Abstract: A method for installing an offshore wind turbine system includes driving a cylindrical annular monopile or a substructure into the soil. The monopile includes a flanged portion configured to support a wind turbine tower or a superstructure. The flanged portion extends radially from a peripheral surface of the monopile. The method further includes mounting a wind turbine tower directly on to the monopile, wherein the wind turbine is supported by the flanged portion of the monopile.

Abstract: A fan shaft structure includes an annular groove portion, an end head adjacent to the groove portion, and several teeth equally spaced around the surface of the shaft. The annular groove portion, end head and teeth constitute an insert part of the fan shaft, around which the plastic fan blade is molded by insert molding. The present invention enables the center part of the fan blade to enwrap the insert part of the shaft, and firmly engage with the shaft. It is, therefore, not only able to enhance the robustness of the combination but also successful in preserving the adhesion effect between the shaft and the fan blade.

Abstract: The present invention is a method of minimizing steam boiler pressure changes or turbine power changes during turbine control valve operational safety test stroking. The method of the present invention uses control valve positions as feedback into a compensation algorithm to minimize flow disturbance caused by the closing and reopening of a turbine control valve during periodic operational testing. By maintaining the total mass flow through several parallel turbine inlet control valves constant, the steam generator pressure is maintained constant, and the inlet pressure regulator is unaffected during inlet control valve testing. Maintaining the total mass flow through several parallel turbine inlet control valves constant also minimizes turbine power changes during inlet control valve testing. In addition, the monitoring of additional process parameters is not needed.

Abstract: A gas turbine engine strut segment includes a strut, which may be hollow, extending radially between co-annular radially inner and outer platforms, axially spaced apart inner platform flanges extending radially inwardly from the inner platform, and axially spaced apart outer platform flanges extending radially outwardly from the inner platform. At least one inner set of coaxial tapered inner holes extend axially through the inner platform flanges and at least one outer set of coaxial tapered outer holes extend axially through the outer platform flanges. The inner set of coaxial inner holes define an inner conical surface and the outer set of coaxial outer holes define an outer conical surface. Each of the axial spaced apart platform flanges may be circumferentially continuous or scalloped having spaced circumferentially apart lugs. The strut may have two inner sets of coaxial tapered inner and outer holes extending axially through the inner and outer platform flanges, respectively.

Abstract: The present invention features a fluid flow regulator that functions to significantly influence fluid flow across an airfoil or hydrofoil, as well as various rotating or rotary devices, including propellers, impellers, turbines, rotors, fans, and other similar devices, as well as to significantly effect the performance of airfoils and hydrofoils and these rotary devices subjected to a fluid. The fluid flow regulator comprises a pressure recovery drop that induces a sudden drop in pressure at an optimal pressure recovery point on the surface, such that a sub-atmospheric barrier is created that serves as a cushion between the molecules in the fluid and the molecules at the airfoil's or hydrofoil's surface. More specifically, the present invention fluid flow regulator functions to significantly regulate the pressure gradients that exist along the surface of an airfoil or hydrofoil.

Abstract: A pump which is bladeless, and uses a substantially cylindrical outer cylinder to rotate inside a ridged inner chamber.

Abstract: An impingement baffle includes a perforate plate having a pattern of impingement holes. An imperforate deflector is spaced from the plate and is smaller than the plate for deflecting inlet air around the deflector to the holes. The baffle is disposed between a turbine shroud and supporting hanger, and the deflector is disposed between the hanger and the baffle.

Abstract: A gas turbine engine turbine blade includes a hollow airfoil extending radially from a blade root to a radially outer airfoil tip. The airfoil includes an airfoil outer wall having transversely spaced apart pressure and suction side walls meeting along chordally spaced apart leading and trailing edges of the airfoil. A radially extending cooling air supply channel within the airfoil includes a bank of pins integral with and extending transversely between the pressure and suction side walls. The bank of the pins is tuned such that a natural frequency of the blade associated with an engine forced driving mode of the blade is sufficiently away from a steady state engine operating frequency to substantially avoid natural frequency resonance of the blade during steady state engine operation. The bank of the pins is tuned by locations of the pins within the cooling air supply channel.

Abstract: A technique of generating a flow from a gas. The technique includes the steps of selecting molecules from the gas on a nanoscopic or microscopic scale, and generating the flow from the selected molecules. The gas can be air. In one embodiment, the molecules are selected based on the direction of movement of the molecules. In another embodiment, the molecules are selected based on the velocities (i.e., direction and speed) of the molecules. Also, devices that implement the technique.

Abstract: An annular air baffle disposed in a cavity of a rotatable gas turbine engine part includes an annular split ring supporting a plurality of circumferentially spaced apart fins. The cavity is closed at a radially outer diameter and open at a radially inner diameter of the part. The ring and the fins may be integrally formed in one piece. The fins may have common surfaces with the ring and the common surfaces may be circular cross-sectional surfaces of the ring and radially outer rounded corners of the fins. The fins may have triangular cross-sectional shapes with first, second, and third sides, rounded first radially inner corners between the first and second sides, rounded second radially inner corners between the second and third sides, and the radially outer rounded corners between the first and third sides. The fins may extend radially inwardly from the annular split ring.

Abstract: A method and apparatus for assembling a steam turbine is provided. The method includes performing a finite element analysis to determine a cross-section of a sealing member, positioning the sealing member in a leakage path defined between an inner casing and an outer casing such that a leakage flow activates the sealing member. The apparatus includes a groove defined in a channel, a divider positioned in the channel such that a gap defined between the divider and the channel defines a leakage path, and a sealing member that extends at least partially within the groove and positioned to substantially prevent a flow though the leakage path.

Abstract: An attachment system for use with a variable incidence vane is disclosed. The attachment system includes a vane arm for joining a unison ring to a vane spindle. The vane arm has an arm portion and a bushing connected to the arm portion. The attachment system further has a pin for joining the vane arm to the unison ring. The pin fits within an interior bore in the bushing and is joined to the unison ring by a dual swage.

Abstract: A component includes a wall with a cold and a hot surface. At least one film-cooling hole extends through the wall for flowing a coolant from the cold to the hot surface. The film-cooling hole defines an exit site in the hot surface. At least one flow modifier is formed on the hot surface and is adapted to direct the coolant flowing from the film-cooling hole and out of the exit site toward the hot surface. The flow modifier extends outwards from and conforms to the hot surface. A turbine assembly includes a first and a second component that define a secondary cooling slot, which receives and guides a secondary coolant flow. At least one flow modifier is formed on a surface of one of the two components and is adapted to enhance the secondary coolant flow along at least one of the two components within the secondary coolant slot.

Abstract: A method and apparatus for detecting the occurrence of surge or incipient surge in a centrifugal compressor is supplied. The centrifugal compressor has an inlet passage, an inlet passage wall and an impeller. When flowing a fluid through the centrifugal compressor thereby establishing a fluid flow in the inlet passage, the fluid flow is measured in the inlet passage proximate the inlet passage wall and proximate the impeller. The measurements may include detecting a reverse in the fluid flow direction, measuring a tangential component to the fluid flow, measuring a substantial decrease in the axial fluid flow, and/or measuring the fluid temperature. Fluid flow in the compressor can then be modified or controlled to prevent surge.

Abstract: A turbofan engine includes in serial flow communication a first fan, second fan, multistage compressor, combustor, first turbine, second turbine, and third turbine. The first turbine is joined to the compressor by a first shaft. The second turbine is joined to the second fan by a second shaft. And, the third turbine is joined to the first fan by a third shaft. First, second, and third cooling circuits are joined to different stages of the compressor for cooling the forward and aft sides and center bore of the first turbine with different pressure air.

Abstract: A maritime energy generating device including a windmill mounted on a floating foundation, the windmill having a machine compartment mounted at the top of a tower and the foundation being fixed to the bottom of a water body by a connection and including two tanks and a unit for shifting liquid between the tanks and the tanks and the surroundings.

Abstract: This invention relates an improved cylindrical blades for axial steam turbines comprising a leading edge and a trailing edge and a pressure face and a suction face and an inlet flow angle and an outflow flow angle at the leading edge and trailing edge respectively characterized in that the blades formed by setting angle variation for incompressible flow as well as at subsonic Mach numbers at the exit with a lower loss for a range of stagger angles.

Abstract: A fan shroud having an integrated aspirator is provided comprising a first section and a second section. The first section and second section are designed to mateably engage one another so as to form an air passage between a fan and a cooling module of a vehicle. The first section of the shroud includes an air duct formed by a channel in the shroud and a similar channel in a duct cover, so that when the duct cover is mated to the first section of the shroud an air duct is created. A first end of the air duct terminates at an aperture disposed in an end of shroud situated proximal to the fan. A second end of the air duct curves upwardly to a nozzle provided on the top side of the duct cover. A pre-cleaner unit having an air intake and an air exhaust is aspirated through an aspirator port. When the pre-cleaner is mounted to the shroud, the aspirator port is disposed in the nozzle of the duct cover. The aspirator port is thus in communication with the air duct and the shroud aperture.

Abstract: A main rotor blade includes a tip section having a splice cap, a structural tip spar, a core and an upper and lower tip skin. The tip section is mounted to a central blade section by mounting the tip spar to a main blade spar. The tip spar includes a first surface substantially parallel to a second surface. The first and second surfaces each extend from a shear web therebetween to define the generally C-shape in cross section. The shear web generally carries rotor blade torsional loads and eliminates the heretofore required structural core. A section of the tip spar overlaps a section of the main blade spar. The tip section thereby transfers the loads carried thereby through interaction between the overlapped spar sections. The tip section core and skins need not be structural members as the tip spar carries rotor blade tip section torsional loads.

Abstract: A fan guide hood structure includes a fixing seat and a hood. The fixing seat has a hollow cylinder, which has clamping parts and guide rails arranged in symmetry at its edge and a fixing part on its top. The fixing part is designed to couple with the fan unit and the hood has a sleeve at one end. The sleeve has clamping grooves and slide grooves corresponding to said clamping parts and said guide rails and extends downwards to form a trumpet hood part. An elastic member lies between said hood part and said fixing seat and the whole structure forms a seamlessly adjustable guide hood structure.