| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | 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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| 142 | ROTOR A STRUCTURE EN NID D'ABEILLE CIRCULAIRE | EP04714335.9 | 2004-02-25 | EP1719918A1 | 2006-11-08 | Sanchez Sanchez, Felix |
Rotor rond en nid d'abeilles pour améliorer le rendement des hélices conventionnelles dans son usage comme rotor pour engins volants, motopompes, embarcations, ainsi que pour toutes applications hydrauliques ou pneumatiques, disposant de pièces hélicoïdales initiées dans son cube ou noyau circulaire et montées sur un ou plusieurs cylindres tubulaires et concentriques entre eux. Le cylindre de plus grand diamètre sera prolongé par une pièce en forme de tronc conique afin de contrôler et diriger la sortie des forces centrifuges tandis que les pièces hélicoïdales sont présentés comme des trapèzes hélicoïdaux, lesquels accouplés les uns sur les autres forment un nid d'abeilles rond qui ferme dans sa totalité les périmètres extérieurs, ce qui permet le rassemblement de toutes les forces centrifuges et augmente d'un 10% ou plus le rendement des hélices classiques dans n'importe quel de ses multiples usages. |
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| 143 | DUCTED AIR POWER PLANT | EP03761692.7 | 2003-06-27 | EP1534590A1 | 2005-06-01 | BRYANT, Ashley Christopher |
| A ducted air power plant, comprising a motor driven fan (7) situated in a duct (4), the fan (7) having an air intake side and in operation providing a high pressure air stream in the duct, and the fan being located adjacent air splitter means (18), the air splitter means (18) being arranged to divert the air stream into two or more subsidiary streams for delivery to respective jet nozzles (9) of the plant. The plant may be used in a vehicle such as an aircraft in order to provide a vertical take-off and hover capability as well a level flight power source. | ||||||
| 144 | IMPROVED VERTICAL TAKE-OFF AND LANDING VEHICLES | EP03709001.6 | 2003-02-06 | EP1478570A2 | 2004-11-24 | MOLLER, Paul, S. |
| A VTOL vehicle including a fuselage with two foldable wings, two tiltable nacelles attached to the wings, a vertical stabilizer, a horizontal stabilizer, and two auxiliary thrusters. Each nacelle contains a system of vanes located at the rear opening thereof, and actuators are provided for extending and retracting the vanes in conjunction with nacelle tilting mechanisms to deflect the airflow over a predetermined range of angles from the horizontal. Each nacelle also contains two rotary engines, each of which directly drives a fan. The fans face each other and operate in counter-rotating directions at the same rotational speed. An alternative embodiment includes two additional nacelles attached to the fuselage instead of having the auxiliary thrusters. A redundant computerized flight control system maintains stability of the vehicle as it transitions from one flight mode to another. | ||||||
| 145 | VERTICAL LIFT FLYING CRAFT | EP02706116.7 | 2002-01-31 | EP1441946A2 | 2004-08-04 | Baldwin, Gilbert |
| A disclosed vertical lift flying craft (10) includes a lift unit (20) that, during operation, develops a force including an upward component. A payload unit (50) suspends from the lift unit (20). The payload unit (50) suspends from the lift unit (20) in such a way as to impart lateral stability while remaining capable of horizontal flight, without incurring the adverse effects of a downward pitching moment. In addition to a lift unit (20) and a payload unit (50), the vertical lift flying craft includes a pair of bearings (26, 65) and a suspension structure (60), which cooperate to suspend the payload unit (50) from the lift unit (20). Other systems and methods are also disclosed. | ||||||
| 146 | VORTEX GENERATOR | EP00978281.4 | 2000-10-27 | EP1224396A1 | 2002-07-24 | REINFELD, David; ILLINGWORTH, Lewis |
| A vortex generating apparatus (60) has the capability of attracting and removably adhering one or more solid objects. The apparatus (60) comprises an impeller housed within a shell. The vortex attractor generates a vortical fluid flow (69a) generally in the form of a helical or spiral shaped flow. The fluid flow (69a) creates a low pressure region extending from the impeller end of the device. This low pressure region is contained by the walls of the fluid flow, thus directing the attractive forces toward a surface and minimizing effects of ambient fluid on the system. When the surface is part of a stationary object, wall, floor or ceiling, the vortex attractor may move toward and adhere to the surface. When the surface is part of a movable object, the vortex attractor may attract the object and maintain the attracted position. | ||||||
| 147 | PROPULSIVE THRUST RING SYSTEM. | EP92912005 | 1992-05-28 | EP0586511A4 | 1994-11-17 | LEMONT HAROLD E |
| a low-aspect ratio propeller system is provided with a multiple ring structure (42) formed with a plurality of circular or non-circular, annular, narrow equivalent air foil rings (56.1, 56.2, 56.3, 56.4) which are held by rails (40) in a predetermined relationship with the propeller blades (44). The upstream ring (56.1) is located downstream from the tip vortex of the propeller (44) within the axial span of the propeller. One or more additional downstream-located rings (56.2, 56.3, 56.4) are used so as to provide at least one annular multiple ring-defined pump aperture (60, 62, 64) through which peripheral vortices generated by the propeller blades (44) or fan blades may enhance the mass flow. These vortices increase thrust because their induction action on the rings (56.1, 56.2, 56.3, 56.4) increase beneficial ring flow circulation. Augmented ring flow reduces the velocities in the expanding wake by increasing the mass flow. The destruction of tip and root vortices reduces noise. The multiple ring structure (42) also serves as a guard. | ||||||
| 148 | PROPULSIVE THRUST RING SYSTEM | EP92912005.0 | 1992-05-28 | EP0586511A1 | 1994-03-16 | LEMONT, Harold, E. |
| Un système d'hélice à faible rapport d'allongement est pourvu d'une structure (42) à anneaux multiples composée d'une multiplicité d'anneaux sustentateurs (56.1, 56.2, 56.3, 56.4) circulaire ou non, annulaire, étroits et équivalents, qui sont maintenus par des barres (40) en un rapport prédéterminé avec des pales de l'hélice (44). L'anneau amont (56.1) est placé en aval par rapport à l'extrémité du tourbillon (44) de l'hélice dans l'envergure axiale de l'hélice. Un ou plusieurs anneaux additionnels (56.2, 56.3, 56.4) situé(s) en aval sont utilisés pour former au moins une ouverture de pompage (60, 62, 64) annulaire définie par plusieurs anneaux, et à travers laquelle des tourbillons périphériques produits par les pales d'hélice (44) ou de la soufflante peuvent augmenter le flux massique. Ces tourbillons augmentent la poussée du fait que leur effet d'induction sur les anneaux (56.1, 56.2, 56.3, 56.4) augmentent une circulation de flux annulaire. Le flux annulaire augmenté réduit les vitesses dans le sillage qui va s'élargissant en augmentant le flux massique. L'annulation des tourbillons d'extrémité et de base permet de réduire le bruit. La structure à plusieurs anneaux (42) sert aussi d'élément de protection. | ||||||
| 149 | Hoop fan jet engine | EP86202089.8 | 1986-11-24 | EP0244515A3 | 1989-04-12 | Seidel, Gerhard E. |
A fan jet engine assembly comprising a hoop fan surrounding a turbojet (19) is disclosed. The hoop fan includes a pair of rotatable hubs (27, 29) that encircle the turbojet. A stage of fan blades (31, 33) is attached to each hub (27, 29) and radiates outwardly therefrom. The tips of the blades (31, 33) of at least one of the stages are attached to a hoop (23/25 or 61) that encircles the tips of the blades (31, 33) of both stages. Due to the attachment of the hoop (23/25 or 61) to the blades (31, 33), the hoop rotates as the hubs (27, 29) are rotated by the turbojet (19). The pitch of the blades of at least one of the stages is adjustable. |
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| 150 | Ducted propeller | EP82108312.8 | 1980-04-30 | EP0070578B1 | 1989-02-01 | Edgley, John Kelsey |
| 151 | Configuration of propellers, shrouded propellers and/or fans to decrease the noise of and the cyclic loads on the blades | EP87100841 | 1987-01-22 | EP0233501A3 | 1988-11-30 | FISCHER, HANS-OTTO; HOSEMANN, SIEGFRIED |
| 152 | Ausbildung von im Zustrom zu Luftschrauben, Mantelschrauben und/oder Fans liegenden Bauteilen zur Verringerung des von ihnen verursachten Zusatzlärms sowie zur Verringerung der Wechselbelastung der Propellerblätter | EP87100841.3 | 1987-01-22 | EP0233501A2 | 1987-08-26 | Fischer, Hans-Otto; Hosemann, Siegfried |
Im Zustrom von Luftschrauben, Mantelschrauben und/oder Fans liegende Bauteile (1) werden zur Vermidnerung des von ihnen verursachten Zusatzlärms sowie zur Verringerung der Wechselbelastung der Propellerblätter (4) einer besonderen Formgebung und Anordnung unterzogen. |
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| 153 | Ducted propeller | EP82108312.8 | 1980-04-30 | EP0070578A2 | 1983-01-26 | Edgley, John Kelsey |
For quiet and efficient operation of a propeller (13) driven aircraft, a prime mover (29) is mounted rigidly to a shroud (26) which fits closely around the propeller (13), the propeller (13) is mounted rigidly to the prime mover (29) and the shroud (26) is provided with resilient mounting means (25) for making fast in its operative position the power unit so formed and for isolating vibrations of the prime mover (29) in the power unit. |
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| 154 | VERTICAL TAKEOFF AND LANDING AIRCRAFT | EP13873269.8 | 2013-12-17 | EP2899122B1 | 2018-11-28 | TSUNEKAWA, Masayoshi; TAMURA, Tetsuya |
| A vertical take-off and landing aircraft including a propulsion mechanism 2 that generates lift and thrust, a main frame 4 that supports seating 41 and a landing undercarriage 42, a subframe 5 which supports the propulsion mechanism 2 and which is arranged so as to be swingable back and forth relative to the main frame 4, motive power supply means 3 supported by the main frame 4 and supplying motive power to the propulsion mechanism 2, and a control stick 6 connected to the subframe 5, in which the propulsion mechanism 2 includes a pair of ducted fans 21L, 21R arranged on a left side and a right side, respectively, of the main frame 4, swing shafts 22 arranged in the ducted fans 21L, 21R and extending in a horizontal direction, and control vanes 23 connected to the swing shafts 22, and swinging the control vane 23 enables the subframe 5 to move relative to the main frame 4. Maneuverability can be improved with addition of control mechanisms restrained. | ||||||
| 155 | Propeller gas turbine engine | EP13171359.6 | 2013-06-11 | EP2685065B1 | 2018-11-28 | Stretton, Richard; Howarth, Nicholas |
| A gas turbine engine (10) having an axial flow direction (X) therethrough in use. The gas turbine engine (10) comprises one or more rotor stages each comprising at least one rotor blade (120) having a root portion (122). The gas turbine engine (10) comprises a shroud (126) located upstream of one or more of the rotor stages relative to the axial flow direction (X). The shroud (126) defines a through passageway (128) extending between an inlet (130) and an outlet (132) which comprises a diffuser region (138). The diffuser region (138) is configured to reduce the axial velocity of air exiting the outlet (132) relative to air entering the diffuser portion (138) in use, wherein the outlet (132) is located such that air exiting the outlet (132) is directed substantially to the root portion (122) only of the rotor blades (120). | ||||||
| 156 | A THRUST PRODUCING UNIT WITH AT LEAST TWO ROTOR ASSEMBLIES AND A SHROUDING | EP17400003.4 | 2017-01-26 | EP3354559A1 | 2018-08-01 | Mores, Sebastian; Kiesewetter, Uwe; Bebesel, Marius |
The invention is related to a thrust producing unit 3d for producing thrust in a predetermined direction 23, comprising a shrouding 6d and at least two rotor assemblies 7d, 8d, wherein the shrouding 6d defines an internal volume 20c, and wherein a first rotor assembly 7d of the at least two rotor assemblies 7d, 8d defines a first rotor axis and a second rotor assembly 8d of the at least two rotor assemblies 8d defines a second rotor axis, the first and second rotor axes 12d being one of: (i) coaxially arranged, and (ii) inclined by associated inclination angles 21a, 22a with respect to the predetermined direction 23, the associated inclination angles 21a, 22a being comprised in a range between -60° and +60°, and preferably amounting to 0°, and wherein the first rotor assembly 7d is arranged outside of the internal volume 20c of the shrouding 6d.
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| 157 | PROPELLER HAVING EXTENDING OUTER BLADES | EP16829009.6 | 2016-07-06 | EP3328729A2 | 2018-06-06 | LINCH, Jonathon J.; RAHRIG, Kyle M. |
| A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. The ring shroud includes an inner ring surface and a radially spaced, oppositely facing outer ring surface. At least one propeller blade is fixedly attached to both the hub and the inner ring surface and extends radially therebetween for mutual rotation therewith. At least one extending blade has a first extending blade end radially spaced from a second extending blade end. The first extending blade end is fixedly attached to the outer ring surface. The second extending blade end is cantilevered from the first extending blade end and is radially spaced from the ring shroud. | ||||||
| 158 | THRUST RING AND ROTOR FAN SYSTEM | EP17194522.3 | 2017-10-03 | EP3315787A1 | 2018-05-02 | Power, Bronwyn; Rivers, Jonathan |
A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about -5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.
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| 159 | Aircraft lift transducer | EP14199448.3 | 2014-12-19 | EP2889600B1 | 2017-07-26 | Tiseo, Joseph S.; Greene, Randall A. |
| An aircraft lift transducer may include a vane, actuator, an LC circuit, and a processor. The vane may be positioned on the leading edge of a wing of the aircraft, where the angle defined by the chord of the wing and the vane changes when the aircraft angle of attack changes. The actuator may be associated with the vane and change position when the angle defined by the vane and the chord changes. The LC circuit may include an induction coil spaced from the actuator and an oscillator. The oscillation frequency of the LC circuit may change when the position of the actuator changes. The processor may receive the change in the oscillation frequency and may determine a corresponding change in an available lift of the aircraft. | ||||||
| 160 | A propulsion unit for an aircraft | EP12185886.4 | 2012-09-25 | EP2578490A3 | 2017-07-19 | Brown, Stephen; Raffaelli, Lorenzo |
This invention relates to a propulsive unit (10) for an aircraft, comprising: a nacelle (12) which defines a duct (20) for channelling an airflow when in use and which provides an outwardly facing surface (14) of the propulsive unit (10), the outwardly facing surface (14) having an aerodynamic shape; a fan unit (16) for accelerating the airflow within the duct (20) when in use; wherein the duct (20) has an inlet (26) and an outlet (28) and the nacelle (12) is operable to adjust the either or both of the area of the inlet (26) and outlet (28) whilst substantially retaining the aerodynamic shape of the outwardly facing surface.
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