| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | EROSION RESISTANT BLADE AND BLADE COATING | EP14882408 | 2014-02-14 | EP3105272A4 | 2017-10-18 | KUMAR RAJESH S; BARTH ROBERT A; SCHMIDT WAYDE R |
| 42 | EROSION RESISTANT BLADE AND BLADE COATING | EP14882408.9 | 2014-02-14 | EP3105272A1 | 2016-12-21 | KUMAR, Rajesh S.; BARTH, Robert A.; SCHMIDT, Wayde R. |
| Airfoil blades are disclosed having a coating thereon that includes a polyurethane, a polysiloxane, and a linking agent that promotes a connection between the polyurethane and the polysiloxane. | ||||||
| 43 | PROPELLER | EP13875362 | 2013-12-09 | EP2941539A4 | 2016-09-07 | SHARROW GREGORY CHARLES |
| A propeller having a central post to which one or more blades are connected. The blades are disposed and configured to pull air in from the propeller's sides toward the propeller's axis of rotation to create pressure in an area in the vicinity of the center of the propeller's rotating axis for generating thrust. | ||||||
| 44 | VARIABLE GEOMETRY LIFT FAN MECHANISM | EP13830270.8 | 2013-08-23 | EP2888165A1 | 2015-07-01 | LONG, Geoffrey, A.; LYASOFF, Rodin |
| A vertical takeoff and landing aircraft includes rotors that provide vertical and horizontal thrust. During forward motion, the vertical lift system is inactive. A lift fan mechanism positions the fan blades of the aircraft in a collapsed configuration when the vertical lift system is inactive and positions the fan blades of the aircraft in a deployed configuration when the vertical lift system is active. | ||||||
| 45 | PROPROTOR BLADE WITH LEADING EDGE SLOT | EP03815629.5 | 2003-01-23 | EP1585665B1 | 2008-05-28 | ROBERTSON, Daniel, B.; SMITH, Dudley, E.; HOLLIMON, Charles, L.; NARRAMORE, Jimmy, C.; MULLINS, Robert, B. |
| A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so that a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades. | ||||||
| 46 | DUCTED TURBINE | EP98949489 | 1998-09-24 | EP1015306A4 | 2002-08-07 | FOSDICK GEORGE |
| A turbine (400) has a central duct (410) of non-cylindrical geometry which accelerates fluid passing through it, and a blade configuration which retards the flow of fluid near the tips of the turbine (400). A plurality of blades (408) are arranged in a spiral configuration extending from an external surface (412) of a hollow blade support (401), in which the blades (408) are connected at the tips by tip foils (402). The central duct (410) has an internal surface in the upstream side with a smaller diameter than does the downstream side. The external surface (412) has a smaller diameter at the upstream side than the diameter at the downstream side. In an alternate embodiment, the central duct can have a half venturi shape. The blades (408) have a constant cord width. | ||||||
| 47 | Rotorblatt | EP87730113.5 | 1987-09-28 | EP0295353B1 | 1991-04-17 | Al-Majed, Tahsin |
| 48 | Luftschraube | EP84890156.7 | 1984-08-16 | EP0138800B1 | 1990-05-23 | Asboth, Oscar |
| 1. Airscrew, such as, for example, for driving vehicles having low travelling speeds with high slip, for instance at least 60%, which has a performance factor PI of at least 70% calculated according to the formula : PI = S/3 2Root 2gamma/g . F . L**2 S being the effective thrust in N, gamma/g being the mass of 1 m**3 of air in kg/m**3 , F being the circular area of the screw in m**2 and L being the power consumed in m**2 kg/S**3 , for 100% slip, characterized in that the ratio of the diameter (D) of the airscrew to its pitch (H) of one rotation is about 1.18 to 2.9 times the value of the performance factor and its blade width (B) corresponds to 0.09 to 0.19 times the value of the pitch (H). | ||||||
| 49 | Schraube für gasförmige oder flüssige Medien, insbesondere Luftschraube | EP85107847.7 | 1985-06-25 | EP0166425B1 | 1990-03-14 | Zeides, Otto |
| 50 | Schraube für gasförmige oder flüssige Medien, insbesondere Luftschraube | EP85107847.7 | 1985-06-25 | EP0166425A1 | 1986-01-02 | Zeides, Otto |
Es wird eine Schraube für gasförmige oder flüssige Medien, insbesondere Luftschraube, vorgeschlagen, mit mindestens einem Flügel (11), der zumindest zwei in radialem Abstand vom Drehzentrum sich erstreckende einzelne Flügelblätter (12, 13) aufweist, die unter Belassung eines Zwischenraumes (14) dazwischen mit Abstand voneinander verlaufen. Der Flügel ist zur Bildung der einzelnen Flügelblätter (12, 13) erst ab etwa 40% bis 50% seines ab Drehzentrum gemessenen Radialabstandes beginnend bis zur Flügelspitze durchgehend unter Bildung eines Spaltes (15) geschlitzt, wodurch sich ab Schlitzanfang der bis dahin wie ein normaler Flügel durchgehende Flügelschaft (16) in die beiden einzelnen Flügelblätter (12, 13) aufteilt. Die einzelnen Flügelblätter (12, 13) sind, im Querschnitt betrachtet, entlang der Profilsehne des nichtgeteilten Flügelprofiles hintereinander angeordnet, wodurch sich ein Spaltflügel ergibt. Dadurch ist in dem hinsichtlich entwickelter Schubkräfte erst interessanten Radialbereich eine zweistufige Beschleunigung möglich. Es ergeben sich wesentlich höhere Schubwerte, ein höherer Leistungskoeffizient und bei geringen Kosten, Gewicht und axialen Abmessungen wesentlich reduzierte Lärmemissionswerte. |
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| 51 | NOISE REDUCTION MEANS FOR PROP-FAN. | EP80901388 | 1981-02-09 | EP0032915A4 | 1982-07-28 | HANSON DONALD BURNETT; METZGER FREDERICK BRUCE |
| 52 | PROPELLER | PCT/US2013073811 | 2013-12-09 | WO2014130134A3 | 2015-03-26 | SHARROW GREGORY CHARLES |
| A propeller having a central post to which one or more blades are connected. The blades are disposed and configured to pull air in from the propeller's sides toward the propeller's axis of rotation to create pressure in an area in the vicinity of the center of the propeller's rotating axis for generating thrust. | ||||||
| 53 | Rotor blade having passive bleed path | EP11165283.0 | 2011-05-09 | EP2390178A2 | 2011-11-30 | Denner, Brett W.; Domel, Neal D. |
A rotor blade (14) includes a bleed path (30) opening to a suction surface (28) eg. via inlet (32), extending through the blade (14), eg. via conduit (34), and exiting, eg. via outlet (36), to at least one of the suction surface (28) or a trailing surface (24). Working fluid flows through the bleed path (30) under centrifugal pumping forces when the blade rotates to passively bleed working fluid from the suction surface (28).
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| 54 | Apparatus and method for modulating the lift of a blade airfoil | EP03254503.0 | 2003-07-18 | EP1384896B1 | 2010-03-31 | Saddoughi, Seyed Gholmali; Leyva, Ivett Alejandra; Dean, Anthony John; Robic, Bernard Francois; Butler, Lawrence |
| 55 | PROPROTOR BLADE WITH LEADING EDGE SLOT | EP03815629 | 2003-01-23 | EP1585665A4 | 2007-09-12 | ROBERTSON DANIEL B; SMITH DUDLEY E; HOLLIMON CHARLES L; NARRAMORE JIMMY C; MULLINS ROBERT B |
| A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so that a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades. | ||||||
| 56 | Motorgetriebener Propeller für einen Flugkörper und Verfahren zur Bearbeitung eines Propellers | EP06000679.8 | 2006-01-13 | EP1808372A1 | 2007-07-18 | Riegerbauer, Hermann |
Motorgetriebener Propeller (1) für einen Flugkörper und Verfahren für einen motorgetriebener Propeller (1) mit einer Nabe (2) zur Befestigung an einer mit dem Motor in Drehverbindung stehender Antriebswelle und mit mindestens zwei um eine Propellerachse, sich von einer Nabe wegerstreckende Propellerblätter (3), wobei die Propellerblätter (3) jeweils einen zum Drehmittelpunkt spiegelsymmetrisch umgekehrt verlaufenden Anstellwinkel aufweisen und wobei Elemente (4) vorhanden sind, die derart am Propeller (1) angebracht sind, dass die Effizienz des Propellers gesteigert wird.
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| 57 | LOW LIGHT LEVEL ILLUMINATION FOR ROTATING OBJECTS | EP03765842.4 | 2003-07-22 | EP1540239A2 | 2005-06-15 | BUCKINGHAM, Thomas, M.; ELGER, Wallace, M. |
| Low light level illumination is applied to rotary blades (102, 202) of vehicles to increase visibility to minimize ground injuries. Either photoluminescent paint (208) or photoluminescent film (104) may be affixed to rotary blades (102, 202) in use to help deter accidents. An electro-luminescent film (509) may be integrated into future rotary blades (502) to provide greater visibility without making the vehicle vulnerable to detection. | ||||||
| 58 | Method and apparatus for modulating airfoil lift | EP03254503.0 | 2003-07-18 | EP1384896A2 | 2004-01-28 | Saddoughi, Seyed Gholmali; Leyva, Ivett Alejandra; Dean, Anthony John; Robic, Bernard Francois; Butler, Lawrence |
An apparatus (100) comprising: an airfoil (110) adapted for generating a lift force; and a first pulse detonation actuator (120) disposed inside the airfoil (110) and adapted for impulsively detonating a fuel/air mixture to produce a pressure rise and velocity increase of combustion products therein, the airfoil (110) having a plurality of lift control holes (130) adapted for communicating combustion product flows from the first pulse detonation actuator (120) to an airfoil surface (140) to modulate the lift force. |
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| 59 | DUCTED TURBINE | EP98949489.3 | 1998-09-24 | EP1015306A1 | 2000-07-05 | FOSDICK, George |
| A turbine (400) has a central duct (410) of non-cylindrical geometry which accelerates fluid passing through it, and a blade configuration which retards the flow of fluid near the tips of the turbine (400). A plurality of blades (408) are arranged in a spiral configuration extending from an external surface (412) of a hollow blade support (401), in which the blades (408) are connected at the tips by tip foils (402). The central duct (410) has an internal surface in the upstream side with a smaller diameter than does the downstream side. The external surface (412) has a smaller diameter at the upstream side than the diameter at the downstream side. In an alternate embodiment, the central duct can have a half venturi shape. The blades (408) have a constant cord width. | ||||||
| 60 | Propeller, dessen Blätter mit einem Vorflügel versehen sind | EP88109182.1 | 1988-06-09 | EP0297321B1 | 1990-08-16 | Kallergis, Michael, Dipl.-Ing. |
