| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Propeller, dessen Blätter mit einem Vorflügel versehen sind | EP88109182.1 | 1988-06-09 | EP0297321A1 | 1989-01-04 | Kallergis, Michael, Dipl.-Ing. |
Direkt angetriebener Propeller, dessen Propellerblätter (4) mit einem Vorflügel (6) versehen sind und der für eine niedrige Blattspitzen-Machzahl zur Verringerung des Propellerschalls ausgelegt ist. Die Vorflügel (6) sind starr mit den Propellerblättern (4) verbunden, und die Vorflügelspitzen liegen auf einem Durchmesser gemäß der Formel |
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| 62 | Rotorblatt | EP87730113.5 | 1987-09-28 | EP0295353A1 | 1988-12-21 | Al-Majed, Tahsin |
Dieses Rotorblatt (2) ist zu einem großen Teil seiner Länge gespalten, wobei sich durch das Ausstellen der beiden Blatthälften dieser Spalt (3) zum Blattende hin verengt. Die so entstandenen beiden Blattwurzeln (4, 5) sind in einem Anstellwinkel von etwa 45° hintereinander an der Rotornabe (1) befestigt, wobei sich durch diese Verdoppelung und die entstehende Verwindung das Rotorblatt abstützt und sich die Blattwurzelbelastung und -ermüdung erheblich verringert. Sowohl an der Stirnseite (6), als auch an der Rückseite (7) des Rotorblattes sind über die gesamte Blattlänge schmale Streifen bis zu einem bestimmten Grad angewinkelt. |
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| 63 | Auftriebselement insbesondere für Tragflügel und Schaufeln von Strömungsmaschinen, wie z.B. Luftschrauben und Schiffspropeller | EP82900352.4 | 1982-02-10 | EP0071616B1 | 1985-10-16 | SPRANGER, Günter |
| The flow gaz is compressed before reaching the leading edge of the wing and expanded on the back of the wing. Simultaneously, gaz from the undersurface sucked by the expanded gaz is mixed therewith thereby increasing the flow on the back of the wing and directing it so that the flow speed of the gaz leaving the trailing edge is evenly distributed over the length of the wing, that the take off point migrates towards the trailing edge and that, in the direction of the wing edge, the gaz pressure on the back of the wing is increased. The back of the wing is provided, at the vicinity of its edge (4), with at least one or a plurality of flow throats (1, 1a) which are integrated, at the foot (5) of the wing (2), in its profile, and which are evenly warped along its length. The distance between the wing and the throats (1, 1a) increases, towards the wing end, up to a slot (6, 6a) of maximum width. The profile (8) of the throat (1, 1a) has a maximum curvature at the foot (5) of the wing (2) and is flattened at its free end (9). The subtended angle between the profile chord of each throat and the profile chord of the wing varies from the feet (12) of the throats (1, 1a) up to the ends (9, 9a) as a function of the variable curvatures along the throats (1, 1a). | ||||||
| 64 | Luftschraube | EP84890156.7 | 1984-08-16 | EP0138800A2 | 1985-04-24 | Asboth, Oscar |
Luftschraube, wie z.B. für den Antrieb von Fahrzeugen mit kleinen Fahrtgeschwindigkeiten bei hohem Schlupf, etwa mindestens 60%, die einen Gütegrad von mindestens etwa 70% für 100% Schlupf aufweist, wobei das Verhältnis des Durchmessers der Luftschraube zu ihrer Steigung etwa dem 1,18 bis 2,9fachen Wert des Gütegrades aufweist und ihre Blattbreite dem 0,09 bis 0,19fachen Wert der Steigung entspricht. |
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| 65 | NOISE REDUCTION MEANS FOR PROP-FAN | EP80901388.1 | 1980-07-15 | EP0032915B1 | 1985-04-10 | HANSON, Donald Burnett; METZGER, Frederick Bruce |
| A prop-fan (10) of the type having a high solidity factor (1 or greater) near the root fairing to a lower solidity factor (less than 1) near the tip and operable over a critical Mach No. range is designed for sound suppression by contouring the tip so that its sweep and sweep distribution of the leading and trailing edge bears a judicious relationship with the Mach surface (20, 21). This feature is obtainable by designing the planform from a prescribed linearized or non-linearized acoustic theory and tailoring in the sweep so that the leading and trailing edges fall behind the Mach surface. | ||||||
| 66 | VERFAHREN ZUR VERMINDERUNG DES STRÖMUNGSWIDERSTANDES VON VON GASEN WIE LUFT OD.DGL. UMSTRÖMTEN FLÜGELN INSBESONDERE TRAGFLÜGELN UND SCHAUFELN VON STRÖMUNGSMASCHINEN UND EINE EINRICHTUNG ZUR DURCHFÜHRUNG DES VERFAHRENS | EP82900352.0 | 1982-02-10 | EP0071616A1 | 1983-02-16 | SPRANGER, Günter |
| Le gaz en ecoulement est comprime avant d'atteindre le bord d'attaque de l'aile et detendu sur le dos de l'aile. Simultanement, du gaz de l'intra-dos aspire par le gaz detendu y est melange ce qui augmente l'ecoulement sur le dos de l'aile et le dirige de facon que la vitesse d'ecoulement du gaz quittant le bord de fuite soit distribuee uniformement sur la longueur de l'aile, que le point de decollage migre vers le bord de fuite et que, dans la direction du bord de l'aile, la pression du gaz sur le dos de l'aile soit augmentee. Le dos de l'aile est muni, au voisinage de son bord (4), d'au moins un ou plusieurs etrangleurs d'ecoulement (1, 1a) qui sont integres, au pied (5) de l'aile (2), dans son profil, et qui sont gauchis uniformement sur sa longueur. La distance entre l'aile et les etrangleurs (1, 1a) augmente, vers l'extremite de l'aile, jusqu'a une fente (6, 6a) de largeur maximale. Le profil (8) de l'etrangleur (1, 1a) presente une courbure maximum au pied (5) de l'aile (2) et est aplati a son extremite libre (9). L'angle sous-tendu entre la corde du profil de chaque etrangleur et la corde du profil de l'aile varie des pieds (12) des etrangleurs (1, 1a) jusqu'aux extremites (9, 9a) en fonction de la courbure variable le long des etrangleurs (1, 1a). | ||||||
| 67 | NOISE REDUCTION MEANS FOR PROP-FAN AND THE CONSTRUCTION THEREOF | EP80901388.0 | 1980-07-15 | EP0032915A1 | 1981-08-05 | HANSON, Donald Burnett; METZGER, Frederick Bruce |
| Une soufflante (10) du type ayant un facteur de solidite eleve (1 ou plus) a proximite de la racine est profilee avec un facteur de solidite plus petit (inferieur a 1) pres de la pointe et fonctionnant dans une plage a Mach critique est concue pour supprimer le bruit en profilant la pointe de maniere telle que sa fleche et la distribution de la fleche du bord d'attaque et du bord de fuite aient une relation avantageuse avec la surface de Mach (20, 21). Cette caracteristique peut etre obtenue en dessinant le plan-forme a partir d'une theorie acoustique prescrite linearisee ou non linearisee et en y taillant la fleche de maniere a ce que les bords d'attaque et de fuite tombent en deca de la surface de Mach. | ||||||
| 68 | Composite Fan Blades with Integral Attachment Mechanism | US15863210 | 2018-01-05 | US20190211841A1 | 2019-07-11 | Daniel Cottrell; Randall Tatman; Steven Petullo |
| A fan blade comprising a blade body spanning from a blade root to a blade tip in a longitudinal direction and a fluid passageway formed within the blade body and extending from the blade root to the blade tip. The blade body spanning from a leading edge to a trailing edge in a lateral direction. The fluid passageway allowing fluid to flow out of the blade. | ||||||
| 69 | REDUCED BLADE VORTEX INTERACTION | US15768767 | 2016-10-12 | US20180297692A1 | 2018-10-18 | Daniel C. Sargent; Mark W. Scott |
| A blade includes an elongated body having a leading edge, a trailing edge, a root end, and a tip end, a fluid inlet arranged closer to the root end than the fluid outlet, a fluid outlet arranged near the tip end of the elongated body, and a centrifugal air flow channel defined within the body between the inlet and the outlet to direct air from the inlet to the outlet to issue the flow when the rotor blade is rotating in a rotational path. The blade also includes a valve to selectively open and close the centrifugal air flow channel to selectively issue the flow and change a blade vortex issuing from the rotor blade at discrete portions of the rotational path of the rotor blade. A controller can be operatively connected to the valve to control the valve to open and close the centrifugal air flow channel. | ||||||
| 70 | METHOD AND APPARATUS FOR INHIBITING FORMATION OF AND/OR REMOVING ICE FROM AIRCRAFT COMPONENTS | US15788716 | 2017-10-19 | US20180037329A1 | 2018-02-08 | Alan M. Giles; James T. Machin; John A. Geriguis |
| Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system for an aircraft comprising: a component of the aircraft having a surface; a plurality of piezo-kinetic actuators each positioned proximate to a portion of the surface; and a control unit coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface. | ||||||
| 71 | PROPELLER BLADE SHEATH | US15602342 | 2017-05-23 | US20170334577A1 | 2017-11-23 | Arnaud ANDRZEJEWSKI; Pierre-Alex PICARD; Ludovic PRUNET; Frederic VIGIER; Patrick MOLES |
| A propeller blade assembly includes an airfoil having a base, a tip and a leading edge and a root extending from the base of the airfoil for attaching the airfoil to a hub. The assembly further comprises an electrically conductive sheath for electrically grounding the airfoil. The electrically conductive sheath is attached to the leading edge of the airfoil and extends from the base to the tip of the airfoil. The assembly further comprises an electrically conductive element for electrically connecting the electrically conductive sheath to the root or hub. Also disclosed is an electrically conductive sheath for grounding an airfoil and a method for assembling a propeller blade assembly. | ||||||
| 72 | Oxidized-zirconium-alloy article and method therefor | US15224602 | 2016-07-31 | US09523143B1 | 2016-12-20 | Jonathan P. Garino; Robert A. Ruggiero, Sr. |
| Described are articles having, at least, an outer surface comprising unalloyed oxidized Zirconium with Niobium having a thickness and configurations suitable for sports equipment, golf clubs, aircraft, boat hulls, motor vehicle, propellers, helicopter rotors, and various other non-medical applications. | ||||||
| 73 | Propeller slipstream enhancer | US12931113 | 2011-01-25 | US20120189457A1 | 2012-07-26 | Anthony C. Occhipinti |
| The invention relates a fluid or air propeller propulsion apparatus using modified state of the art propeller that reduces the typical propeller slipstream disc contraction at the propeller tips, by simply adding a novel channel or trough on the back surface spanwise midway between the leading edge and trailing edge. A portion of the air or fluid flowing over the back face of propeller blade is raked off and collected in the channel during rotation of the propeller, wherein the fluid or air is acted upon by centrifugal force varying directly with the propeller speed causing the fluid or air to be accelerated thru the channel or trough to the trailing edge of the propeller. This additional flow increases the propeller capacity additional jetting action bootstrapping causing the propeller to turn more easily, all of which increases the propeller thrust and efficiency as much as 10 percent. | ||||||
| 74 | Propeller augmentation | US12661648 | 2010-03-22 | US20110229329A1 | 2011-09-22 | Anthony C. Occhipinti |
| The invention relates a fluid or air propeller propulsion apparatus using the state of the art propeller that reduces the typical propeller slipstream disc contraction taking place very close to the propeller tips, containing an inlet slot on the leading edge of the propeller some distance measured from the propeller tips and connected internally to an exit tip slot at the propeller trailing edge. Fluid or air enters the leading edge slot during rotation of the propeller and is acted upon by centrifugal force varying directly with the propeller speed causing the fluid or air to be accelerated thru the internal passage and out the trailing edge exit slot parallel to the cambered face of the propeller at less than a right angle to the trailing edge, inducing flow at zero or low forward speed previously with little or no flow at the propeller tips and at greater speeds, increasing the propeller capacity, and adding an additional jetting action or bootstrapping which causes the propeller to turn more easily, all of which increases the propeller thrust and efficiency. | ||||||
| 75 | Low light level illumination for rotating objects | US10623186 | 2003-07-21 | US20050052880A1 | 2005-03-10 | Thomas Buckingham; Wallace Elger |
| Low light level illumination is applied to rotary blades of vehicles to increase visibility to minimize ground injuries. Either photoluminescent paint or photoluminescent film may be affixed to rotary blades in use to help deter accidents. An electro-luminescent film may be integrated into future rotary blades to provide greater visibility without making the vehicle vulnerable to detection. | ||||||
| 76 | Propeller and impeller blade configuration | US211106 | 1998-12-14 | US6164919A | 2000-12-26 | Arthur Vanmoor |
| A novel concept for a propeller blade configuration incorporates the model of the natural wave behavior. The leading edge of the propeller blade is parallel to the trailing edge, but offset by a given amplitude. The surfaces between the leading and trailing edges are rounded so as to promote proper fluid sheet formation along the surface and to reduce undesirable vortice formation. Best results are obtained by modeling the surfaces along a sine or tangent function. | ||||||
| 77 | Dual-plane blade construction for horizontal axis wind turbine rotors | US586808 | 1990-09-24 | US5161952A | 1992-11-10 | Alfred J. Eggers, Jr. |
| Dual-plant blade construction for wind turbine rotors having a horizontal shaft having a rotor hub adapted to be mounted on the horizontal shaft and having a horizontal axis. First and second sets of straight blades are secured to said rotor hub in circumferentially equally spaced apart positions on the rotor hub. Each of said sets of blades include first and second blades having tip and root portions with the root portions of the blades being secured to the rotor hub at spaced apart positions along the axis of the rotor hub and the tip portions of the blades being secured to each other whereby there is generated substantially equal and opposite cyclic spanwise forces and minimal cyclic flatwise moments in the first and second blades in response to non-steady aerodynamic normal forces acting on these blades in non-uniform turbulent winds. | ||||||
| 78 | Blades for high speed propeller fan | US219390 | 1988-07-15 | US4846629A | 1989-07-11 | Kazunori Takigawa |
| Each blade of a high speed propeller fan extended radially outwardly from a member connected to a rotating body has a coarsened surface at least part of its suction side. The coarsened surface has a coarsened density or depth which gradually increases from the rear edge of the blade to its front edge. | ||||||
| 79 | Method and device for decreasing the flow resistance on wings particularly aerofoils and blades of turbomachines exposed to gas flux such as air | US699226 | 1985-02-07 | US4687416A | 1987-08-18 | Gunther Spranger |
| A device and method for reducing the flow resistance of air foils utilizes one or more flow compressors on the leading edge of the foil. The gas flowing in front of the leading edge is compressed and is expanded on the upper surface of the wing so that through induction of the expanded gas, gas from the area of the lower surface of the wing is admixed to increase the flow on the upper surface of the wing. The direction of the admixed gases is such that the velocity of the gas flowing out at the trailing edge of the wing is identical over the entire wing length. The separation point of the flow is displaced towards the trailing edge of the wind and, in the direction of the tip of the wing, the pressure of the gas flowing over the upper surface of the wing is increased. | ||||||
| 80 | Propeller for gaseous and fluidic media | US750876 | 1985-07-01 | US4636143A | 1987-01-13 | Otto Zeides |
| A propeller for gaseous and fluidic media, particularly an air propeller which is formed with at least one vane mounted to a hub of the propeller and rotatable about a central axis of the propeller. The vane includes two blades extended in the radial direction of the vane. The blades are spaced from each other by an elongated slot formed in the vane and extended in the radial direction of the vane. The slot has the length which is about 40 to 50% of the length of the radius of the vane, defined between the center of rotation of the vane and its tip. | ||||||
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