case liner panel, and bonding a second fan case liner panel.

Abstract: A horizontal-shaft wind machine having improved low wind speed performance and greater overall efficiency consists of multiple rotors, wherein each successive rotor is larger in diameter than the previous rotor moving from the most windward rotor to the most leeward rotor. Each rotor may be coupled to a separate concentric shaft, and all rotors may rotate in the same direction with the output shafts of each rotor coupled via an overrunning clutch to a single shaft, the output of which is used to drive the load. Winglets attached to the leading edge and tip of the rotor sails improve low wind startup torque.

Abstract: A compressor of a gas turbine engine includes a plurality of rotors rotatable about a central longitudinal axis, a plurality of stators, and a circumferential inner case wall located outwardly of the plurality of rotors and the plurality of stators. The inner case wall includes a plurality of first slots located in a first section of the circumferential inner case wall and a plurality of second slots located in at least one second section of the circumferential inner case wall. A first area of each of the first slots is greater than a second area of each of the second slots. A circumferential manifold is located outwardly of the inner case wall including a port. At least one of the plurality of second slots is located proximate to the port.

Abstract: The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. The rotor disk assembly further comprises a second rotor disk operatively coupled to the first rotor disk, an inter-disk device disposed on the second rotor disk and extending axially toward the first rotor disk, and a boss disposed on the first rotor disk, wherein the boss protrudes axially from the web toward the inter-disk device.

Abstract: A wind turbine blade assembly includes a rotary shaft, and a plurality of blade units connected to the rotary shaft and angularly spaced apart from each other. Each blade unit includes a grid frame connected to the rotary shaft and formed with a plurality of grid spaces, a plurality of blade panels swingably connected to the grid frame and corresponding in position to the grid spaces, and a plurality of counterweight members respectively disposed on the swing ends of the blade panels. Each counterweight member includes a soft hollow main body and a counterweight fluid accommodated in the main body.

Abstract: The present invention provides improved methods, apparatus, and manufacture for an Archimedes Screw using a strake design as a blade to increase the volume of water raised or lowered by about 10%. The invention, in part, alters the shape of the blades within the screw from a helicoid shape to a strake shape. A helicoid blade in an Archimedes Screw has been used since antiquity and has not changed since then, limiting the efficiency and manufacturing process. The strake shape allows a greater quantity of water to be contained within the screw and is a developable surface that enables easier fabrication than the helicoid shape.

Abstract: A bottom surface of a housing recess of a turbine housing includes a close attachment portion in a continuous annular land shape, which is located radially outside a fitting recess. The close attachment portion is closely attached to a portion radially outside first support holes in a surface of a shroud ring opposite from its facing surface, by a fastening force of attachment bolts. The first support holes in the shroud ring communicate with an outlet side of a turbine impeller through a connection path and a cutout.

Abstract: A method of fabricating a thermoplastic composite tubular structure for use as a wind turbine blade is presented using a combination of induction heating with smart susceptors to consolidate a wrapped mandrel. The method can include overbraiding the mandrel with a continuous fiber thermoplastic composite material to form an overbraided mandrel that is then installed in a ceramic induction oven where the mandrel is pressurized internally to consolidate the thermoplastic overbraid during heating.

Abstract: A balancing kit and balancing method is provided for balancing a rotating component. The balancing kit comprises a receptacle and a balancing mass. The balancing mass comprises a pin that may be passed through a corresponding slot in a plate of the receptacle during installation. To complete installation, the balancing mass is rotated so that the pin can no longer pass through the slot, and is instead retained in an installed position in which the pin rests on a lower surface of the plate. The balancing mass can be removed by the reverse process.

Abstract: Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section.