Abstract: A hollow rotor core assembly for a wind turbine with at least one set of cylindrical stacks having a plurality of guiding vanes on the internal surface of the cylindrical stacks, having at least one set of air openings to accept airflow into the hollow rotor core for creating when in rotation a vortex inside the hollow rotor core, having at one end a partial blocking device as such to allow the exhaust of only a fraction of the peripheral portion of the vortex and to redirect the remaining central portion of the vortex towards the other end of the hollow rotor core where the bulk of the airflow will be exhausted from the hollow rotor core.

Abstract: A blade retention disk includes, on its external surface, a peripheral annular groove configured to receive a plurality of blade roots of the hammer attachment type, the peripheral annular groove including a loading orifice intended for the introduction of blade roots inside the peripheral annular groove. The retention disk also includes: a crown covering the peripheral annular groove; a crown centering device to center the crown, the crown centering device and the crown forming an air supply enclosure from the bottom of the peripheral annular groove; at least one orifice opening in the air supply enclosure, the orifice being configured to introduce cooling air into the air supply enclosure. The blade retention disk finds a direct application in the field of low pressure turbines for aircraft turbine engines.

Abstract: A blade arrangement is provided for a gas turbine, in which blade leaves, having a leading edge and a trailing edge and also a pressure side and a suction side, are assembled sealingly with platforms configured as separate components. A peripheral sealing arrangement is provided between the blade leaves and the associated platforms, which seals off an interspace between the blade leaves and platforms against hot gas flowing around the blade leaves. A directed site-dependent supply of cooling air for purging the sealing arrangement is provided on a side of the sealing arrangement which faces away from the hot gas. A method of operating the above blade arrangement is also provided. The method includes supplying cooling air for purging the sealing arrangement at a pressure which decreases from the leading edge of the blade leaves to the trailing edge.

Abstract: A multi-inlet vacuum pump has a first pump device (10) and a second pump device (12). The first pump device (10) includes a first rotor element (18) having a plurality of first rotor discs (20, 21) arranged consecutively in the delivery direction (36). The second rotor disc includes a second rotor element (26) having a plurality of second rotor discs (28) arranged consecutively in the delivery direction (36). A first fluid flow (34) is suctioned through a main inlet (32) by the first pump device (10) and delivered in the direction of the second pump device (12). A second fluid flow (40) is suctioned through an intermediate inlet (38) by the second pump device and delivered in the direction of a pump outlet. The diameter of the last rotor disc (21) of the first pump (10) substantially corresponds to the diameter of the first rotor (28) of the second pump device (12).

Abstract: A fluid turbine comprises a rotor rotatable in use about an axis transverse to the direction of fluid flow, the rotor having a first part carrying a plurality of arcuate blades that may be arranged selectably in compact straight shapes or in arcuate shapes and a second part journalled in a base structure by two or more bearings. Another aspect of the invention discloses an installation frame, devised to support the turbine or other elongated structures in a folded arrangement for transportation on a trailer, and to support assembly and erection thereof.

Abstract: A gas turbine engine has a rear mounting structure incorporating a mounting apparatus attached to a bypass duct wall with a link device of six rods for transferring core portion related inertia-induced loads, from an inner case of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.

Abstract: A method for estimating an operating temperature of component in turbo machinery includes providing body detachably affixed to component, operating machinery, stopping operation of machinery, and removing body. The method includes obtaining concentration profile by determining final concentration of at least one species in first material and in second material, and determining a transient concentration of at least one species between first material and second material. The method includes determining an operating temperature by correlating concentration profile to corresponding operating temperature for system. A system including body is also provided. Body includes at least one species, a first material having a starting first concentration of the species, a second material arranged to permit migration of the species from first material to second material. Species migrates from first material to second material during operation of turbo machinery allowing body to estimate temperature during operation.

Abstract: Method and rotor for a compressor. The rotor includes a solid first stub having a first end configured to engage with a corresponding bearing and a second end having a flange configured to be attached by bolts to a corresponding flange of a first impeller of the compressor; a tie rod configured to pass through the first impeller of the compressor; a nut being configured to engage a threaded region of the first end of the tie rod; and a solid second stub having a first end configured to receive the threaded portion of the second end of the tie rod and a second end configured to engage with a corresponding bearing. The tie rod does not contact the solid first stub.

Abstract: A system of operating a wind turbine that is capable of extending electricity production, such as in low and high wind speed environments. In accordance with various embodiments, a wind turbine speed maintenance system has a wind turbine with at least one turbine blade that has a trailing edge with a speed feature. The speed feature is connected to a controller and a pressure vessel, the controller selectively activating the speed feature in response to the turbine blade reaching a predetermined radial velocity.

Abstract: A turbo machine (1) comprises a casing (2) and a first volute tongue (12), an impeller (3) with at least one vane (4), and a flow splitter plate (5) comprising a second volute tongue (13) for splitting a flow of a fluidic medium produced by the impeller. The flow splitter plate comprises at least one opening (10) connecting the first surface (8) and the second, opposite surface (9) so as to reduce or eliminate vibrations.

Abstract: An inner shroud assembly includes an aft core segment mountable to a forward core segment to support a multiple of vanes for rotational movement relative thereto. A shroud backing plate segment engageable with the aft core segment and at least one fastener which passes through the shroud backing plate, the aft core segment and the forward core segment.

Abstract: A seal assembly disposed between a rotor and a stator especially of a turbo-machinery is provided with a close clearance gap there between. The clearance gap is bordered by a rotor surface at the side of the rotor and by a stator surface at the side of the stator. The rotor surface or the stator surface or both are provided with openings which open into at least one chamber arranged at the side of the openings turned away from the clearance gap.

Abstract: The present application provides a steam turbine system. The steam turbine system may include a high pressure section, an intermediate pressure section, a shaft packing location positioned between the high pressure section and the intermediate pressure section, a source of steam, and a cooling system. The cooling system delivers a cooling steam extraction from the source of steam to the shaft packing location so as to cool the high pressure section and the intermediate pressure section.

Abstract: A retaining ring presenting, on its periphery, a plurality of radial bores, each of the bores being able to receive a blade root. The retaining ring also includes at least one first radial opening traversed by a compression tube and at least one second radial opening, the at least first radial opening and the at least second radial opening being separated from each other by at least one of the bores of the plurality of radial bores. The ventilation device finds a particularly interesting application in the field of turbine engines including a pusher open rotor.

Abstract: A device for supporting and securing a piece of equipment on an aircraft engine or nacelle case, including a vibration damper including a first part secured to the case and a second coaxial part rigidly connected to the piece of equipment, the damper associated with a safety member configured to hold the damper in place on the case in the event of damper failure or breakage. The safety member, which is independent of the damper, is mounted astride the damper and secured to the case.

Abstract: A labyrinth seal is provided for forming a seal between a first and a second component which rotate relative to each other. The seal has an abradable lining mounted to the first component, and a plurality of fins projecting from the second component. The fins are arranged in abutment with the abradable lining to form a labyrinthal path for a flow of air through the seal. The seal further has a bypass passage which extends through the abradable lining. The bypass passage allows air to flow through the seal and bypass the labyrinthal path.

Abstract: A turbine for extracting power from a flowing fluid comprises a blade for interaction with the fluid, the blade being rotatable both about a primary axis and a blade axis. The blade axis is proximate to the blade, substantially parallel to the primary axis and spaced therefrom. Rotation actuating means is provided to rotate the blade about the blade axis in dependence upon the rotation of the blade about the primary axis such that the rotation angle of the blade about the blade axis is a function of the rotation angle of the blade about the primary axis. The rotation of the blade about the blade axis is in the same direction of rotation as the blade axis about the primary axis.

Abstract: A gear arrangement is disclosed herein. The gear arrangement includes a housing. The gear arrangement also includes a plurality of gears at least partially disposed in the housing and engaged with respect to one another. The gear arrangement also includes a support post mounted to the housing. The support post supports at least one of the gears. The support post has a first portion extending away from the housing and encircled by one of the gears. The support post also has a pin projecting away from the first portion. The first portion and the pin are eccentric to one another such that the first portion is centered on a first axis and the pin is centered on a second axis. The first and second axes are parallel to and spaced from one another. The gear arrangement also includes a plurality of pin apertures defined by the housing.

Abstract: A stationary blade and a steam turbine capable of reducing self-excited vibrations with a simple configuration are provided. A stationary blade has a cavity, extending in a blade-width direction, formed therein and slits communicating between the cavity and the outside. A wave-shaped plate spring that is in sliding contact with at least one of a pressure-side member and a suction-side member is provided between the pressure-side member, which is a portion on the pressure side of the cavity, and the suction-side member, which is a portion on the suction side of the cavity. When the stationary blade is elastically deformed, the wave-shaped plate spring causes friction between itself and at least one of the pressure-side member and the suction-side member. This friction attenuates relative positional displacement between the pressure-side member and the suction-side member. Thus, self-excited vibrations occurring at the stationary blade can be reduced.

Abstract: A hydrocarbon presence sensor used to detect for the presence of a fuel in a buffer cavity of an inter-propellant seal. A sensor is formed on a rotor shaft in the buffer cavity and an optical imaging device is used to view a change in appearance of the sensor when a hydrocarbon forms on the surface. The sensor is formed from either an oil/fuel leak detection powder or an oil colorimetric developer. A white light source or a laser is reflected off of the sensor and an optical imaging device reads the reflected light to detect for a change in color or intensity of the light to indicate if a hydrocarbon is present on the sensor surface.