Abstract: The present application provides an abradable bucket shroud for use with a bucket tip so as to limit a leakage flow therethrough and reduce heat loads thereon. The abradable bucket shroud may include a base and a number of ridges positioned thereon. The ridges may be made from an abradable material. The ridges may form a pattern. The ridges may have a number of curves with at least a first curve and a second curve and with the second curve having a reverse camber shape.

Abstract: An airfoil has a hollow shell providing external airfoil surfaces, and a corrugated core within the shell. The core contacts inner surfaces of the shell to support the shell. The airfoil is formed by consolidating a hollow shell pre-form and a corrugated core pre-form. At least a part of the hollow shell has a leading edge shell portion and/or a trailing edge shell portion which, before consolidation of the pre-forms, is a unitary body having a shape which wraps around the respective edge.

Abstract: The present invention provides a pitch drive apparatus of a wind generator and the wind generator constituted not to affect a main shaft or a gear box, and capable of preventing reliability from being deteriorated. The pitch drive apparatus includes a wind turbine blade (6) having a base portion (21) mounted so as to be turnable around an axis center L with respect to a rotor head (4), an electric drive member having an output shaft (19) mounted on the rotor head (4) so as to extend in a direction along the axis center (L), a lever (15) having one end fixed to the output shaft (19) and extending in a direction intersecting with the output shaft (19), and a connecting link (17) disposed so as to extend in a direction intersecting with the output shaft (19). One end of the connecting link (17) is rotatably mounted on a free end of the lever (15) and the other end of the connecting link (17) is rotatably mounted on a drive position P of the wind turbine blade (6).

Abstract: A steam turbine singlet nozzle airfoil with integral outer sidewall is engaged with an inner ring and an outer ring in a nozzle assembly. The interface of the outer sidewall with the outer ring may include a plurality of mechanical hooks on one or both of the upstream face and the outer radial face of the outer sidewall that engage with complimentary structures on the outer ring. The outer interface may further include low energy welds along limited distances of one or both of the upstream or downstream interface of the outer sidewall and the outer ring. An inner radial end of the singlet nozzle airfoil is pinned into position and fastened to the inner ring. Without a need for high heat welds, distortion of the airfoil and the steam flow path and the associated rework is eliminated and stage performance is improved.

Abstract: A first seal member includes a double-structure bellows in corrugated form, and vibration control device provided on the outside of the bellows such as to cover part of the bellows. A flat portion that is not in corrugated form is provided in part of the bellows. The vibration control device is provided in circumferential direction on an outer surface of the flat portion, and made up of a ring-shaped rib having a plurality of holes in a circumferential direction and weights inserted in the holes provided in a wall of rib. Natural frequency is adjusted by adjusting the number of weights, thereby preventing resonance between the natural frequency of the first seal member and the rotational frequency of rotor from occurring.

Abstract: A thrust bearing shaft has an enlarged disk at one axial end to provide a rotating surface in a thrust bearing. A first cylindrical portion extends from the disk. A second cylindrical portion has a smaller diameter than the first cylindrical portion and extends from the first cylindrical portion to an end of the thrust shaft remote from the disk. The thrust shaft has a hollow bore with a ledge extending across the bore at a location within the first cylindrical portion. The ledge is formed with a central hole of a first hole diameter, and twelve air holes spaced circumferentially about the central hole. The twelve holes are formed of a second hole diameter, with a ratio of the first hole diameter to the second hole diameter being between 2.55 and 2.71. In addition, a bearing assembly, a compressor, and a method of assembling a compressor are disclosed.

Abstract: The invention relates to a locking device (13) that includes at least one locking system (16), intended to be placed on a first moving element (11), and a retaining member (17), intended to be placed on a second moving element (12), the locking system (16) having a first hook (18) designed to engage with the retaining member so as to lock the locking device (13). The locking system (16) includes at least a second hook (19) set back from the first hook (18) so as to engage with the retaining member in the event of the first hook (18) breaking.

Abstract: A thrust bearing shaft has a radially enlarged thrust disk to be mounted between two static housing surfaces in an air cycle machine. A first portion of the thrust bearing shaft extends from a first face of the thrust disk. A second portion extends from a second opposed face of the thrust disk. The second portion has sealing ribs and six holes. The sealing ribs are spaced closer to the thrust disk than are the holes. A ratio of a distance from an end of the second portion to a center of the holes compared to a distance from the end of the second portion to the second face of the thrust disk is between 0.20 and 0.22. In addition, an air cycle machine incorporating the thrust bearing shaft, and a method of assembling the thrust bearing shaft into an air cycle machine are disclosed.

Abstract: A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor.

Abstract: A gas turbine is provided. The gas turbine includes at least one rotor, having rotor blades arranged on the periphery of rotor disks in a plurality of radial planes, and a tie-bolt extending along slots in the rotor disks and holding the rotor disks together as a unit. At least one annular spacer for fixing the position of the tie-bolt in relation to the center line of the rotor disks is also provided. The spacer includes through-openings that are arranged radially in relation to the tie-bolt or to its center line and that extend coaxially.

Abstract: A steam turbine apparatus is disclosed. In one embodiment, the steam turbine apparatus comprises: an exhaust shell portion including: a first section having a semi-circular cross-section; an exhaust section contiguous with the first section, the exhaust section including an intermediate-pressure exhaust outlet; and a second section having an oblate spherical cross-section including a substantially flattened portion, the second section configured to fluidly connect with the first section, wherein the first section and the second section form a continuous steam flow path.

Abstract: A balancing assembly for a rotor assembly of a gas turbine engine includes a flange engaging portion defining a flange receiving opening for mating with the flange in a slidable manner. A hole extends through at least part of the flange engaging portion, the hole corresponding in size to a recess and adapted to receive a rivet or other suitable fastener to fix the balancing weight with respect to the disc.

Abstract: A one-piece air exit port baffle for containment for an air start turbine includes a circular arc section with a circumferentially corrugated circular arc section and a flange section. The circumferentially corrugated circular arc section has a plurality of openings. The flange section is axially adjacent to the circumferentially corrugated circular arc section and configured for attachment adjacent to an air exit port of an air turbine starter.

Abstract: A turbomachine compressor including variable-pitch vanes, each including an airfoil connected via a plate of circular outline to a pivot guided to pivot in an orifice in a casing, the plate including an air feed duct including one end for communication with a passage formed in the casing when the vane is in a first position, so as to inject air into the annulus of the compressor upstream from the vane, and to be closed by the casing when the vane is in a second position.

Abstract: A yawing system for a wind turbine with a tower construction and a nacelle includes a stationary part associated with the tower construction, and a rotating part being associated with the nacelle. The rotating part is allowed to rotate relative to the stationary part via a gear connection. The rotating part includes a plurality of modules, each having a sub-module, the sub-modules substantially identical in size and shape. Each module is configurable to perform various functions by positioning one or more function defining elements in the corresponding sub-module. Thereby a configured module belongs to a category of modules reflecting the function of the configured module. A module belonging to a category may be replaced or reconfigured to belong to a different category of modules without altering the main design of the rotating part.

Abstract: Provided is a turbine blade cascade endwall that is capable of suppressing a vortex generated on a suction surface of a turbine stator blade and that is capable of reducing secondary-flow loss due to this vortex. A turbine blade cascade endwall that is positioned on a tip side of a plurality of turbine stator blades arranged in a ring form is provided with a pressure gradient alleviating part that alleviates a pressure gradient generated in the blade height direction at a suction surface of the turbine stator blades due to a clearance leakage flow, leaking out of a gap between a tip of a turbine rotor blade located on the upstream side of the turbine stator blades and a tip endwall disposed facing the tip of this turbine rotor blade.

Abstract: A steam supply for a turbomachine with an inner housing and an outer housing is provided. The steam supply includes an inner pipe and an outer pipe, a cooling medium inlet opening disposed in the outer pipe and a cooling medium entering thereby into space between the inner pipe and the outer pipe, and the inner pipe being cooled thereby.

Abstract: A system of counter-rotating propellers for an aircraft turbine engine including a first and a second propeller, each including a stalling control system for the blades, a rotating actuating mechanism for sliding an element to move the angle of attack of the blades, and a disengaging mechanism for rigidly fixing in rotation the rotating actuating mechanism. The system is designed so that when the disengaging mechanism is engaged, a relative rotation speed is created between the elements and the associated rotating actuating mechanism thereof, bringing the blades into a neutral position thereof for feathering.

Abstract: An airfoil includes a leading edge, a trailing edge, a suction side and a pressure side; a plurality of internal cooling cavities extending radially within the airfoil, one of the plurality of internal cavities extending along the trailing edge. The trailing edge is provided with a plurality of coolant exit apertures extending therealong. A plurality of vortex generators is formed on an internal surface of at least one of the pressure and suction sides of the airfoil. The vortex generators are arranged in radially spaced relationship in one of the plurality of internal cooling cavities, extending substantially parallel to and in proximity to the plurality of coolant exit apertures.

Abstract: The invention relates to a vane (200) for an aircraft turbine engine receiver. The vane is a blade (14) having an aerodynamic shell (24) enveloping a principal hollow structure core (34) extending in the direction of wingspan of the blade. The vane further has a secondary structural assembly (34?) enveloped by the hollow core (34) and extending also in the direction of wingspan, as well as a first coating made of shock-absorbing material (50) arranged between a longeron (44) of the core (34) and the assembly (34?), and a second coating made of shocking-absorbing material (52) arranged between another longeron (38) of the core (34) and this same assembly (34?).