Abstract: Wind turbine apparatus is described for converting wind energy into electrical energy. The apparatus includes a rotatable central shaft, a plurality of rotor blades attached to the central shaft, and a plurality of convex airfoils spaced around the periphery of the rotor blades. The ratio of the number of rotor blades to the number of airfoils is at least 1.25 to 1. The size of the apparatus may vary, and the apparatus is useful in a variety of applications and environments. It is very efficient in converting wind energy to electrical energy. It may be operated even in very high wind conditions.

Abstract: A fluid moving device (100) includes a rotatable assembly (101), and a plurality of fan blades (102-04) disposed circumferentially around and extending outward from rotatable assembly (101), at least one of plurality of fan blades (102-04) includes shape memory alloy. The fan blade which includes shape memory alloy transforms into a predetermined shape memory state when the fan blade experiences a predetermined temperature which may be as a result of a predetermined temperature of surrounding fluid passing over fan blades (102-04) when rotation of rotatable assembly (101) is at a given speed. The shape memory state increases or decreases volume flow of surrounding fluid when rotatable assembly (101) is rotating at substantially a constant speed. The speed is substantially constant which limits noise generated from fluid moving (100) device while volume flow rate of the fluid moving device is being changed.

Abstract: An impeller having flexible impeller blades with a stiffness which allows the blades to flex into a backward-curved impeller configuration at the maximum intended rotational speed of operation, and to return to a more radial blade configuration at lower rotational speeds, thereby enabling efficient operation at a broad range of rotational speeds.

Abstract: A helicopter blade assembly for permitting rapid forward flight in a helicopter having separate means for providing a forward impetus. The assembly has a set of rotatable blades attached to a substantially vertical mast. These blades slope downward near to their distal ends, thereby creating an inverted disk virtual air foil when the blades are rapidly rotated by the mast. In a preferred embodiment the camber of the blades and, therefore, the shape of the virtual air foil is controllable.

Abstract: A submersible magnetic motor having improved rotary blades comprising a magnetic motor body, a magnetic rotor and a rotary impeller wherein the rotary impeller comprises a rotary hub provided with a plurality of blades which are uniformly distributed and extend outwardly around the periphery of the hub. The rotary hub is provided with an axial hole centrally formed therethrough for positioning an end of a central shaft of the magnetic rotor. The present invention is characterized in that the blades are each provided at the outer end edge with two stoppers and a fin freely pivoted therebetween, so as to be adjacent to the inner surface of the wall of the receiving chamber of the submersible motor. When the magnetic rotor is actuated to rotate, the fins each pivots to contact one of the two stoppers due to the resistance of the water such that the submersible motor can be maintained at a constant rotation speed, and the water pumping efficacy can be substantially improved.

Abstract: This invention is a wind energy catchment system using a central vertical shaft, the bottom end of which rotates and is secured to a rigid support fixed to the ground. The lower part of the shaft has radial arms secured to it, evenly spaced one from the other. The upper end of the shaft and the outer ends of the radial arms are all connected by cables or cords. The cables between the ends of the radial arms define a regular polygon; between it and the upper end of the shaft and the outside end of each radial arm and around the shaft, there are triangular, dihedral or trihedral sails all formed by triangular surfaces secured at their vertices. In all cases, the furthest external side of these sails is arranged between the top end of the shaft and the furthest external end of the associated arm, while the lower edge runs between the end of each arm and one or more points on the surface on the same plane as the radial arms.

Abstract: A controllable variable twist rotor blade assembly wherein the twist along the span of the blade is continuously variable and may be controlled either manually by the pilot or automatically according to data input from flight sensors monitoring flight parameter data. The continuously variable twist of the blade is controlled by an out-of-plane weight assembly having a weight member which is selectively movable between a first position and a second position relative to the elastic axis of the blade so as to optimize the twist of the blade during various flight conditions.

Abstract: Propeller with twistable blades comprising a spar with ribs which can be rotated in opposite directions about the axis of the spar by an adjusting device. A coupling device in the propeller ensures that when two ribs are rotated in opposite directions by the adjusting device, the other ribs are adjusted accordingly. The coupling device consists of a rod substantially parallel to the spar and designed to be relatively bendable in the plane through the spar and the rod, and relatively resistant to bending in the plane perpendicular thereto. The rod couples at least three ribs together in such a way that it distorts when two ribs are rotated in opposite directions along a helix about the spar, causing subsequent ribs to move with it on this helix.

Abstract: The present invention discloses a main rotor collective pitch control assly for rotary wing aircraft. The assembly uses segmented rotor blades. The collective pitch of each movable segment may be independently varied, or may be adjusted in unison with one or more other segments on the same or different rotor blades. Control inputs may be made manually by the pilot or may be made by a computer which interprets data pertaining to the vibrational level and velocity of each rotor span. The pilot may override the computer in the event of system failure or if otherwise desired.

Abstract: Thermally actuated flow diverters for gas turbine engines are provided which include an arrangement of vanes in spaced overlapping array, which direct, e.g. coolant air flow to rotating engine components, each vane having 3 foil components joined at 3 hinge points. That is, a leading foil positioned on the suction side of the vane, a trailing foil pivotably mounted to a rearward portion of such leading foil at a first pivot axis and a third foil positioned on the pressure side of the vane connecting a forward portion of such leading foil and such trailing foil at second and third pivot axes respectively. Either the third foil or the leading foil is fixedly mounted to engine walls of the same material, the other of these two foils defining an actuation link that is expandable and contractable relative to such walls; the third foil having a coefficient of thermal expansion greater than that of the leading foil.

Abstract: A propeller for a prop-jet engine having a propellor blade formed as a hollow shell member whose outer surface has an aerodynamic blade profile, the propellor blade being secured to a rotor via an adjustment pin. The hollow shell member is internally braced partly along its radial length by a flexible spar secured to the pin and made of thermoplastic material. The flexible spar is hollow and receives a metal spar hich is fixed to the pin and is given flexibility in bending by the provision of a slot therein.

Abstract: An improved design for a structure such as a turbine vane or blade subjected to extreme temperature levels and/or gradients resulting in extreme deformation stresses within the structure. The present structures comprise an interior skeletal support having a plurality of spaced, flexible support legs which extend out and are attached to spaced areas of a flexible outer surface skin which is subjected to extreme temperature levels or temperature gradients during use. The extreme stresses normally developed by the expansion of the surface skin are avoided by the ability of the skin to move minutely and flex the spaced support legs to variable extents and in predetermined directions.

Abstract: An impeller for a centrifugal pump is disclosed for attenuating the effects of pressure and flow surges experienced by the pump. The impeller includes a rotatable impeller shaft to which a plurality of circumferentially-spaced vanes are mounted for rotation therewith, the vanes extending outwardly relative to the impeller shaft and each including first and second axially spaced edges. First and second axially-spaced cover members are provided for the plurality of vanes, the cover members being mounted for rotation with the impeller shaft and extending outwardly relative to the axial direction of the impeller shaft. The first cover member is disposed adjacent to first edges of the vane and the second cover member is disposed adjacent to second edges of the vane so as to provide an impeller chamber between the first and second cover members which is divided into subchambers by the vanes.

Abstract: A helicopter blade positioning mechanism provides collective and cyclic pitch angle adjustment of the blades independently. This mechanism is all enclosed within the blade driving axle. The pitch angle of each blade is adjusted collectively and cyclicly by direct action on and within the blade hub. No other linkage is required between the blade and the blade pitch actuation means. The cyclic pitch adjustment of each blade is obtained either by a rotation imparted to the whole blade body or by twisting the blade, depending upon the mechanism configuration used. In both cases, the cyclic pitch variations are superimposed on the collective pitch setting, vary sinusoidally as the blades gyrate around their vertical axis of gyration, one full pitch variation cycle for each full gyration of the blades. This mechanism plays the role and replaces the well known swash-plate/linkage arrangement used on most helicopters.

Abstract: A propeller blade made of an advanced composite of uniaxial fibers laminated in crossplies to take advantage of their high axial strength. The thinness and strength of the plies are exploited in assembling the plies at various orientations to produce propeller blades which respond to changing aerodynamic loads in the complex ways necessary to maintain an optimum shape.

Abstract: A wind turbine, having(a) at least one pair of sail means, each said sail means having upper and lower portions hingedly connected together to permit said portions to move away from and towards each other to thus open and close, respectively, said sail means being in the shape of an airfoil;(b) a vertical shaft,(c) a support,(d) means mounting said vertical shaft in said support for rotation about the vertical axis of said shaft; and(e) means mounting said sail means to said shaft, said sail means being disposed to move under the action of the wind in a plane about said vertical axis; said mounting means for said sail means including means for opening and closing one sail means of each pair of sail means while the other sail means of said pair is closed and opened, respectively, as said sail means moves about said vertical axis in said plane, said mounting means for said sail means being operable to dispose said plane at a predetermined angle to the horizontal and being adjustable to change said angle as desi

Abstract: The present invention relates to an apparatus for the stabilizing of the direction of travel of watercraft. The invention relates specifically to a sword or fin for sailboards. In order to allow the wind-profile like shape of the apparatus to adjust itself in accordance with a prevailing velocity of flow or a prevailing flow thereagainst, the apparatus comprises two deformable side walls which are mounted to a rigid and stiff center wall exclusively at an area located at the leading edge thereof in relation to the direction of flow. These side walls enclose together with the two oppositely arranged surfaces of the center wall two void spaces. Depending on the prevailing pressure situations between the luff side and the leeward side, an optimal hydrodynamic flow profile is automatically generated. According to preferred embodiments, the trailing edge of the apparatus comprises vacuum pumps which communicate with the void spaces, which vacuum pumps are present in form of water jet pumps.

Abstract: A high-temperature, extremely high-speed ceramet composite blade comprising a ceramic blade jacket seated from above on a metallic core having a crossweb near its upper end for securing the jacket on the core by one or more metallic retaining pins extending through the crossweb and secured to the core. A head on each bolt is located within a chamber formed above the cross-web and surrounded by the radially projecting end of the blade jacket. A porous abradable coating is secured to the head of the bolt and substantially fills the chamber. The coating projects slightly beyond the end of the blade jacket and is supplied and permeated with cooling air via a cooling duct extending through the retaining pin and metallic core.

Abstract: An aerodynamic rotor having a flexible blade comprising a plurality of planar layers and an anvil having configured bearing areas engagable with the flexed blade is presented. The plurality of layers are slidably movable in a shearing motion with respect to other layers. The blade is secured by the anvil with the configured bearing areas being engagable with an adjacent portion of the blade when the blade is flexed by forces created by the driven rotory motion of the anvil about an axis of rotation. Such a rotor with a laminated blade exhibits reduced head moment forces and reduced stress/strain forces within the blade thereby permitting improved reliability and maintenance.

Abstract: A flexible fan device includes a power driven boss and a plurality of fan blades, each secured on the boss at an attached angle. The fan blade has a root portion secured to the boss and a tip portion offset with respect to the root portion in the downstream direction so that the blade angle is decreased under the influence of centrifugal force in response to an increase in the rotating speed. The fan blade is formed to have an angle inclined in the direction of rotation of the boss.

Abstract: The fan assembly for a motor vehicle includes a plurality of radially extending blades each having a first rearwardly facing concave curvature extending along the entire length of the blade adjacent the leading edge and a forwardly facing concave curvature at the outer end of the blade adjacent the trailing edge to increase the cooling efficiency of the fan and decrease the noise produced during operation.

Abstract: A rotor blade extended radially from a hub, characterized by an elongated spar and a plurality of axially aligned shells pivotally mounted on the spar, each having an aerodynamic center located in trailing relation with the spar and supported thereby for simultaneous axial and angular displacement as centrifugal forces are applied thereto, and a pitch controller including a plurality of pivotal pitch limiting arms transversely related to the spar, each being characterized by a cam surface defined along one edge thereof, engaging in supporting relation a cam follower of a truck pivotally connected to a shell and supported thereby for pivotal motion about an axis coincident with a radius of said spar, and a push-pull link interconnecting the arms for imparting simultaneous pivotal motion thereto, whereby the angular relationship of the arms to the spar is varied for varying the motion of the trucks along the arms for thus limiting the pitch of the segments about the spar.

Abstract: A torsionally compliant helicopter blade having its aerodynamic center axis positioned selectively forward of its center of gravity and elastic axes throughout a selected portion of the blade span so that, during operation, the blade will experience airloading which will induce two per rev torsional deflection of the blade to thereby improve rotor performance by reducing the total power required to drive the rotor.

Abstract: A torsionally compliant helicopter rotor blade with maximum blade torsional flexibility at the blade tip portion and so shaped at the blade root portion that the locus of shear centers and the locus of centers of lift are substantially coincident, and so shaped at the tip portion so that the locus of shear centers is selectively forward of the locus of centers of lift to establish an aerodynamic restoring moment in response to blade tip torsional excursions, thereby improving blade torsional stability.

Abstract: A centrifugal compressor assembly for a gas turbine engine includes an inducer section and an impeller section mounted for rotation about an axis. Because leading edges of the impeller blades are cambered, damper pads, extending perpendicular to the low pressure sides thereof also extend axially forward. Blades of the inducer section are indexed rotationally rearward of the impeller blades to improve the distribution of compression gases through the impeller section and high pressure surfaces of the inducer blades mate near their leading edges with outward surfaces of the damper pads. Because the pads and inducer blades vibrate at different frequencies, inducer blade vibrations that might otherwise cause fatigue are attenuated by contact with the damper pads. The damper pad arrangement thus permits the damping of vibrations in the inducer blades notwithstanding the indexed relationship between the inducer section and the impeller section.