Abstract: The present invention relates to a control system for a wind turbine, comprising an electrical device that is arranged for being used during normal operation of a wind turbine and a power source that is arranged to be used as an emergency power supply to a blade pitch motor, wherein the blade pitch motor is arranged to test at least one property of said power source. The invention also relates to a method for testing a power source.

Abstract: A steam turbine having a fork-type joint structure is provided that secures sufficient strength for endurance of stress corrosion cracking, low-cycle fatigue, and high-cycle fatigue, and extends an operating life while making it possible to endure long-term operation. The turbine includes a rotor having a plurality of rotor forks rowed in an axial direction; a turbine blade having blade forks arranged in the axial direction of the rotor, the blade forks engaged with the rotor forks; a plurality of pin holes whose positions are different from each other in the radial direction of the rotor; and a plurality of fork pins inserted into the plurality of pin holes in the axial direction of the rotor. A clearance exists between an inner diameter of the pin hole of the blade fork and a diameter of the fork pin, the clearance varying depending on positions in the axial direction of the turbine.

Abstract: The present application provides a seal carrier for use about a number of flow orifices of a platform of a turbine nozzle. The seal carrier may include an inner surface facing the platform with the inner surface having a number of slots therein aligning with the flow orifices of the platform and an opposed outer surface with a seal positioned about the outer surface.

Abstract: The present disclosure relates to a rotor for a wind turbine (1), having a rotor hub (8), having at least one rotor blade (9) mounted on the rotor hub (8) so as to be rotatable about a blade axis (11). At least one threaded spindle mechanism (13) is positioned between the rotor hub (8) and the rotor blade (9) and is connected both to the rotor hub (8) and the rotor blade (9). The rotor blade (9) is adapted to be rotated relative to the rotor hub (8) about the blade axis (11) by means of an actuation of the threaded spindle mechanism (13). The threaded spindle mechanism (13) has a drive (22), an actuating element (31), a spindle nut (18) detachably coupled to the actuating element (31), and a threaded spindle (19) which can be rotated about the longitudinal axis (25) thereof by means of the drive (22) and which is detachably coupled to the drive (22), such that the threaded spindle (19) and the spindle nut (18) can be separated from the threaded spindle mechanism (13).

Abstract: A wind turbine having a set of curved blades mounted on a central rotatable hub. Each of the blades has a defined pitch angle, to a rotational axis of the hub, along the blade from the hub to the tip. A curve is provided on the wind contact surface along each of the blades over the blade surface from the leading edge of the blade to the trailing edge of the blade by an amount between about 6 and about 24 degrees. The defined pitch angle from any point along the leading edge of the blade being defined by the arc-sine of a ratio of blade velocity to apparent wind velocity, with a variance of ±30 percent of the complementary angle to the arc-sine; and apparatus for varying the velocity of the blade to control power output so that it is within fifteen percent of maximum obtainable power of the blade most distant from the hub.

Abstract: Methods, systems and apparatus for cleaning turbines, such as power generation turbines, are disclosed. Supplemental piping is connected to existing compressor air extraction and turbine nozzle cooling air piping, to supply water and/or cleaning agents into areas of a turbine not ordinarily accessible by injection of water and/or cleaning agents into the bellmouth of the turbine alone. Pressure and flow sensors, pumps, valving, and a control system to regulate the operation of the pumps and valving are provided to control the introduction of water and/or cleaning agents into the turbine.

Abstract: A turbine blade for a gas turbine engine is disclosed. The turbine blade can include at least one internal cooling path, and an internal vane disposed in the at least one internal cooling path. The internal vane can include a central portion, a first leg extending in a first direction from the central portion, and a second leg extending in a second direction from the central portion. The central portion can have a thickness greater than a thickness of the first leg or a thickness of the second leg.

Abstract: A coupling pin for use in a pump housing, the pump housing including an outer casing and an inner pump liner, the coupling pin being suitable for locating the liner and casing relative to one another, the coupling pin including a shank and a head at one end of the shank. The head includes a cammed surface thereon which is adapted to co-operate with a follower on the liner, and a locating section on a remote or terminal end of the head which is adapted to be positioned against a seat in the outer casing when fitted. The arrangement is such that rotation of the coupling pin causes the follower to track along the cammed surface so as to cause relative movement between the outer casing and the inner pump liner.

Abstract: A turbine bucket includes a radially inner mounting portion; a shank radially outward of the mounting portion; at least one radially outer airfoil having a leading edge and a trailing edge; a substantially planar platform radially between the shank and the at least one radially outer airfoil; at least one axially-extending angel wing seal flange on a leading end of the shank thus forming a circumferentially extending trench cavity along the leading end of the shank, radially between an underside of the platform leading edge and a radially outer side of the angel wing seal flange; and slash faces along opposite, circumferentially-spaced side edges of the platform. At least one of the slash faces is formed with a dog-leg shape, a leading end of the at least one of slash face terminating at a location circumferentially offset from the leading edge of the at least one radially outer airfoil.

Abstract: A cooling arrangement (82) for a gas turbine engine component, the cooling arrangement (82) having a plurality of rows (92, 94, 96) of airfoils (98), wherein adjacent airfoils (98) within a row (92, 94, 96) define segments (110, 130, 140) of cooling channels (90), and wherein outlets (114, 134) of the segments (110, 130) in one row (92, 94) align aerodynamically with inlets (132, 142) of segments (130, 140) in an adjacent row (94, 96) to define continuous cooling channels (90) with non continuous walls (116, 120), each cooling channel (90) comprising a serpentine shape.

Abstract: A fan cooling system has individual fan modules which are connected together in an end-to-end configuration, where one of the fan modules is connected to a mechanism which rotates the linear array of fan modules. The fan modules are substantially identical, which allows prefabrication of the fan modules prior to on-site installation of the system. Each fan module may contain water injection piping and nozzles, which allows the fan cooling system to dispense fog. The linear array of fan modules may be rotated along a longitudinal axis, such that the axial flow direction of the fans may be changed with respect to a vertical plane. A suggested use of the fan cooling system is for the cooling of livestock in large livestock structures.

Abstract: A submersible centrifugal pump is disclosed. The submersible centrifugal pump includes a pump housing having a pump intake disposed generally opposite a pump outlet. A shaft extends at least partially through the pump housing and is adapted to be driven by a submersible motor. A centrifugal impeller is attached to the shaft and has an opening for fluid intake. A diffuser is disposed corresponding to the centrifugal impellers to form a pump stage. And an auger is coupled to the shaft.

Abstract: An air-handling unit including a housing with a discharge opening, and a fan disposed substantially within the housing. The fan includes a fan discharge that extends through the discharge opening thereby defining a gap between the fan discharge and the housing surrounding the discharge opening. A brush seal is coupled to one of the housing about the discharge opening and the fan discharge such that the brush seal extends across the gap forming a seal between the discharge opening and the fan discharge.

Abstract: A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage formed therein, wherein, in operation, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein a suction side of the platform comprises a topside extending circumferentially from the airfoil to a suction side slashface, and wherein the suction side of the platform comprises an aft edge. The platform cooling arrangement may include: a manifold positioned within an aft side of the suction side of the platform; a high-pressure connector that connects the manifold to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the manifold to the low-pressure coolant region of the interior cooling passage; and heat transfer structure positioned within the manifold.

Abstract: A gearbox assembly includes a first face gear driveable about a face gear axis in a first direction by at least one first pinion gear and a second face gear driveable about the face gear axis in a second direction opposite the first direction by at least one second pinion gear. A thrust bearing is located between the first face gear and the second face gear. The first face gear is configured to drive rotation of a first shaft in the first direction and the second face gear is configured to drive rotation of a second shaft in the second direction. Further disclosed is a power train for a rotary wing aircraft having a gearbox including a first face gear rotatable in a first direction and a second face gear rotatable in a second direction opposite the first direction.

Abstract: A high pressure turbine includes a stator, a rotor, a tangential on-board injector, and a heat shield. The rotor is located downstream of the stator and the tangential on-board injector directs cooling air to the rotor. The heat shield is retained by abutment with the stator and the tangential on-board injector.

Abstract: A hub is supported rotatably about an axis of rotation, and the diameter thereof increases from upstream to downstream sides along a fluid flow. A plurality of impeller blades extend radially outward from an outer circumferential surface of the hub. A shroud is formed in a cylindrical shape whose diameter increases from the upstream to downstream sides along the fluid flow and joins outer circumferential ends of the plurality of impeller blades. The impeller blades are composed of upstream blade segments and downstream blade segments bonded at a bonding surface extending in a direction substantially perpendicular to the axis of rotation. The upstream blade segments are integral with at least a portion of the shroud, and the downstream blade segments are integral with at least a portion of the hub. This improves the reliability and performance of an impeller and a compressor.

Abstract: A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root.

Abstract: A fan assembly includes a case, a bracket and a fan module. The cage includes a ventilation plate. An installation portion and a positioning post are located on the ventilation plate. The fan module is secured to the ventilation plate and includes a bracket and a fan secured to the bracket. The bracket includes a body, a first sidewall, and a second sidewall. The first and second sidewalls are located on opposite sides of the body. The first sidewall defines a first receiving slot and a first positioning hole. The second sidewall defines a second receiving slot and a second positioning hole. The first positioning hole is aligned with the second positioning hole. An area of the first receiving slot is larger than that of the second receiving slot. The positioning post is engaged in the positioning hole. The installation portion is received in the first receiving slot.

Abstract: A rotor section for a rotor of a gas turbine is provided. The rotor section includes a rotor disk with rotor blades inserted in retaining grooves thereupon, the rotor blades being secured against displacement along the retaining grooves by means of a sealing element which is arranged on the end face. In order to disclose a reliable construction which can be designed in a straightforward and simple manner for the circumferential fixing of the sealing element, each sealing element is secured by means of a blocking element in each case which in this case engages in a hole which is arranged in the rotor blade root on the end face.