| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | Disc rotor retraction system | EP12157385.1 | 2012-02-28 | EP2492192A2 | 2012-08-29 | Podgurski, Daniel Michael |
A disc rotor blade retraction system includes a main blade spar (22) incorporating a hydraulic cylinder (54) and having a screw thread (34). A ball screw (24) is concentrically carried within the main blade spar and is operably connected to a ball nut (60) which has an outboard end connected to an intermediate spar (26) with a hydraulic piston (62) received for reciprocation in the hydraulic cylinder. A first geared actuator (20) engages the ball screw and a second geared actuator (30) engages the main blade spar screw thread. A hydraulic fluid accumulator (74) providing pressurized hydraulic fluid is connected to an outboard end of the hydraulic cylinder and a controller actuates the first and second geared actuators.
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| 102 | VARIABLE-DIAMETER ROTOR WITH CENTRIFUGAL FORCES COMPENSATION MECHANISM | EP08737551.5 | 2008-04-28 | EP2162353B1 | 2010-10-06 | TURMANIDZE, Raul; CHKOIDZE, Malkhaz; JOJUA, Nodari |
| A variable-diameter rotor comprises a hub with a shaft and rotor blades mounted on the hub, wherein each one of the rotor blades comprises a radially internal blade part (6), which is radially stationary, and a radially external blade part, which is radially movably mounted on the radially internal blade part.. In each of the rotor blades, a jackscrew mechanism arranged therein includes a jackscrew arranged in the radially internal blade part and a nut connected with the radially external blade part, the nut cooperating with the jackscrew for radially moving the radially external blade part with respect to the radially internal blade part. The rotor further comprises an energy storage system, including a compressed-gas accumulator (18). The compressed-gas accumulator comprises a volume of gas and a piston (19) for compressing and expanding the volume of pressurized gas. The energy storage system also includes means (11-15) for converting a radial motion of the radially external blade part into a motion of the piston of the compressed-gas accumulator and vice-versa, the compressed gas accumulator being arranged on the rotor shaft. | ||||||
| 103 | VARIABLE-DIAMETER ROTOR WITH CENTRIFUGAL FORCES COMPENSATION MECHANISM | EP08737551.5 | 2008-04-28 | EP2162353A1 | 2010-03-17 | TURMANIDZE, Raul; CHKOIDZE, Malkhaz; JOJUA, Nodari |
| A variable-diameter rotor comprises a hub with a shaft and rotor blades mounted on the hub, wherein each one of the rotor blades comprises a radially internal blade part (6), which is radially stationary, and a radially external blade part, which is radially movably mounted on the radially internal blade part.. In each of the rotor blades, a jackscrew mechanism arranged therein includes a jackscrew arranged in the radially internal blade part and a nut connected with the radially external blade part, the nut cooperating with the jackscrew for radially moving the radially external blade part with respect to the radially internal blade part. The rotor further comprises an energy storage system, including a compressed-gas accumulator (18). The compressed-gas accumulator comprises a volume of gas and a piston (19) for compressing and expanding the volume of pressurized gas. The energy storage system also includes means (11-15) for converting a radial motion of the radially external blade part into a motion of the piston of the compressed-gas accumulator and vice-versa, the compressed gas accumulator being arranged on the rotor shaft. | ||||||
| 104 | METHODS AND SYSTEMS FOR STARTING PROPELLER-DRIVEN DEVICES | EP04810203.2 | 2004-11-01 | EP1687200A2 | 2006-08-09 | SLIWA, Steven, M.; VON FLOTOW, Andreas, H.; DENNIS, Brian, D. |
| Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one portion exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link between the fixture and the propeller. | ||||||
| 105 | ROTOR SYSTEM HAVING ALTERNATING LENGTH ROTOR BLADES FOR REDUCING BLADE-VORTEX INTERACTION (BVI) NOISE | EP96942814.3 | 1996-11-27 | EP0866765B1 | 1999-05-12 | VISINTAINER, Joseph, A.; MOFFITT, Robert, C. |
| A rotor system (4) having odd and even blade assemblies (Ob, Eb) mounting to and rotating with a rotor hub assembly (6) wherein the odd blade assemblies (Ob) define a radial length RO, and the even blade assemblies (Eb) define a radial length RE and wherein the radial length RE is between about 70 % to about 95 % of the radial length RO. Other embodiments of the invention are directed to a Variable Diameter Rotor system (4) which may be configured for operating in various operating modes for optimizing aerodynamic and acoustic performance. The Variable Diameter Rotor system (4) includes odd and even blade assemblies (Ob, Eb) having inboard and outboard blade sections (10, 12) wherein the outboard blade sections (12) telescopically mount to the inboard blade sections (10). A positioning means (70) is provided for positioning the outboard blade sections (12) with respect to the inboard blade sections (10) such that the radial length RE of the even blade assemblies (Eb) is equal to the radial length RO of the add blade assemblies (Ob) in a first operating mode, and such that the radial length RE is between about 70 % to about 95 % of the length RO in a second operating mode. | ||||||
| 106 | ROTOR SYSTEM HAVING ALTERNATING LENGTH ROTOR BLADES FOR REDUCING BLADE-VORTEX INTERACTION (BVI) NOISE | EP96942814.0 | 1996-11-27 | EP0866765A1 | 1998-09-30 | VISINTAINER, Joseph, A.; MOFFITT, Robert, C. |
| A rotor system (4) having odd and even blade assemblies (Ob, Eb) mounting to and rotating with a rotor hub assembly (6) wherein the odd blade assemblies (Ob) define a radial length RO, and the even blade assemblies (Eb) define a radial length RE and wherein the radial length RE is between about 70 % to about 95 % of the radial length RO. Other embodiments of the invention are directed to a Variable Diameter Rotor system (4) which may be configured for operating in various operating modes for optimizing aerodynamic and acoustic performance. The Variable Diameter Rotor system (4) includes odd and even blade assemblies (Ob, Eb) having inboard and outboard blade sections (10, 12) wherein the outboard blade sections (12) telescopically mount to the inboard blade sections (10). A positioning means (70) is provided for positioning the outboard blade sections (12) with respect to the inboard blade sections (10) such that the radial length RE of the even blade assemblies (Eb) is equal to the radial length RO of the add blade assemblies (Ob) in a first operating mode, and such that the radial length RE is between about 70 % to about 95 % of the length RO in a second operating mode. | ||||||
| 107 | VARIABLE DIAMETER ROTOR DRIVE SYSTEM. | EP93919838 | 1993-07-27 | EP0651713A4 | 1997-02-26 | FRADENBURGH EVAN A; MILLER GORDON GLENN |
| A drive system for varying the diameter of a variable diameter rotor has a gear assembly associated with a single coaxial shaft (13) lower end which includes a gear set for increasing the speed of rotation of the central shaft (13) relative to the rotor drive shaft (2) to change the diameter of the variable diameter blades. A pair of brakes are used, one (37) to slow the coaxial shaft relative to the drive shaft and another (25) to lock the rotor shaft (2) and coaxial shaft (13) together for corotation during constant diameter flight conditions. Utilizing a lower gear assembly reduces hub complexity and allows the variable diameter rotor drive system to be adapted to gimballed rotors which require shaft flexibility. Since only a single shaft extends through the rotor drive shaft, hub complexity is reduced. | ||||||
| 108 | METHODS AND SYSTEMS FOR STARTING PROPELLER-DRIVEN DEVICES | PCT/US2004036349 | 2004-11-01 | WO2005042342A3 | 2006-06-29 | SLIWA STEVEN M; VON FLOTOW ANDREAS H; DENNIS BRIAN D |
| Method and systems for starting propeller driven aircraft and other devices. A system in accordance with one embodiment of the invention includes a removable fixture (130) that is coupled to the propeller (120) and has at least one portion (131a) exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine (110) begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link (132) between the fixture and the propeller. | ||||||
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