Abstract: Upper and lower surfaces of an aerofoil are defined by the following coordinates given in the table below, and the configuration of a leading edge of the aerofoil is defined by the following leading edge radius and the center of circle. Thus drag divergence Mach number Mdd and maximum lift coefficient Clmax can be increased and the noise level can be reduced.______________________________________ X/C Yup/C Ylow/C ______________________________________ 0.00000 -0.00323 -0.00323 0.00100 0.00155 -0.00758 0.00250 0.00418 -0.00925 0.00500 0.00782 -0.01062 0.00750 0.01060 -0.01155 0.01000 0.01312 -0.01213 0.01750 0.01912 -0.01316 0.02500 0.02381 -0.01388 0.05000 0.03437 -0.01561 0.75000 0.04070 -0.01707 0.10000 0.04466 -0.01852 0.15000 0.04893 -0.02100 0.20000 0.05083 -0.02312 0.25000 0.05150 -0.02506 0.30000 0.05149 -0.02663 0.35000 0.05105 -0.02775 0.40000 0.05016 -0.02835 0.45000 0.04875 -0.02839 0.50000 0.04663 -0.02767 0.55000 0.04359 -0.02618 0.60000 0.03974 -0.02407 0.65000 0.03515 -0.02146 0.70000 0.

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: The invention relates to heatable wind energy turbine blades and to a method of heating and deicing the turbine blades using conductive fabrics to displace and/or cease the buildup of ice on the turbine blades by electrothermal fabric heater disposed or integrated on the turbines for effectively deicing the blades. Multiple turbine blade design methods are explored as well as heater materials and the application of such materials.

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: A blood pump used for extra corporeal circulation, and more particularly, as a small turbo blood pump including a casing having an interior region, an aperture formed in an upper portion defining a blood inlet, and an aperture formed in a lower portion defining a blood outlet. An impeller is rotatably mounted within said casing interior region and includes a rotary shaft and at least one vane depending therefrom. The at least one vane has an upper radius adjacent the blood inlet that is less than a lower radius adjacent the blood outlet. The base of the at least one vane forms an exterior angle of less than 90.degree. with the axis of the rotary shaft. A driven magnet is mounted to the at least one vane. The impeller is rotationally driven by a non-contacting driving magnet that is exterior to the casing.

Abstract: In injection-molding first and second blade bodies (2, 3), convex parts (23, 32) are formed on the surfaces of the first and second blade bodies (2, 3), respectively. Then, a horn (16) of an ultrasonic welding device is placed at a position of crossing both the convex parts (23, 32) to come into contact with the top surfaces of the convex parts (23, 32) while pressing them at the same time, and in this state, the ultrasonic welding device is operated. Contact surfaces of the first and second blade bodies (2, 3) are welded at their portions corresponding to a pressing direction of the horn (16) and concurrently, both the convex parts (23, 32) are deformed by melting under pressure through the horn (16) to trickle melting resin of both the convex parts (23, 32) into a clearance (10) between the first and second blade bodies (2, 3), so that both the blade bodies (2, 3) are joined to each other.

Abstract: A windmill having a plurality of radially extending blades, each being an aerodynamic-shaped airfoil having a cross-section which is essentially an inverted pan-shape with an intermediate section, a leading edge into the wind, and a trailing edge which has a flange doubled back toward the leading edge and an end cap. The blade is of substantial uniform thickness. An air compressor and generator are driven by the windmill. The compressor is connected to a storage tank which is connected to the intake of a second compressor.

Abstract: An axial flow fan comprising a printed circuit board which mounts the circuitry for operating the motor which is a bipolar winding motor. A voltage regulator IC and a driving IC for a bipolar winding motor are mounted on the printed circuit board. The fan housing is employed as a heat sink for the voltage regulator. Large circuit elements are eliminated. The axial flow fan further comprises a plurality of blades for cooling electronic components wherein the blades comprise of a plurality of specially designed airfoil sections, each section having along substantially the entire length thereof, a cross-sectional shape characterized by a maximum thickness located substantially constantly between about 19% chord to about 20% chord and a maximum camber located substantially constantly between about 45% chord to about 46% chord. The circuitry, housing, and blades are designed so that the axial width of the axial fan is decreased while maintaining performance parameters and design constraints.

Abstract: An impeller for a supercharger is described. The impeller comprises a body having a base and an air intake end wherein the body is adapted to mount to a drive assembly of the supercharger. Further, the drive assembly is able to drive and rotate the body. Precision made air vanes are attached to the body wherein the precision made air vanes and the body are able to be positioned within a volute chamber housing creating precision sealing gaps.

Abstract: A bi-directional fan includes asymmetrically-shaped fan blades wherein, at each transverse cross-section of the blade, the profile of the blade includes a leading portion lying on one side of a straight line connecting the leading and trailing edges of the blade and a trailing portion lying on the opposite side of the straight line. The leading portion of the blade is larger than the trailing portion of the blade, and the point at which the blade's mean line of profile crosses the straight line is closer to the trailing edge than the leading edge. From the leading edge to a point of maximum camber, the shape of the profile of the blade is described by a polynomial expression. From the point of maximum camber to the trailing edge, the shape of the profile of the blade is described by a cosine wave function. The larger leading portion presents a greater forward-curved surface area which allows the blade to move air more efficiently in the forward direction.

Abstract: In an axial fan having a plurality of blades (2, 2, . . . ) around an outer periphery of a hub (1), a cross-sectional configuration of each of the blades (2) at an arbitrary distance from a center of the fan is set such that a blade thickness gradually increases moving away from a blade leading edge (2a) and then gradually decreases towards a blade trailing edge (2b). Also, if a length of a camber line extending from the blade leading edge (2a) to a position where the blade thickness becomes maximum is taken to be L, and a length of a camber line extending from the blade leading edge (2a) to the blade trailing edge (2b) at the arbitrary distance is taken to be L.sub.0, then L/L.sub.0 falls within a range of 0.27 to 0.35. Thus, the aerodynamic performance never lowers even if the inflow angle of air into the blade (2) varies.

Abstract: A triple mode aircraft which can take off as a helicopter, or in gyrocopter mode with no power to the rotors or as a conventional aircraft obtaining lift from a circular wing and in another embodiment from short stub wings; a canard wing and high lift tailplane. So it combines the flexibility of a helicopter with the same efficiency and safety of a gyrocopter and a fixed wing aircraft, also has the same simplicity and efficiency of flying a helicopter that doesn't have a tail rotor to worry about. The rotor craft includes two counter-rotating rotors with weighted tips on one set of rotors or a circular airfoil (CA) attached to at least one set of rotors. This CA gives the lift to function as a conventional aircraft, it also weights the tips of the rotor to give a gyro-stabilizing effect to the whole aircraft. Also there is a down draft rudder that functions as a rudder in horizontal flight or catches the down draft from the rotors for directional control.

Abstract: The present invention provides a fan (100) that includes a hub (102) and a plurality of blades (104). The hub (102) has a blade attachment surface (106) that extends around the circumference of the hub (102). The blades (104) extend from the blade attachment surface (106). Each of the blades (104) has a blade tip (108) distal from the blade attachment surface (106) and a chord length (110) defined as the width of the blade (104). Each blade (104) includes a hub chord length (112) defined as the chord length of the blade (104) at the blade attachment surface (106) and a tip chord length defined as the chord length at the blade tip (108). The relationship of the chord length to the blade radius is defined as the area bounded by the following equations:blade radius=0.0205 metersblade radius=0.0369 meterschord length=0.438*(blade radius)+0.021 mchord length=0.438*(blade radius)+0.028 m,and the blade angle is defined as the area bounded by the following equations:blade radius=0.0205 metersblade radius=0.

Abstract: A quiet compact radiator cooling fan having a hub portion, which extends radially outwardly and axially from its inlet to its outlet end, a shroud portion, which extends radially inwardly and axially adjacent the inlet end and radially outwardly and axially adjacent its outlet end forming a converging annular opening and a plurality of airfoil shaped, forward sweep blades disposed between the hub and shroud which cooperate with the hub and shroud to produce a mixed flow radiator fan which has improved blade loading and aeroacoustic performance producing a quiet and efficient cooling fan for off the road vehicles.

Abstract: A flow sensor using induction pickup and having an improved paddle wheel type impeller within an impeller housing having a concave opening defining a protective skirt area for shielding a portion of the paddle wheel and a stem of the paddle wheel with a varying thickness for reducing cavitational backflow and therefore achieving a precise measurement of the fluid flow velocity and a high turndown ratio is disclosed.

Abstract: A blade for an axial fluid machine comprises an effective blade portion having a root portion and a tip portion and projecting blade portions. The projecting blade portions are defined by axis reference lines extending to an upstream side with respect to a fluid flow from at least one of the root portion and the tip portion of the effective blade portion and by axes obliquely extending from ends of the axis reference lines toward a leading edge of the effective blade portion. The projecting blade portions are formed continuously to and integrally with the leading edge of the effective blade portion so that the effective blade portion and the projecting blade portions have substantially the same maximum blade thickness.

Abstract: Airfoils for the tip and mid-span regions of a wind turbine blade have upper surface and lower surface shapes and contours between a leading edge and a trailing edge that minimize roughness effects of the airfoil and provide maximum lift coefficients that are largely insensitive to roughness effects. The airfoil in one embodiment is shaped and contoured to have a thickness in a range of about fourteen to seventeen percent, a Reynolds number in a range of about 1,500,000 to 2,000,000, and a maximum lift coefficient in a range of about 1.4 to 1.5. In another embodiment, the airfoil is shaped and contoured to have a thickness in a range of about fourteen percent to sixteen percent, a Reynolds number in a range of about 1,500,000 to 3,000,000, and a maximum lift coefficient in a range of about 0.7 to 1.5. Another embodiment of the airfoil is shaped and contoured to have a Reynolds in a range of about 1,500,000 to 4,000,000, and a maximum lift coefficient in a range of about 1.0 to 1.5.

Abstract: This invention provides a compact, flat axial fan which is not limited by the shape of an incorporated rotor magnet and ensures a sufficiently large air flow and wind pressure, wherein the slide (under) piece of a mold that forms the under-molding portions of the vanes of the impeller of the axial fan is pulled out while being twisted (while performing a helical motion) in the direction of central axis of the base portion of the impeller, so that the mold can be formed simple to realize a multi-cavity mold, and the vanes can be formed into an ideal form by setting vane angles depending on different rotating peripheral velocities of the vanes, so that air can be supplied form the under-molding portions of the vanes to the vanes on the outer circumferential side during rotation of the impeller and a method of manufacturing an impeller for the axial fan.

Abstract: A turbine meter used for measuring the volume of fluid flowing through a conduit includes an elongated housing having an upstream end and a downstream end and a rotor mounted within the housing. A plurality of turbine blades are mounted on the rotor at an angle with respect to the axis of rotation of the rotor which causes each of the rotor blades to have a high pressure surface which faces toward the upstream end of the housing. Each of the rotor blades also has a trailing edge closest to the downstream end of the housing. An extension is included at approximately the trailing edge on the high pressure surface of at least one and preferably a plurality of the rotor blades. The extension has a length and forms an angle with respect to the high pressure surface of the rotor blade on which it is mounted which causes the percentage of error of the accuracy of the meter across a chosen operating range of the meter to be within predetermined limits.

Abstract: Ceiling fan blades for low speed fan operation. The blades have a positive twist at the root motor portion of the blade and a slightly twisted rounded tip. The chord of the blades taper down from the root to the rounded tip, and have a tapered airfoil from the aft forward aft edge to the trailing edge. The airfoil has a combination of a rounded leading edge with sharp trailing edge, and a square leading edge and rounded trailing edge. The blades can be twenty inches in length and twenty-six inches in length, and be used in ceiling fans having two, three, four or more blades in a ceiling mount. The ceiling fan blades are optimized to operate in ceiling fans running at low speed ranges of approximately 50 to approximately 200 revolutions per minute(rpm) with an enhanced axial airflow which provide substantial energy savings and increased air flow over conventional flat planar ceiling fan blades.

Abstract: An aerodynamic-shaped fan blade for use in a fan apparatus. The blade has a cross-section which is essentially an inverted pan-shape with an intermediate section, a leading edge section, and a trailing edge section which form concave and convex surfaces. The trailing edge has a flange doubled back toward the leading edge within the concave envelope.

Abstract: The invention relates to an impeller (1) for a mass flow measuring device receiving inflow of material through an inlet tube (6), the impeller comprising a bottom plate (4), an upper plate (5) and vanes (3) extending between the lower and upper plates. An inner edge (7) of the vanes (3) is continuously or successively rising from the center (9) of the impeller (1), or the vicinity thereof, towards the outer edge (R.sub.1m) of the inlet tube (6), and that the vanes (3) are provided with a continuously or successively rising outer edge (14) corresponding to an increase of the radius of the impeller from the radius (R.sub.2) of the bottom plate (4) to the radius (R.sub.xm) of the upper plate (5).

Abstract: An aerodynamic-shaped airfoil having a cross-section which is essentially an inverted pan-shape with an intermediate section, a leading edge into the wind, and a trailing edge which has a flange doubled back toward the leading edge.

Abstract: An aerodynamic-shaped propeller blade. The blade has a cross-section which is essentially an inverted pan-shape with an intermediate section, a leading edge section, and a trailing edge section which form concave and convex surfaces. The trailing edge has a flange doubled back toward the leading edge within the concave envelope.

Abstract: An air flow sensor and impeller flow for use in industrial, agricultural and civil applications as well as in process control, emission control and measurement. The impeller is suspended for free rotation in a tube section and has a central core and a number of impeller blades extending from the core wherein at least one blade extends from the core to the adjacent inner wall of the tube section. The flow sensor is equipped with measuring means to measure the number of revolutions of the impeller per unit of time and to register an associated calibration speed of the impeller.

Abstract: A variable speed helicopter rotor system and method for operating such a system are provided which allow the helicopter rotor to be operated at an optimal angular velocity in revolutions per minute (RPM) minimizing the power required to turn the rotor and thereby resulting in helicopter performance efficiency improvements, reduction in noise, and improvements in rotor, helicopter transmission and engine life. The system and method provide for an increase in helicopter endurance and. The system and method also provide a substantial improvement in helicopter performance during take-off, hover and maneuver.

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: 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 turbine blade (18) for a gas turbine engine includes a machining datum (60) that extends radially from a pocket (54) in the outer shroud (36) of the blade. The datum is spaced from a sidewall (64) of the pocket so that the datum is peripherally continuous irrespective of whether the blade is in a prefinished state or in a completely finished state. Because the datum's peripheral continuity survives the original manufacturing process, the datum is available for use in post-manufacturing inspection and repair operations.

Abstract: The blades (38) of a gas turbine engine fan rotor (32) are uniquely distributed in the rotor hub (48) so that combination tone noise attributable to one or more physical nonuniformities in the blades is mitigated. The invention recognizes that the frequency spectrum of the combination tone noise includes both decay prone harmonics and decay resistant harmonics and that allocation of acoustic energy into the decay prone harmonics and out of the decay resistant harmonics is effective for mitigating combination tone noise. In particular, the blades are distributed so that the spatial or circumferential spectrum of the physical nonuniformity is dominated by circumferential harmonics whose order is no greater than the order of the highest decay prone harmonic of the combination tone noise spectrum.

Abstract: A composite article comprising of a non-metallic composite core, a fluoroelastomer adhesive layer which has a curing temperature substantially similar to the composite core, and a metallic structure which overlays the fluoroelastomer adhesive layer, wherein the composite article can be formed by co-curing the core and the fluoroelastomer adhesive layer.

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: In a helicopter blade aerofoil, upper and lower surfaces thereof are defined by the following coordinates, and the leading edge profile of the aerofoil is defined by the following leading edge radius and center of circle. Thus drag divergence Mach number Mdd and maximum lift coefficient Clmax can be increased and the level of noise can be reduced.______________________________________ X/C Yup/C Ylow/C ______________________________________ 0.00000 0.00000 0.00000 0.00250 0.00781 -0.00558 0.00500 0.01131 -0.00765 0.00750 0.01423 -0.00874 0.01000 0.01660 -0.00964 0.01750 0.02224 -0.01156 0.02500 0.02658 -0.01276 0.50000 0.03585 -0.01568 0.07500 0.04128 -0.01758 0.10000 0.04480 -0.01901 0.15000 0.04893 -0.02113 0.20000 0.05095 -0.02306 0.25000 0.05181 -0.02492 0.30000 0.05200 -0.02647 0.35000 0.05179 -0.02760 0.40000 0.05129 -0.02821 0.45000 0.05038 -0.02827 0.50000 0.04888 -0.02775 0.55000 0.04673 -0.02662 0.60000 0.04393 -0.02491 0.65000 0.04037 -0.02268 0.70000 0.03592 -0.01996 0.75000 0.03052 -0.01682 0.

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 distribution 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 mixing process may be carried out in a tank of a certain diameter. The process may also be constrained to the use of an impeller of certain diameter in order to obtain the flow pattern desired to carry out the process. The power consumption of the system which may be expressed in terms of flow per unit (Q/P) is optimized for the impeller diameter to tank diameter (D/T) constraint by utilizing an axial flow blade, preferably having camber and a tip chord angle at the tip and an angle near the attachment to the shaft (the hub) which rotates the impeller, where the tip chord angle and the twist the difference between the blade angle (between the chord and a plane perpendicular to the axis of rotation of the shaft between the tip and hub) are varied in opposite senses; for example, increasing the tip chord angle to provide a more D/T for a more optimum Q/P to which the process is constrained and then reducing the twist to maintain the power efficiency at the higher tip chord angle.

Abstract: A molten metal pumping device is disclosed that comprises a pump base including at least one input port, a pump chamber, and a discharge leading to an output port. A rotor is retained within the chamber and is connected to a rotor shaft. The device further includes a superstructure attached to and positioned above the pump housing, a motor on the superstructure, a drive shaft connected to the motor and a coupling connecting the drive shaft to the rotor shaft. The rotor extends beyond the input port to deflect solid particles thereby reducing jams and preferably is a dual-flow rotor, directing molten metal both into the chamber and out through the discharge. The coupling is flexible and has two coupling members with a flexible disc disposed therebetween. Another aspect of the invention is a housing for a transfer pump that includes a discharge leading to an output port and a button adaptor extending from the discharge.

Abstract: A rotor (18) for use with a fluid flow generator or reactor, the rotor being intended to rotate about a central axis (19) and having a surface which defines an arcuate fluid pathway for fluid flow about the central axis about which the rotor is able to rotate, wherein the surface has the configuration of a logarithmic curve substantially conforming to the mathematical progression known as the Golden Section or the Fibonacci Progression.

Abstract: An airfoiled blade for improving the performance of a propeller at low aircraft speeds and for maintaining good performance of the propeller at high aircraft speeds is disclosed. The blade comprises a root portion for connection to a hub of the propeller and a tip portion defining an opposite end of the root portion. An elongated portion extends between the base portion and the tip portion and defines a leading edge and a trailing edge. The elongated portion has a cross-section defined by a scaleable airfoil section. The scaleable airfoil section comprises a chord having a fifty-percent chord station, a forward end defining the leading edge of the blade and an aft end defining the trailing edge. The airfoil section is aft end loaded for developing aft end lift. The scaleable airfoil section also has a camber distribution and a thickness distribution based therefrom.

Abstract: A high efficiency, low solidity, low weight, axial flow fan (100, 200, 300) includes a hub (102, 202, 302), fan blades (104, 204, 304) and a circular band (106, 206, 306). The hub (102, 202, 302) rotates about a rotational axis (110, 210, 310) when torque is applied from a shaft (not shown) rotatably driven by a power source (not shown). The circular band (106, 206, 306) is concentric with the hub (102, 202, 302) and is spaced radially outward from the hub. The blades (104, 204, 304) are distributed circumferentially around the hub (102, 202, 302) and extend radially from the hub to the circular band (106, 206, 306). The blades (104, 204, 304) are configured to produce an airflow when rotated about the rotational axis (110, 210, 310). Each blade (104, 204, 304) has a chord length distribution which varies along the length of the blade, such that the chord length has a local minimum value at a predetermined location between the ends of the blade.

Abstract: A main rotor is provided for use on a model helicopter. The main rotor includes rotor blades having an inboard section and an outboard section. The inboard section includes a higher camber, thin, wide airfoils, and greater pitch and camber relative to the outboard section. The outboard section includes an average chord length that is less than the chord length of the inboard section, The rotor blades also include a blade body that is semiflexible to bend during a crash landing of the model helicopter.

Abstract: An ultra high head pumpturbine power generating plant with a turbine having a runner rotating with water flow supplied through a high head conducting tube. A rotary electric machine rotates with rotation of the runner. The head is in the range of 400-600 m, and the runner is at least 5 meters in diameter. The said runner has characteristics of toughness at room temperature: at least 500 N/mm.sup.2, or tensile strength at room temperature: at least 650 N/mm.sup.2, elongation at least 16%, reduction of area at least 45%, 2 mm U-notch impact value at 0.degree. C. at least 100 J, and fracture toughness at least 6000 N/mm.sup.3/2.

Abstract: A liquid flow meter is designed to monitor the flow of a liquid through an enclosed stream such as through the tubes or internal passageways of a device such as a filtration system. The liquid flow meter includes an axial-flow magnetic turbine and a detector such as a reed switch that monitors turbine rotation by counting pulses. The counted pulses are then used to determine the aggregate volume of liquid that has flowed through the flow meter. When the liquid flow meter is used in a domestic potable water filtration system or in a similar application, the counted pulses can also be used in conjunction with a timer to determine liquid flow rate as well as the remaining useful life of a filter cartridge of the filtration system and/or of the remaining volumetric filtration capacity of the filter cartridge. The liquid flow meter exhibits high linearity or consistency of flow measurement over a wide range of liquid flow rates--even at very low pressures and low flow rates.

Abstract: An iron-nickel superalloy of the type IN 706 has an addition of 0.02 to 0.3 percent by weight of boron and/or 0.05 to 1.5 percent by weight of hafnium. By means of this addition, a virtual doubling of the ductility is achieved as compared with an addition-free iron-nickel superalloy of the type IN 706, while the hot strength is reduced only slightly. The alloy is particularly suitable as a material for rotors of large gas turbines. It has a sufficiently high hot strength. When locally acting temperature gradients arise unwanted stresses can occur to only a slight extent because of the high ductility of the alloy.

Abstract: A fan assembly includes a circular first array of first fan blades; a first primary ring member supportively connecting inner extremities of the first blades about a fan axis, respective end extremities of at least a majority of the first blades defining inside and outside diameters of the array, the first blades being oriented for producing a primary axial fluid flow between the inside and outside diameters in response to rotation of the first ring member, the first ring member extending between the inside and outside diameters. A second primary ring member connects outer extremities of the first blades, the first blades in combination with the first ring member defining a generally circular opening about the fan axis.

Abstract: A nickel-base gamma-sigma intermetallic matrix composite material suitable for forming gas turbine engine components and structural coatings for such components. The composite material contains, in weight percent, about 20 to 50 chromium, about 0 to 32 molybdenum, and about 0.5 to 7 silicon, with the balance being nickel and incidental impurities. In addition, the composite material may contain aluminum and titanium in amounts of up to about 7 and 3 weight percent, respectively. The resulting intermetallic matrix composite material is characterized by a sigma volume fraction of greater than 30 percent, preferably at least about 50 percent, and may have a dendritic, fibrous or lamellar microstructure. The composite material can be cast to form a component, or deposited by known techniques to form a structural coating on a component.

Abstract: A pump body 10 of a drainage pump 1A comprises a pump chamber 12, inlet 15, and outlet 17. A rotary vane 300 mounted in the pump body 10 is coupled to a motor mounted above the pump body 10, and comprises a shaft 310 and four large-radial blades 320. Formed below the large-radial blades 320 are small-radial blades 350 to make a liquid at the inlet rise. Lower edges of the large-radial blades 320 are connected together by a disk 350 having an opening at the center and interceptively dividing the surface of the liquid rising from the inlet. Thus the amount of the liquid in contact with the large-radial blades 320 above the disk 350 decreases, and the load to the rotary vane decreases. At the same time, bubbles, noise and vibrations caused by bubbles also decrease. By surrounding the outer circumference of the large-radial blades 320 with a ring member, return water W5 moving back from the outlet 17 when the pump stops is damped by the wall member 360 and returns smoothly to the inlet 15.

Abstract: An axial-flow impeller having a maximum blade width less than 20% of the impeller diameter, the pitch angle at the radial position 0.6 is 12.degree.-22.degree., the width at the tip end portion of the blade is 12-75% of the width at the radial position 0.6, the pitch angle at the tip end portion of the blade is 5.degree.-10.degree. smaller than the pitch angle at the radial position 0.6, the width at the root of the blade is 40% or more of the width at the radial position 0.6, and the pitch angle at the root of the blade is 25.degree.-50.degree.. An axial-flow impeller having a maximum width of the blade 20% or more of the impeller diameter, the radial position of the maximum width portion is 0.4-0.8, the pitch angle of the maximum width portion is 12.degree.-22.degree., the width at the tip end portion of the blade is 12-75% of the maximum width, and the pitch angle at the tip end portion of the blade is 5.degree.-10.degree.

Abstract: A marine propulsion device improves the handling characteristics and the responsiveness of the watercraft on which it is used. The propulsion device includes a pair of counter-rotating propellers. At least the blades of the front propeller each have a mean camber line in cross-section which has a generally constant radius of curvature. This blade shape reduces cavitations and permits the rear propeller to be mounted closer to the front propeller, and consequently closer to the steering axis of the outboard drive. As a result, steering torque is reduced. The blades of the rear propeller also are not more than thirty percent smaller than the blades of the front propeller, and the average pitches of the propellers do not differ by more than one to four percent. These blade configurations of the front and rear propellers improve the stability of the watercraft when turning, thereby reducing chine walk, as well as improve the responsiveness of the watercraft.

Abstract: An airfoiled blade is disclosed which comprises a plurality of airfoil sections, a root portion, and a tip portion. Each section has along substantially the entire length thereof a cross-sectional airfoil shape characterized by a parabolic leading edge, a front loading and a blunt trailing edge. Each of the airfoil sections has a chord passing therethrough with a 50% point and a maximum thickness forward of the 50% point, toward the leading edge. A thickness ratio range from a first of the airfoil sections nearest the tip portion to a last of the airfoil sections nearest the root portion of substantially 3% to 28% is preferred. In one embodiment, the blade further includes a second airfoil section, a third airfoil section and a fourth airfoil section located between the first and last airfoil sections. The first airfoil section has a thickness ratio of substantially 3.3%, the second airfoil section has a thickness ratio of substantially 4.1%, the airfoil section has a thickness ratio of substantially 7.

Abstract: The turbine comprises a plurality of blades disposed between two end plates and defining flow passages between an inner ring and an outer ring. The turbine is formed by first and second parts, each part made as a single one-piece part out of thermostructural composite material, the first part forming both a first end plate and the blades, while the second part forms the second end plate which is applied against the blades of the first part. The first part and the second part are preferably assembled to each other solely by being clamped together via their central portions.