Abstract: A turbomachine intermediate casing including an internal hub designed to accept a turbomachine compressor shaft, an outer shell ring, and a plurality of radial arms connecting the hub and the shell ring, one of the arms including an internal housing of radial shaft for driving auxiliary machines, the casing further includes a bevel gearbox for the radial shaft arranged in the outer shell ring, the gearbox being formed as one with the outer shell ring, and the bevel gearbox includes a housing for gears between a radial shaft and an accessories gearbox, the housing including an opening opening to the periphery of the outer shell ring.

Abstract: Provided is a wind turbine for generating electric energy using wind power, and more specifically, a wind turbine having a nacelle fence for improving aerodynamic performance by mounting a fence structure on the nacelle of a horizontal axis wind turbine. The wind turbine having a nacelle fence decreases the vortex that is generated at the downstream ends of rotating blades so as to improve the aerodynamic performance of the blades, and increases the power coefficient of the wind turbine.

Abstract: A turbocharger housing has a valve device. The valve device is formed with at least one first duct section and a second duct section. The two duct sections are arranged with their longitudinal axes parallel to one another and they are formed without any undercuts.

Abstract: A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine static structure and configured to cooperate with the first member to limit movement of the geared architecture relative to the static structure. A fan drive gear system and method are also disclosed.

Abstract: An attachment that attaches to the trailing edge of a ceiling fan blade has a curved and flexible dam that curves rearwardly from the trailing edge and downwardly from a lower surface of the fan blade. When the ceiling fan is operational and fan blades are rotating, the curved dam interacts with the air moved by the fan blade and directs the air in a downwardly direction toward the occupants of the room where the fan is installed. At increased fan speeds, the dam flattens out, decreasing any additional load placed on the motor of the fan by the downwardly curved dam. One attachment is attached to each of the blades of the fan.

Abstract: A seal segment is positioned, in use, radially adjacent the rotor. The seal segment has first and second circumferentially spaced passageways each of which extends in the fore and aft direction. In use, a first support bar is contained within the first passageway, and a second support bar is contained within the second passageway. The first and second support bars being mountable to complementary formations provided by the casing of the engine. The first passageway is configured such that the seal segment is fixed relative to the first support bar in the radial and circumferential directions. The second passageway is configured such that the seal segment is fixed relative to the second support bar in the radial direction but allows relative movement of the seal segment and the second support bar in the circumferential direction to accommodate differential thermal expansion of the seal segment and the casing.

Abstract: An induced draught fan, including: a motor, the motor including a shaft; a volute; and a wind wheel. The volute is provided with an air intake and an air outlet. The wind wheel is arranged inside the volute. The top of the volute is provided with a through-hole. The shaft of the motor passes through the through-hole and is connected to the wind wheel. A seal ring is arranged on the volute corresponding to the through-hole. An outer side of the seal ring is provided with an annular groove. The volute is embedded in the annular groove. The middle of the seal ring is provided with a center hole. The middle of the side wall of the center hole is provided with a ring-like convex edge. The shaft passes through the center hole and contacts with the ring-like convex edge.

Abstract: A device for providing a grounding path between an outer surface of a gas turbine aircraft engine and an inner surface of a gas turbine aircraft engine uses a structural guide vane (SGV) with a nonconductive coating on the surface. Bolts are put in bolt holes that have a bolt receiving cavity without the nonconductive coating. A washer and bolt are used so that attachment of the SGV to a surface provides a ground path from the SGV through the bolt, washer and nut for electrical engagement with a surface to which the bolt attaches the SGV.

Abstract: A blade for use in water, the blade comprising an outer shell of fiber reinforced plastic defining a cavity. A substantial portion of the cavity is filled with a resin which adheres to the inner wall of the shell.

Abstract: An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.

Abstract: An annular seal positionable in a gap is disclosed herein. The annular seal includes a plurality of leaves positioned about a center axis. Each leaf extends to a distal end that is elastically deflectable relative to the center axis to accommodate changes in a size of the gap. The annular seal also includes a ring encircling the center axis and at least partially interconnecting the plurality of leaves together for concurrent installation and removal. The annular seal also includes a plurality of tabs projecting from the ring along the center axis. Each of the tabs is directly connected to at least one of the plurality of leaves such that elastic deformation of one of the plurality of leaves induces bending in the corresponding tab before inducing bending in the ring.

Abstract: In order to increase the flexibility of the positioning of a stacked computer system within a data center, a removable fan unit is positioned within the stacked computer system. The removable fan unit includes a housing and a fan housing rotatably attached to the housing. The fan housing supports a fan that is electrically connected to a connector on a side of the housing of the removable fan unit. The connector of the removable fan unit may be electrically connected to a computer system-side connector. The fan housing may be rotated into at least two different orientations relative to the housing of the removable fan unit, such that the removable fan unit moves air through the stacked computer system in at least two corresponding directions.

Abstract: An airfoil in a gas turbine engine includes an outer wall and an inner wall. The outer wall includes a leading edge, a trailing edge opposed from the leading edge in a chordal direction, a pressure side, and a suction side. The inner wall is coupled to the outer wall at a single chordal location and includes portions spaced from the pressure and suction sides of the outer wall so as to form first and second gaps between the inner wall and the respective pressure and suction sides. The inner wall defines a chamber therein and includes openings that provide fluid communication between the respective gaps and the chamber. The gaps receive cooling fluid that provides cooling to the outer wall as it flows through the gaps. The cooling fluid, after traversing at least substantial portions of the gaps, passes into the chamber through the openings in the inner wall.

Abstract: A fan for an aircraft turbine engine, including an intake cone including a balancing system including a plurality of mass accommodation holes and at least one balancing mass mounted in one of the holes. The balancing system further includes an attachment mechanism exerting pressure that flattens the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone.

Abstract: A turbine driving a planet gear and an epicyclic gear train and including a planet pinion cage and a ring driving two propellers in rotation, is connected to the planet gear through a flexible sleeve surrounding a turbine support shaft rather than through a support shaft itself to achieve a flexible assembly with a limit stop position in contact with the shaft to limit parasite internal forces applied to the epicyclic gear train without tolerating a loose assembly or breakage of the sleeve due to a condition of the limit stop after a clearance has been eliminated.

Abstract: A concave (a relief portion) is formed along a circumferential direction of a rotor in a trailing-edge end surface of a platform. In the trailing-edge end surface disposed outside of the relief portion in the radial direction of the rotor an opening of a cooling channel is provided. The end surface is formed thicker in the radial direction of the rotor at the opening of the cooling channel than at a position corresponding to a trailing-edge end of a hub of an airfoil portion connected to the platform.

Abstract: A support bar for a steam turbine nozzle assembly is disclosed. In one embodiment, the support bar includes a hook-shaped portion for engaging a lip portion of a steam turbine diaphragm, wherein the steam turbine support bar is configured to non-affixedly join a steam turbine casing to the steam turbine diaphragm.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: A centrifugal pump for delivering hot fluids, having a contacting shaft seal, a seal housing (13) for the shaft seal (14), and a return line (8) for a partial flow of the delivered fluid, in which no delivered fluid is discharged out of the seal housing (13); a separate housing cover (9) is disposed between the seal housing (13) and the pump housing (1); there is a contact surface which minimizes heat transfer between the seal housing (13) and the housing cover (9); and the return line (8) is connected to the housing cover (9) and/or to the pump housing (1).

Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, ?, and exit angles, ?. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, ?, and exit angle values, ?, set forth in one of Tables 1, 3, 5 and 7.