Abstract: A rotor blade airfoil of an axial-flow turbomachine, for a fan or a compressor high-pressure stage of a gas turbine system, configured in the tip area to improve supersonic performance. The blade afflux edge has a forward-back sweep. The tip region of the blade efflux edge can be designed essentially similar to the blade afflux edge, with the tip region extending across the outer 15% to 25% of the blade span.

Abstract: The invention concerns a blade having an axial length L, expressed in meters, equal by approximately 20%, to the value of L0 given by the following formula (I): L0=0.426262−5.14288.D+23.1798.D2−44.2505.D3+30.8841.D4, D being the blade diameter expressed in meters. The invention enables to substantially reduce the blade axial space requirement, for a given diameter and for obtaining the desired performance. The invention is useful for cooling a motor vehicle engine.

Abstract: A portable cooling fan. The fan includes a fixed rack arranged under a frame body, a wheel set disposed laterally on the fixed rack, a support rod located at a position opposite against the wheel set for stabilization, and a handgrip arranged on an upper position of the fan body for carrying the cooling fan easily. In addition, an indented costa is formed on each of the leaf blades by pressing, to enhance intensity of the leaf blades and create turbulence to enlarge the blowing area. The frame body includes a protective mantle, which is supported with a plurality of reinforcement ribs.

Abstract: The fan comprises a hub, the axis of which coincides with the axis of rotation of the fan, and a plurality of blades which extend from the hub between a minimum radial distance from the axis in the vicinity of the hub and a maximum radial distance. In the vicinity of the hub, the cross-section of each blade has an angle of attack and an angle of curvature which are substantially equal to 0° and, starting from the hub, the cross-sections of each blade have angles of attack and angles of curvature which increase as the radial distance from the axis increases, up to a radial distance of between 30% and 40% of the radial extent of the blade.

Abstract: A compressor airfoil includes pressure and suction sides extending from root to tip and between leading and trailing edges. Transverse sections have respective chords and camber lines. Centers of gravity of the sections are aligned along a double bowed stacking axis for improving performance.

Abstract: An axial flow fan for an air conditioner is disclosed. This axial flow fan is capable of changing the shape of blades by varying a design factor such as a chord length, a sweep angle, etc., generating an enough flowing amount of a fan for implementing an efficient heat radiation of a heat exchanger, and decreasing a noise which occurs during an air flowing operation of the fan, so that it is possible to implement a high efficiency and low noise fan system. The above-described axial flow fan according to the present invention includes a hub engaged to a rotary shaft of a motor, and a plurality of blades engaged to the hub, wherein assuming a coordinate which is obtained by computing a distance R in a radial direction of the blade into a distance from a radius Rh to a radius Rt at a blade tip BT based on a non-dimensional method as “r” (r=(R−Rh)/(Rt−Rh), a maximum camber ratio Hc(r) which is a ratio between a maximum camber Cmax and a chord length 1 has 0.02±0.

Abstract: Upper and lower faces of a helicopter blade aerofoil are defined by the following coordinates. TABLE 1 X/C Yup/C Ylow/C 0.00000 0.00000  0.00000 0.00100 0.00511 −0.00584 0.00250 0.00843 −0.00813 0.00500 0.01218 −0.01014 0.00750 0.01505 −0.01136 0.01000 0.01747 −0.01218 0.01250 0.01959 −0.01277 0.01500 0.02150 −0.01328 0.01750 0.02325 −0.01375 0.02000 0.02487 −0.01415 0.02500 0.02780 −0.01483 0.05000 0.03891 −0.01714 0.07500 0.04682 −0.01862 0.10000 0.05291 −0.01979 0.15000 0.06152 −0.02206 0.20000 0.06666 −0.02470 0.25000 0.06892 −0.02729 0.30000 0.06895 −0.02949 0.35000 0.06841 −0.03109 0.40000 0.06744 −0.03211 0.45000 0.06568 −0.03270 0.50000 0.06301 −0.03272 0.55000 0.

Abstract: A centrifugal fan runner, equipped with backward blades, being suitable to be applied to, in particular, an air cleaner, an air conditioner, and a fan for air blow and ventilation, with high fan efficiency, a large air volume, low noises, comprising: a core plate being connected to an axis of a motor; and a side plate being provided opposing to said core plate, wherein backward blades, being inclined in an anti-rotational direction thereof, are provided at a distance in a circumferential direction, and the backward blades are bent in a position at distance of about ½-{fraction (1/(3.5))} of a length of the blade from an outer periphery thereof, so that an outlet portion thereof is inclined into a direction of rotation of the blade, and an outlet angle of the outlet portion with respect to a tangential direction on an outer periphery of said side plate lies from about 40 degree to about 60 degree.

Abstract: An axial blower includes a cylindrical hub, a driving device for rotating the cylindrical hub through a rotational shaft, a plurality of vanes arranged to an outer peripheral surface of the cylindrical hub in a circumferential direction thereof, and a plurality of stream-line ribs each having a stream-line shape and provided at a leading edge portion of a negative pressure surface-side of each of the vanes in a range from an end portion of the leading edge portion towards a trailing edge portion of the vane. The stream-line ribs are formed integrally such that an outer surface of a cross section of each stream-line rib along a rotational direction of the axial blower forms a circular arc and a radius of a circular arc curve of the outer surface at a vane leading edge side is larger than a radius of a circular arc curve at a vane inner surface side.

Abstract: A rotor blade for a turbine engine including a blade root section and an airfoil section which extends radially outward along a radial line RAS from the blade root section, is described. The radial line RAS extends at an angle relative to a plane extending across a top surface of the platform, rather than normal, or perpendicular, to such plane. As a result, and during a blade out event, an over turning moment is generated in a root of the airfoil section. The overturning moment facilitates bending the airfoil section reducing damage to the stator.

Abstract: An axial flow fan is disclosed. The axial flow fan comprises a hub, a plurality of blades extending radially outwardly from the hub, and an outer band surrounding peripheral ends of the blades. The median sweep angle of each blade increases gradually from 0° along the outward radial direction. The leading sweep angle of each blade starts from an angle of less than 0°, increases gradually and terminates at an angle of more than 40°. The trailing sweep angle of each blade increases along the outward radial direction after it decreases from an angle of more than 0° along the outward radial direction. The chord length of each blade gradually increases along the outward radial direction. The pitch angle of each blade gradually decreases along the outward radial direction.

Abstract: Improvement is made to the shape of blades of a fan assembly for sucking air into an annular wall through slits in the wall, in order to increase the aerodynamic performance and energy efficiency. In the fan assembly for sucking air in through slits provided in an annular wall (2), the blade tips of an axial fan (21) are bent in the rotating direction to smoothly take in air flowing in through the slits. The axial fan is formed so that the blades except the tips thereof are in a shape of a radial or a rearward tilting blade. The angle formed by the blade forward tilting angle near the blade tip of the axial fan and the slit angle is between −5 and 15°, and the blade tip is bent in the wind blowout direction. This configuration improves the P-Q characteristic, reduces noise and improves energy efficiency.

Abstract: A propeller for aircraft has a tip-to-tip flex-beam spar and torsionally stiff hollow blades bonded to the spar throughout an outer portion of the blades. The spar has two end caps which are separated from each other at the hub and converge in the outer portion. The blades have an inner region which is not bonded to the spar, allowing an inner portion of the spar to twist during pitch changes. A counterweight is mounted to an arm extending from an inner end cuff of each blade. The counterweight is located out of the plane of rotation. The counterweight is also located on a side of a line opposite from the trailing edge, the line passing through the pivot axis perpendicular to the plane of rotation.

Abstract: A blade for a rotary wing aircraft includes a blade tip winglet intended to reduce the blade-vortex interaction noise during descending flight. The winglet has, in plan view, an at least approximately trapezoidal shape, and the mean value of a chord C.sub.1 of the winglet is between 25% and 40% of a chord C.sub.0 of the main part of the blade. Compared with a conventional rectangular tip, and for the same aerodynamic thrust, the reduction in noise associated with use of the blade tip winglet can be as much as 40%.

Abstract: Disclosed is a runner for a Francis-type hydraulic turbine, comprising a ring, a hub, and a number of blades all having a curved shape and being attached to the ring and hub. Each blade has an inlet edge and an outlet edge. The blades are characterized in that, in the direction of turbine rotation, the junction point of each blade inlet edge at the ring is located forwardly of the inlet edge attachment point for that blade at the hub, and the junction point of each blade outlet edge at the hub is located forwardly of the outlet edge attachment point for that blade at the ring.

Abstract: An impeller for a marine waterjet propulsion system has blades that are configured to reduce cavitation, vibration, noise and physical damage to the major components of the propulsion system or host vessel of installation. The leading edge of each blade of the impeller is skewed forwardly over at least the outer 70% of its span, the forward skew being maximum at the tip and being not less than 35.degree.. The impeller has a blade area ratio of not less than 1.5. The chord lengths of each blade increase progressively from the point of minimum skew to the tip, resulting in reduced loading in the cavitation critical region. A partial or full tip band may be affixed to the blade tips.

Abstract: A blade is disclosed for an aircraft rotating aerofoil. The aerodynamically profiled main part of the blade includes an external end part adjacent to the tip of the blade and extending along the span over a distance of at least 0.2 R, where R is the radius of the rotor. The end part having a rear camber over a distance along the span of at least 0.15 R, and the aerodynamically profiled main part includes also a front cambered part, immediately adjacent to the inside of the rear cambered end part.

Abstract: A propeller used to interact with a fluid to either move the fluid, e.g., a fan or generate thrust for propulsion, e.g., for an aircraft or boat. The propeller is characterized by at least first and second planar blades configured for mounting on a propeller shaft. Each of the planar blades defines a periphery including (1) a trailing edge lying substantially in a common plane oriented perpendicular to the propeller shaft and (2) a leading edge inclined at an angle of A.degree. relative to the common plane so that the midpoint of the leading edge is axially displaced, relative to the propeller shaft, from the midpoint of the trailing edge.

Abstract: A high efficiency axial flow fan includes a hub, fan blades and a circular band. The hub rotates about a rotational axis when torque is applied from a shaft rotatably driven by a power source. The circular band is concentric with the hub, connected to the tip of each blade, and is spaced radially outward from the hub. The blades are configured to produce an airflow when rotated about the rotational axis. Each blade has a chord length distribution, stagger angle and dihedral (axial) distance which varies along the length of the blade. The dihedral distance of each blade varies as a function of blade radius from the rotational axis.

Abstract: A high aspect ratio, low solidity fan blade of an axial flow air cycle machine has a local tip center of gravity axis that has been shifted ahead of an elastic axis. The center of gravity axis can be shifted by clipping the tip of the blade at the trailing edge, by undercutting a rear portion of the pressure surface, or by sweeping forward leading and trailing edges of the blade by about five degrees (without clipping or undercutting the blade).

Abstract: A centrifugal fan including a fan hub lying generally in a plane normal to the axis of fan rotation and having a central opening for receiving a motor housing, and a plurality of fan blades of substantially identical construction spaced circumferentially evenly around the fan hub and extending away from the fan hub in a direction parallel to the axis of fan rotation. Each fan blade includes a leading edge at its innermost radial periphery, and the leading edge, at least at the axially upper one-half section thereof, is convexly curved in the shape of a quarter ellipse having a major axis, Mg, substantially parallel to the axis of fan rotation and a minor axis, mh, normal to the major axis Mg. The fan also includes a continuous shroud joined to each fan blade at an axially upper section of the radially outer portion thereof and the shroud is concave in cross-section.

Abstract: A fan module with an axial flow fan and a shroud member. The axial flow fan has a hub and a plurality of fan blades, each blade extending radially from the hub. At the tips of the blades are air guide members secured to respective fan blades and concentric with the hub. Each air guide member has an axially-extending arcuate portion, and a respective lip portion extending radially outwardly from each said arcuate portion. The axially-extending portion has an axial length substantially equal to or less than the axial length of said hub. The shroud member has a surface cooperating with the air guide members in an arrangement to reduce tip vortices.

Abstract: The present invention relates to a blade with a swept-back tip for a rotary wings of an aircraft, a blade being formed of successive elemental cross sections. The blade is divided into different regions, with the chord length L and the offset y'f of the center of pressure from the pitch-change axis and the relative thickness of each elemental section are optimized for high-speed flight. The first region has a linearly increasing chord length, the second region has the maximum and constant chord length, the third region has a linearly decreasing chord length and the fourth region has a decreasing chord length according to a parabolic function. The offset of the aerodynamic center is positive and increases in proportional to the distance in the first region, is at its maximum and constant in the second region, and decreases linearly and become negative in the third region.

Abstract: The coordinates defining the upper surface, lower surface, leading edge configuration and center of circle for a helicopter blade airfoil are given to increase maximum lift coefficient and lift-to-drag ratio, and to reduce noise level.

Abstract: A counter-rotating fan which comprises a forward-skewed upstream rotor and a backskewed downstream rotor. The counter-rotating fan may be used in a cooling module with a heat exchanger, for example as an engine cooling fan in a vehicle.

Abstract: Gas-cleaning equipment is disclosed, which comprises a housing having an intake vent and an exhaust vent and having disposed between the two vents a fan having at least one rotating blade. Air pollutant-removing system using the gas-cleaning equipment is also disclosed. This gas-cleaning equipment can effectively clean a gas through the action of plasma produced by glow discharge caused by rotation of said fan. When a metal layer having a catalytic activity is fixed onto the surface of said rotating blade, this metal layer also functions to effectively clean the gas. In the case where both the plasma and the metal layer function to clean the gas, there car be obtained synergistic effects. Cleaning of the gas can be conducted with more efficiency by bringing the intake gas into contact with the fan in an oxygen-free state. A magnet provided as an outer wall of the housing serves to generate plasma with higher density, leading to more effective cleaning of the gas.

Abstract: An axially compact axial flow fan with improved air-moving properties has a first array of fan blades that extend radially from a fan hub to a circumferential blade support member, a second array of fan blades extend from the first support member to a radially outward second circumferential blade support member. The fan blades in the second array each enjoy pitch angles that decrease from the second circumferential blade support radially along only a portion of each blade length. Thereafter, the pitch angles for the blades in the second array remains constant to the second circumferentially extending blade support member.

Abstract: A fan has a hub and a plurality of blades each having a medial line, a root region secured to the hub and extending radially outwardly to a tip region, with a leading edge and a trailing edge of each blade having a respective surface portion which is tangential to a respective radius of the fan, the leading edge and the trailing edge of each blade at the tip region being circumferentially behind, with respect to a first direction of rotation, the leading edge and trailing edge at the root region whereby the fan is rearwardly skewed wherein each blade has a dihedral angle formed between a plane perpendicular to a center axis of the fan and a line tangent to the medial line, each blade having a surface which is curved so that the dihedral angle decreases along the span of the blade moving from the root to the tip over a portion of the span equal to about 50% of the total span and wherein the dihedral angle increases over the remaining portion of the span.

Abstract: A bowed airfoil is provided which includes a plurality of passages disposed between a pressure side wall and a suction side wall. The pressure and suction side walls extend widthwise between a leading edge and a trailing edge, and spanwise between inner and outer platforms. Passages extend spanwise between the inner and outer platforms. Ribs, each having a rib end, separate adjacent passages. Passage turns, each having an end wall, connect the passages. The end wall of each passage turn acutely converges with one of the side walls, and a first fillet extends between the acutely converging side wall and end wall. According to one embodiment, each rib end acutely converges with the other of the side walls, and a second fillet extends between the acutely converging side wall and rib end.

Abstract: A centrifugal ventilator fan having a base plate with an axis of rotation, an inlet ring having an opening therethrough and a plurality of generally flat blades, each having first and second side edges, a leading edge and a trailing edge is provided. Each blade is connected to the base plate along the first side edge, and is connected to the inlet ring along the second side edge. The blades are radially spaced about the axis of rotation and are backwardly inclined with respect to a direction of rotation of the fan. A portion of each blade adjacent to the leading edge has a radius of curvature such that the blade portion adjacent to the leading edge extends generally inwardly towards the axis of rotation to reduce noise generated by the ventilator fan.

Abstract: An impeller pump for moving large volumes of liquid against heads of up to 1 meteris formed by a substantial circular housing having its axis substantially vertical in which an impeller is mounted for rotation on the central axis. The impeller has an maximum diameter substantially equal to the inside diameter of the housing and is formed with a hub and the plurality of blades symmetrically positioned around the hub. Each blade extends radially outward of the hub from a root to a tip and has a foil shaped cross section with a lift to drag ratio at least 75 to 1 at a Reynolds number of under 10.sup.6. Each of the blades is skewed rearward in the direction of blade rotation so that the apparent aspect ratio of blade is increased and to reduce operating noise. Each blade has an angle of attack of between 2.degree. and 6.degree. and has a rake in the direction of flow through the impeller of between 3.degree. and 7.degree.. The impeller lifts water through the housing and directs it into the fish farm.

Abstract: A structure of a ventilation fan provided with a plurality of blades has a performance curve characterized by a gentle slope throughout the wide operating range instead of an S-hysteresis curve, in order to overcome a fluctuation phenomena of the operating flow rate. The blade tip cross-section lies on a first imaginary cylindrical surface and an angle of attack and pitch angle of the blade tip are formed as respective trajections by intersecting the first cylindrical surface by a second cylindrical surface whose center axis has been rotated about two axes.

Abstract: A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius r.sub.t -inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius r.sub.t-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.

Abstract: A blade for a vehicle engine-cooling fan assembly having a curved planform and a high-lift airfoil. The planform has a first region adjacent the root of the blade with forward curvature, a second region adjacent the tip of the blade with backward curvature, and an intermediate region disposed between the first region and the second region with substantially straight curvature. The airfoil has a leading edge; a rounded, bulbous nose section adjacent the leading edge; a trailing edge; a curved pressure surface extending smoothly and without discontinuity from the nose section to the trailing edge; a curved suction surface extending smoothly and without discontinuity from the nose section to the trailing edge; and a thin, highly cambered aft section formed adjacent the trailing edge and between the pressure surface and the suction surface.

Abstract: An axial flow fan has a hub with a back plane that is perpendicular to the axis of hub rotation. The leading and trailing edges of the fan blades that bound the inner region of the respective blades are in general radial alignment with the hub. The leading portion of the tip region is swept forward relative to the back plane and the trailing portion of the tip region is swept in the opposite direction. The forward swept tip region forms an acute angle with the back plane.

Abstract: A plastic fan includes two injection molded parts, each of which includes its own hub and a set blades extending outwardly from the hub to a band. The two parts are co-operatively sized and shaped to be assembled into a single operable fan having: 1) a hub comprising the hubs of each of the component parts; 2) the blades of the component parts; and 3) a circumferential band comprising the bands of the component parts. The fan blade separation on each of the fan parts is relatively large, permitting separate injection molding of each part. The resulting fan may be designed to have far greater blade number and blade solidity that would be possible for a fan that is injection molded by standard techniques. The fan may be packaged in an airhandler assembly that includes a flexible cylindrical retraining member generally coaxial with, and external to, a rigid cylindrical member, the fan band and the stator assembly, so as to support the stator assembly and to maintain the parts in place.

Abstract: A forward-swept, low-noise rotor blade includes an inboard section, an aft-swept section and a forward-swept outboard section. The rotor blade reduces the noise of rotorcraft, including both standard helicopters and advanced systems such as tiltrotors. The primary noise reduction feature is the forward sweep of the planform over a large portion of the outer blade radius. The rotor blade also includes an aft-swept section. The purpose of the aft-swept region is to provide a partial balance to pitching moments produced by the outboard forward-swept portion of the blade. The rotor blade has a constant chord width; or has a chord width which decreases linearly along the entire blade span; or combines constant and decreasing chord widths, wherein the blade is of constant chord width from the blade root to a certain location on the rotor blade, then decreases linearly to the blade tip thereafter. The noise source showing maximum noise reduction is blade-vortex interaction (BVI) noise.

Abstract: A high efficiency fan and stator arrangement for generating an airflow through a heat exchanger is disclosed herein. The fan is rotated about its rotational axis by an electric motor, and includes eight blades extending radially from a hub to a circular band. Each fan blade has a stagger angle and chord lengths which vary along the span of the blades. Each fan blade also includes a trailing edge having a flat surface extending along the edge. The flat surfaces of each fan blade are coincident with a plane perpendicular to the rotational axis. The fan produces an airflow when rotated about the rotational axis, wherein a component of the airflow occurs at a first angle to the rotational axis. The fan support has a central bearing support and twenty elongated airfoils extending radially outward from the bearing support. Each airfoil has substantially the same length as the fan blades and includes a curved airflow guiding surface having a leading edge and a trailing edge downstream from the leading edge.

Abstract: A rotor blade for a gas turbine engine includes a bowed surface on a tip region of the suction side thereof. The curvature of the bowed surface progressively increases toward the tip of the blade. The bowed surface results in a reduction of tip leakage through a tip clearance from the pressure side to the suction side of the blade and reduces mixing loss due to tip leakage.

Abstract: The present invention relates to a fan having a plurality of equiangularly spaced, radially extending blades. The spacing provided between adjacent blades is substantially constant along the entire radial length of the blade for increasing a blowing efficiency, while also allowing a mold separation operation along the axial direction during the formation of the fan using a mold. In a case where the blade is a sweep-forward blade, the number of the blades is seven or more and has a sweep-forward angle of the blades between 35 to 45 degrees. Finally, in case where an electric motor for rotating the fan is supported by stays, the number of stay member and the number of blades, which are not evenly dividable by each other, should satisfy a relationship of 2,000<x.times.y.times.Nf/60, where N.sub.f is a rotational speed of the fan.

Abstract: Gas-cleaning equipment is disclosed, which comprises a housing having an intake vent and an exhaust vent and having disposed between the two vents a fan having at least one rotating blade. Air pollutant-removing system using the gas-cleaning equipment is also disclosed. This gas-cleaning equipment can effectively clean a gas through the action of plasma produced by glow discharge caused by rotation of said fan. When a metal layer having a catalytic activity is fixed onto the surface of said rotating blade, this metal layer also functions to effectively clean the gas. In the case where both the plasma and the metal layer function to clean the gas, there can be obtained synergistic effects. Cleaning of the gas can be conducted with more efficiency by bringing the intake gas into contact with the fan in an oxygen-free state. A magnet provided as an outer wall of the housing serves to generate plasma with higher density, leading to more effective cleaning of the gas.

Abstract: A high output fan assembly for cooling the radiator of a motor vehicle. The fan assembly comprises a shaft, first and second fans, and a motor. The first fan includes a plurality of first blades, each of which has an inner portion attached to the shaft, while an outer hub is attached to an outer portion of at least one of the first blades. The second fan includes a plurality of second blades, each of which has an inner portion attached to the outer hub. The motor is drivingly connected to the shaft to drive the first and second fans at the same number of revolutions per minute. The fan assembly is situated either for pulling or for pushing air across the radiator and an air conditioning condenser of the motor vehicle.

Abstract: In a turbofan engine a fan designed for reduced damage during a blade-out condition wherein the fan blade airfoil is disposed asymmetrically on the platform and includes a forwardly displaced leading edge. The platform is configured to make early contact with a following airfoil upon blade-out.

Abstract: An aircraft variable pitch propeller blade utilized in subsonic flight at relatively slow turning applications with relatively high power coefficients. The blade in plan form is tapered at both ends with the maximum chord approximate the mid station of the blade, the leading edge of the blade being swept behind the longitudinal axis of the blade near its tip and the trailing edge is convex and essentially straight from its maximum chord outward to the tip.

Abstract: The variation in the length of the chord L and the variation of the offset Y'f of the aerodynamic center are such that the leading edge (5) and the trailing edge (6) of the blade (1), along its longitudinal extent, exhibit no break, the overall aerodynamic center of said blade Being substantially situated on the pitch variation axis.

Abstract: An ultra-thin low noise axial flow fan is provided for office automation machine. The center line along the blade from its root portion to its tip portion is circular arc form and it is perpendicular to the central hub. The leading edge skew angle at the tip portion of the blade is 47 degrees. The blade angle of each blade ranges from 57 to 63 degrees, which is first directly proportional to the radius of the blade and then inversely proportional to the radius of the blade from the root portion to the tip portion of the blade. The pitch-chord ratio of each blade is inversely proportional to the radius of the blade from the root port to the tip portion of the blade. The blade of the fan thereby generates high air flow and high pressure, and has advantages of low noise and ultra-thin outer casing.

Abstract: A combination solar and wind powered generator including a wind generator, responsive to the flow of air currents, for converting mechanical energy into electrical energy. The wind generator includes a plurality of air spirally shaped engaging vanes which are rotatably supported by the wind generator, and operative for intercepting the flow of air currents for producing mechanical energy. The wind generator also includes an electric generator apparatus coupled to the plurality of air engaging vanes, for transforming the mechanical energy into a first source of electrical energy. A plurality of light sensitive cells, disposed proximate the spirally formed air engaging vanes, are adapted for transforming light energy into a second source of electrical energy. The spirally shaped air engaging vanes may include a plurality of surface deviations for altering the flow of air currents intercepted by the vanes and for directing light energy onto the light sensitive cells.

Abstract: In one type of aircraft propulsion system, propeller blades are mounted on a ring which surrounds a turbine. An annular space exists between the turbine and the ring. If a propeller blade should break free, the unbalanced centrifugal load tends to deform the ring. The invention reduces the deformation, as by locating spacers between the turbine and the ring.

Abstract: An aircraft propeller blade utilized in subsonic flight at relatively slow turning applications with relatively high power coefficients. The blade in plan form is tapered at both ends with the maximum chord approximate the 44% percent station of the blade, the leading edge of the blade being swept behind the longitudinal axis of the blade near its tip and the trailing edge is convex and essentially straight from its maximum chord outward to the tip.

Abstract: The invention concerns reduction of tip vortices in aircraft propellers, wherein a fence having anhedral or dihedral is attached to the blades of the propeller. Another form of the invention is applicable to counterrotating propeller systems, wherein a fence is attached to the blades of the forward propeller of the system, and no fences are attached to the aft propeller.