Abstract: An apparatus for generating electric power from water currents comprises a housing having at least one pair of channel, at least one pair of turbine assemblies and at least one pair of generator assemblies. Each channel of the pair has an axial intake, an axial discharge opening and a side intake. Each side intake extends along a length of the channel and faces in an upstream direction to receive a side inflow of water and directs the side inflow up against an interior surface of the channel to create a vortical flow structure having a low pressure core. The vortical flow structures are produced downstream of the turbine assemblies to effect an increase in a pressure drop across each of the turbine assemblies. The apparatus also has partition extending between the channels near said axial intakes.

Abstract: What disclosed is to form an abrasive coating having abrasiveness at a blade pressure side of a deposition layer using a second electrode composed of a second molded body molded from a mixed powder including a powder of a metal and a powder of a ceramic or the second electrode processed with a heat treatment, generating pulsing electric discharges between the blade pressure side of the deposition layer and the second electrode in an electrically insulating liquid or gas, and welding a material of the second electrode or a reacting substance of the material of the second electrode on the blade pressure side of the deposition layer by means of energy of the electric discharges.

Abstract: A method for channeling compressed air to a gas turbine engine augmentor is provided. The method includes coupling an annular slide valve to a gas turbine engine separation liner, coupling a valve seat to a gas turbine engine diffuser such that an airflow passage is defined between the annular slide valve and the valve seat, and channeling compressed air to the annular slide valve to facilitate regulating the quantity of fan bypass air channeled to the gas turbine engine augmentor.

Abstract: One or more vertical axis wind turbines (VAWT), preferably of the Savonius type, are mounted in a relatively simple and inexpensive manner. For a single VAWT a center pole may be disposed within a hollow shaft of the VAWT with at least upper and lower bearings acting between the shaft and center pole. Alternatively, a short tower or platform may mount a lower bearing (e. g. about 4-14 feet off the ground) for the VAWT shaft, and an upper bearing for the shaft may be mounted by an outrigger. The outrigger is connected at a number of different points (e. g. different arms) by strands (such as steel cables) to stationary supports. Where multiple VAWTs are provided, them may be in a cluster. Each VAWT in the cluster has a structural support in common with at least one other VAWT of the cluster, and each VAWT is operatively connected to a separate useful driven mechanism (such as an electricity or fuel gas generator).

Abstract: A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force absorbing arrangement circumferentially surrounds a major proportion of the axial length of the engine.

Abstract: A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.

Abstract: A turbocharger comprises a center housing (3) and a turbine housing (1) with a variable nozzle device arranged there between. The turbocharger further comprises an annular arrangement of adjustable vanes (7) interposed in an annular nozzle (9) for defining a plurality of nozzle passages, wherein the vanes (7) are axially resiliently supported on the center housing (3) or the turbine housing (601), respectively.

Abstract: A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.

Abstract: The present invention is for an apparatus and method for a passive pitchable device for wind turbines comprising: a camshaft having cam grooves engraved; a cylindrical shell; an axial compression spring; said blade assembly and said cylindrical shell are fastened together by screws; a plurality of balls that roll along said cam grooves, and convert the axial displacement to rotation or pitch angle; and wherein the passive pitchable device ensures said blades are at the optimum angle of incidence in the stationary position; as the rotor turns, the net force between centrifugal force on said blade and the resistant force from said compression spring causes the device to move axially outward while rotating to adjust the pitch of the rotor blade so that angle of incidence is optimal for the given wind speed; as the wind speed exceeds the design speed and the centrifugal force on the rotor blade continues to increase, the device continues the move axially outward while rotating in the opposite direction as to adju

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the rectangular coordinates X,Y,Z? given in Table 1, in which the X coordinate is measured in the axial direction of the turbine, and the Z? coordinate is the quotient D/H, where D is the distance of the point in question from a reference plane P0 situated at the base of the nominal profile and H is the height of the profile measured from said reference plane to the tip of the blade, the measurements D and H being taken radially relative to the axis of the turbine.

Abstract: A compressor blade for a gas turbine engine that includes a composite leading edge insert attached to a titanium blade by a row of fastener pins along an aft edge of the insert to prevent unzipping. Each insert is also secured by an electrochemically disbondable composition for easy removable of a damaged insert from an integrally bladed disk. One or more of the fastener pins provides for an electrical conductive path that bypasses the disbondable composition during a lightening strike so that the insert does not release. Each replaceable insert includes a root portion that fits within a slot of the rotor disk, with each insert being secured against radial displacement by two shear pins secured within two shear pin slots formed in both the insert root portion and the rotor disk slot. The shear pin slots are curved and follow the curvature of the airfoil at the junction to the rotor disk.

Abstract: A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may be positioned in an outer wall of the turbine airfoil for receiving cooling fluids from a cooling fluid supply source, passing those fluids through the chambers in the outer wall, and exhausting those fluids into central cooling fluids collection chambers. The outer wall may include a plurality of outer wall cooling chambers that may be configured to pass cooling fluids in a counter flow direction. The outer wall cooling chambers may include a plurality of ribs including a plurality of impingement orifices for increasing the cooling efficiency of the cooling system.

Abstract: A method of assembling a turbine includes positioning a turbine nozzle against a forward inner nozzle support extending from a rotor assembly, and coupling a cover to the forward inner nozzle support. The method also includes inserting a tab that extends from the cover within at least one aperture defined in the turbine nozzle.

Abstract: A turbine blade and platform assembly in which the platform is a separate piece that is secured to the blade through shear pins that extend along slots formed between opposed abutting parts of the blade and the platform. Because the platform is detached from the blade, the blade can be made of a single crystal superalloy with a reduction in casting defects. The platform has one or more airfoil shaped openings or slots on the outer surface in which a blade is inserted. The shear pins are inserted to secure the platform to the blade. In another embodiment, the blade root is inserted into an opening formed in the rotor disk, and shear pins are inserted into slots formed in the root and the disk opening in order to secure the blade to the rotor disk. With this embodiment, the blade can be made of a ceramic material because only compressive forces are formed to hold the blade in place.

Abstract: The present invention provides an axial-flow fan capable of entirely cooling an object to be cooled even when the distance between the object to be cooled and an air discharge opening of the axial-flow fan is short. A plurality of stationary blades 11A to 11E are disposed at intervals in a rotating direction of a rotor and located inside an air discharge opening 16 of an air channel 19. Each of the plurality of stationary blades 11A to 11E has an external end portion 11a connected to an inner wall portion of a fan housing 3, an internal end portion 11b connected to a peripheral wall portion 11B of a motor case 10, a discharge-side edge portion 11c formed between the external end portion 11a and the internal end portion 11b and located at a side of the air discharge opening 16, and a suction-side edge portion 11d formed between the external end portion 11a and the internal end portion 11b and located at a side of the air suction opening 14.

Abstract: A marine propeller is provided with a valve that progressively blocks exhaust flow into aerating relation with the blades of the propeller as the propeller rotational speed increases. A piston within a housing moves radially outwardly, in response to centrifugal forces, as the propeller increases in rotational speed. This movement progressively blocks an aperture that allows the flow of exhaust gas into the region of the propellers. In certain embodiments, a secondary flow path is allowed even when the piston has moved to its extreme outward radial position.

Abstract: A cooling arrangement (11) for a highly tapered gas turbine blade (10). The cooling arrangement (11) includes a pair of parallel triple-pass serpentine cooling circuits (80,82) formed in an inner radial portion (50) of the blade, and a respective pair of single radial channel cooling circuits (84,86) formed in an outer radial portion (52) of the blade (10), with each single radial channel receiving the cooling fluid discharged from a respective one of the triple-pass serpentine cooling circuit. The cooling arrangement advantageously provides a higher degree of cooling to the most highly stressed radially inner portion of the blade, while providing a lower degree of cooling to the less highly stressed radially outer portion of the blade. The cooling arrangement can be implemented with known casting techniques, thereby facilitating its use on highly tapered, highly twisted Row 4 industrial gas turbine blades that could not be cooled with prior art cooling arrangements.

Abstract: A centrifugal fan has an inlet bell that induces turbulence in the intake air stream so as to better distribute air across the rotating radial fan blades and thereby increase fan efficiency. The “turbulator” feature is one or more preferably arcuate surfaces integrally formed in the inlet bell to either project into or away from the intake air stream. The turbulator disrupts smooth air flow across the inside surface of the inlet bell has the effect of randomizing the air at the boundary layer to reduce separation of the air from the inlet bell as it leaves the inlet bell and enters the impeller. The air can thus follow the contour of the inlet bell more closely to make a tighter radius turn as it enters the impeller. In so doing, air is delivered across more of the fan blades so that output air flow is increased.

Abstract: A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.

Abstract: An array of blades for use in a turbomachine is provided comprising a plurality of blades mounted to a rotor disk. A plurality of first blades form a first set of blades and a plurality of second blades form a second set of blades. A blade-to-blade flow field defined between successive ones of the first set of blades is interrupted by the second set of blades to form an asymmetric blade-to-blade flow field around the array of blades. The trailing edges of the second set of blades are positioned forwardly from a line connecting the trailing edges of the first set of blades such that shock forces in the flow field around the array of blades will generally impinge on a stable region of the first set of blades.