Abstract: The invention relates to the fastening of rotor blades to the rotor hub of wind turbines using transverse pins and tension rods in the region of the blade root. The transverse pins are arranged throughout the entire blade root shell wall and can be connected to a flange of the hub by the tension rods in the form of expansion screws. Each transverse pin (4) can be connected to the flange (2) of the rotor hub (1) by two tension rods (5, 6). Each tension rod (5, 6) is arranged in a separate tension rod bore (7, 8) in the blade root shell wall (3).

Abstract: A mastless vertical axis wind turbine that comprises a plurality of sails that rotate about a vertical axis under the influence of wind. A platform is connected to and in tension with the plurality of sails at one or more points about the bottom of the plurality of the sails. Also, an external frame is connected to and in tension with the plurality of sails at one or more points about the top of the plurality of the sails. The external frame itself comprises a plurality of legs that converge above the plurality of sails at a central point about the vertical axis of rotation and extend beyond the path swept by the plurality of sails. A coupling mechanism connects one or more of the plurality of legs to the plurality of sails and allows the sails to rotate about the vertical axis of rotation while the legs remain stationary.

Abstract: An airfoil profile-shaped seal is disposable between an inside surface of a hollow airfoil body and a seal support. The seal includes an elongated member defining a generally closed curve having a generally straight portion, a generally curved portion, and having a solid cross-section across and along the length of the elongated member. When the seal is disposed in an airfoil profile-shaped groove of a seal support adjacent to the inner surface of the hollow airfoil body, and a fluid pressure on one side of the seal is greater than a fluid pressure on the other side of the seal, portions of the seal engage the inner surface of the hollow airfoil body and a surface of the groove to form a seal to inhibit leakage of fluid from the one side to the other side.

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal between the mate face of the first engine component and the mate face of the second engine component. The seal establishes three points of contact with each mate face in at least one condition.

Abstract: A fan includes an impeller and a frame. The frame is used for accommodating the impeller. The frame includes a plurality of static blade groups. Each of the static blade groups has a plurality of static blades. Moreover, at least one first static blade of a first static blade group and at least one first static blade of a second static blade group are symmetric with respect to a central axis of the frame.

Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A first flap is arranged diagonally between the tangential strut and the outer cylindrical surface or the inner cylindrical surface where the first flap minimizes vortex shedding of the fluid flow from the tangential strut.

Abstract: A compressor of a gas turbine engine includes at least one rotor, and at least one stator, wherein the at least one stator includes a water channel wall located on a surface of the stator, wherein the water channel wall is configured to direct water away from a center line of the turbine engine and is located an offset distance from an outside wall of the compressor, wherein the offset distance is zero percent to twenty percent of the span of the stator.

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract: A gas turbine engine mid-turbine frame includes an annular case that has a hole. A tie rod with a first end extends through the hole. The first end includes a threaded portion. A nut is secured to the threaded portion to clamp the tie rod to the annular case. A tab washer is arranged between the nut and the annular case. The tab washer interlocks the nut to the case to prevent relative rotation therebetween.

Abstract: The invention refers to a system and method for reinforcing a weakened area of a wind turbine blade whose interior comprises a box beam extending from the blade root to the blade tip and wherein said box beam comprises an open end at the blade root. The system is characterized by comprising a repair module (100) adapted for moving inside the box beam and transporting a reinforcement element (107) from the blade root to the weakened area; and by the repair module (100), which is adapted for applying the reinforcement element (107) onto a interior surface of the box beam in the weakened area.

Abstract: An assembly can include a turbocharger center housing that includes a through bore and a counterbore positioned between a compressor end and a turbine end of the through bore where the through bore includes a sleeve mating surface positioned between the compressor end and the counterbore and a turbine side bearing lubricant film formation surface positioned between the counterbore and the turbine end; and a sleeve positioned at least in part in the through bore of the turbocharger center housing between the compressor end and the counterbore where the sleeve includes a locating flange and an axial extension that extends from the locating flange where the axial extension includes an outer mating surface, an inner compressor side bearing lubricant film formation surface, a compressor side axially facing spacer surface and a turbine side axially facing spacer surface.

Abstract: The disclosure provides a fan assembly for connecting the first fan to the second fan. The fan assembly includes at least one fastening member. Each of the first fan and the second fan includes a first flange and a second flange and a body interconnecting the first flange and the second flange, the fastening member includes a locating column and an elastic element. The elastic element is held between the first flange of the first fan and the second flange of the second fan, the locating column passes through the elastic element, the first flange of the first fan, and the second flange of the second fan, to connect the first fan to the second fan.

Abstract: A propeller assembly is provided including a plurality of blades arranged in diametrically opposed pairs. Each of the plurality of blades has an electrical deicer located thereon. The propeller assembly also includes a slip ring, and a stationary brush arranged in contact with the slip ring. The brush is configured to transfer electrical power from a power source to the slip ring. A movable portion of an actuator is configured to sequentially couple the electrical deicers of each pair of blades to the rotating slip ring.

Abstract: An air guide element of an aircraft gas turbine, including an external housing that is provided with an inflow opening, as well as with a flow channel that is arranged inside the housing, characterized in that a tubular intermediate element that is made of an elastic material is arranged inside the inflow opening, connecting the inflow opening to the flow channel in a sealing and position-adjusting manner.

Abstract: A casting method for obtaining a part that includes a tapering portion, and a turbine engine blade obtained by casting and including a tapering trailing edge, are provided. The method includes: providing an insert element having a tapering section; making a shell around the insert element; and casting a molten material into the shell including the insert element.

Abstract: A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.

Abstract: A blower assembly includes a housing having a scrolled wall, a motor having an output shaft extending within the housing, an impeller positioned within the housing and mounted to the output shaft for creating an airflow along an airflow path within the housing, an airflow outlet, and a scroll cut-off. The scroll cut-off is a membrane positioned between the scrolled wall and the air flow outlet, and forms a substantially continuous surface with the scrolled wall and with the airflow outlet, along the airflow path. In a first position, the membrane is substantially taut and in a second position, the membrane is relaxed. Alternatively, the membrane is inflatable via a valve in fluid communication with the membrane.

Abstract: A compressor intake mixer system for internal combustion gas engines having a compressed charge bypass system comprises a bypass charge and fuel pre-mixer connected in line with the charge bypass system to reduce pressure gradient between the high pressure bypass charge and the low pressure fuel. A single volume main mixer is connected to the compressor inlet downstream of the pre-mixer to mix the flow of premixed charge and air and provide a mixed gas to the compressor inlet. Thus a need for a separate volume for a fuel mixer and a bypass mixer is eliminated and a single volume is provided at the compressor inlet. The locational constraint of necessarily locating the volumes at the compressor inlet is also obviated by providing a pre-mixer.

Abstract: A vane carrier is provided for a compressor or a turbine section of an axial turbo machine, especially one of a gas turbine, steam turbine, compressor, expander, comprises least a first and second functional means. The first functional means is a cylinder made of a material with a coefficient of thermal expansion (CTE) below 1.3×10?5 [1/K]. The cylinder is provided for carrying a plurality of vanes on its inner side. The second functional means is a support structure made of a material different to and less expensive than the material of said first functional means. The support structure is provided for defining an axial and lateral position of the first functional means within an outer casing of the axial turbo machine.

Abstract: A rotor disc for a vacuum pump, in particular a turbo molecular pump, having an inner ring. The inner ring is connected to a plurality of blade elements extending radially outward. The inner ring has at least one expansion joint. For assembly, the inner ring can be surrounded by a retaining ring and arranged on a hollow cylindrical carrier element as applicable.