| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | Aircraft-propeller | US30009419 | 1919-05-27 | US1401537A | 1921-12-27 | WITT HILL JAMES DE |
| 182 | Woody | US1385908D | US1385908A | 1921-07-26 | ||
| 183 | Propeller | US30419119 | 1919-06-14 | US1378113A | 1921-05-17 | COOPER HEWITT PETER |
| 184 | Aerial propeller | US19509817 | 1917-10-06 | US1344496A | 1920-06-22 | FLATTUM ALBERT L |
| 185 | Propeller | US619136D | US619136A | 1899-02-07 | ||
| 186 | Screw-propeller | US553953D | US553953A | 1896-02-04 | ||
| 187 | Paddle-wheel for steamships | US522827D | US522827A | 1894-07-10 | ||
| 188 | Aircraft with Active Aerosurfaces | US15606163 | 2017-05-26 | US20180339771A1 | 2018-11-29 | Paul K. Oldroyd; John Richard McCullough |
| An aircraft operable to transition between a forward flight mode and a vertical takeoff and landing flight mode. The aircraft includes an airframe having first and second wings. A plurality of propulsion assemblies is attached to the airframe with each of the propulsion assemblies including a nacelle and a tail assembly having at least one active aerosurface. A flight control system is operable to independently control each of the propulsion assemblies. For each of the propulsion assemblies, the tail assembly is rotatable relative to the nacelle such that the active aerosurface has a first orientation generally parallel to the wings and a second orientation generally perpendicular to the wings. | ||||||
| 189 | TURBINE ENGINE AIRFOIL WITH A MODIFIED LEADING EDGE | US15471729 | 2017-03-28 | US20180283180A1 | 2018-10-04 | Nitesh Jain; Abhijeet Jayshingrao Yadav; Kishore Budumuru; Nicholas Joseph Kray |
| A turbine engine can comprise a fan section, compressor section, a combustion section, and a turbine section in axial flow arrangement. At least one of the fan section and compressor section can include an airfoil with a leading edge, and a plurality of riblets can be arranged on the leading edge. | ||||||
| 190 | PROPELLER | US15897767 | 2018-02-15 | US20180186439A1 | 2018-07-05 | Gregory Charles Sharrow |
| A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction. | ||||||
| 191 | Propeller | US15605764 | 2017-05-25 | US09926058B2 | 2018-03-27 | Gregory Charles Sharrow |
| A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction. | ||||||
| 192 | Aircraft propeller warning illuminator | US14545745 | 2015-06-15 | US20160362193A1 | 2016-12-15 | Ian Gill Bemis |
| An aircraft ground safety device that illuminates the blades of a spinning aircraft propeller with bright colored light in order to improve visual awareness of the danger zone created by an otherwise inviable propeller spinning at high RPM. The device consists of lighting fixtures (typically LEDs in the currently envisioned embodiment of the invention) mounted on the propeller blades of an aircraft that display the aircraft propeller as a brightly colored disk of light when the propellers are spinning, as well as an electrical power supply to the aforementioned lighting array, provided by a slip ring connector and powered by the by the electrical system of the aircraft. The lighting array is intended to activate whenever the blades are in motion to further the aim of safety in aviation. | ||||||
| 193 | METHOD AND APPARATUS FOR INHIBITING FORMATION OF AND/OR REMOVING ICE FROM AIRCRAFT COMPONENTS | US15076598 | 2016-03-21 | US20160280379A1 | 2016-09-29 | 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. | ||||||
| 194 | Method and apparatus for inhibiting formation of and/or removing ice from aircraft components | US13204630 | 2011-08-05 | US09327839B2 | 2016-05-03 | 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 between about 1 Hz and about 1 kHz; 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. | ||||||
| 195 | Rotor blade having passive bleed path | US12790091 | 2010-05-28 | US20110293421A1 | 2011-12-01 | Brett W. Denner; Neal D. Domel |
| A rotor blade includes a bleed path opening to a suction surface, extending through the blade, exiting to at least one of the suction or a trailing surface, and through which working fluid flows under centrifugal pumping forces when the blade rotates, to passively bleed working fluid from the suction surface. | ||||||
| 196 | VARIABLE PITCH AFT PROPELLER VANE SYSTEM | US12501520 | 2009-07-13 | US20100014977A1 | 2010-01-21 | Colman D. Shattuck |
| A propulsion system includes a rotationally fixed variable pitch vane system located axially aft of a propeller system. | ||||||
| 197 | Rotor with a split rotor blade | US10030564 | 2002-04-12 | US06736600B1 | 2004-05-18 | Rudolf Bannasch |
| A rotor through which a fluid flows in a main direction of flow, provided with at least one rotor blade, the rotor blade being arranged to rotate about a rotor axis. The rotor blade extends away from the axis of rotation into the field. To reduce the trailed tip vortex at the end of the rotor blades, the fluidic losses, and flow noise, the rotor blade is split in at least two partial blades at a set distance from the axis of rotation and forms a loop. One partial blade extends in the direction of rotation in relation to the rotor blade. The other partial blade extends in a direction opposite the direction of rotation to the rotor blade. The two partial blades are interconnected in one piece at their ends, to encompass a loop surface extending essentially crosswise to the main direction of flow, through which the fluid flows. | ||||||
| 198 | Ducted turbine | US160775 | 1998-09-24 | US6053700A | 2000-04-25 | George A. Fosdick |
| A turbine 400 has a central duct 410 which accelerates fluid passing through it and a blade configuration which retards the flow of fluid near the tips of the turbine. This structure results in a vortex having a higher fluid pressure behind the tips of the turbine blades 408 and a lower fluid pressure behind the duct. In the present invention, this vortex is enhanced by (1) an increased acceleration of the fluid passing through the duct 410 and a deceleration of the fluid passing through the blades 408; and/or (2) by a fluid redirection device 850 for directing the fluid passing through the duct towards the outer diameter of the turbine. | ||||||
| 199 | Air propeller | US212049 | 1988-06-24 | US4927330A | 1990-05-22 | Oscar Asboth |
| A propeller is used to displace a vehicle at a reduced speed but with a high slip of approximately at least 60% and has a quality coefficient of at least 70% for 100% slip. The ratio of the diameter of the propeller to its pitch is approximately 1.18 to 2.9 times the value of the quality coefficient, and the blade width of the propeller is 0.09 to 0.19 times the pitch of the propeller. The propeller pitch is substantially constant and the aerodynamic center of pressure is located at a distance from the propeller axis of rotation equl to approximately 3/4 of the propeller radius. The radius of the curvature of the leading propeller edge, when seen in cross section, is to approximately 1/4 to 1/3 of the greatest blade thickness. In addition the angle of the blade inclination decreases continuously as the propeller diameter increases and the blade thickness is greatest in the leading third of the blade width, relative to the normal rotation direction of the propeller. | ||||||
| 200 | Propeller whose blades are provided with slats | US210115 | 1988-06-22 | US4840540A | 1989-06-20 | Michael Kallergis |
| Directly driven propeller whose propeller blades are provided with slats and which is designed for a lower blade tip Mach number in order to reduce the propeller noise. The slats are rigidly connected to the propeller blades and the slat tips lie on a diameter given by the equation ##EQU1## where LTLP=lower transonic limit of the particular blade configuration including slata.sub.o =velocity of sound in airv.sub..infin. =flight speedn=propeller rotational speed. | ||||||
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