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1. 发明授权

US09701407B2 Emergency stop for blades of drone 有权
公开(公告)号：US09701407B2
公开(公告)日：2017-07-11
申请号：US14666708
申请日：2015-03-24
申请人： Sharper Shape Oy
发明人： Atte Korhonen , Tero Heinonen
IPC分类号： B64C11/20 , B64C39/02 , B64C27/00 , B64C11/00 , B64C27/473
CPC分类号： B64C39/024 , B64C11/002 , B64C11/20 , B64C27/006 , B64C27/473 , B64C2201/027 , F05D2260/902
摘要： Disclosed is a drone having at least one rotor. The at least one rotor comprises a mast and at least two blades having a proximal end and a distal end. The at least two blades are arranged in connection with the mast by their proximal ends. The at least one of the blades comprises an electrically conductive element extending a distance D between its distal end and its proximal end. The electrically conductive element is electrically coupled with means for stopping the blades, thus forming an electrical circuit. The means for stopping the blades is arranged to be actioned when at least one electrical property of the electrical circuit change.

2. 发明申请

US20170126159A1 GENERATION SYSTEM WITH BRAKING MECHANISM 审中-公开
公开(公告)号：US20170126159A1
公开(公告)日：2017-05-04
申请号：US14926708
申请日：2015-10-29
申请人： Hamilton Sundstrand Corporation
发明人： Todd A. Spierling , Glenn C. Lemmers, JR.
IPC分类号： H02P9/06 , F16H1/28 , H02K7/18 , H02K7/102 , H02K7/116
CPC分类号： H02P9/06 , F01D21/006 , F02C6/20 , F02C7/36 , F05D2220/76 , F05D2260/40311 , F05D2260/90 , F05D2260/902 , F16H1/28 , H02K7/102 , H02K7/116 , H02K7/1823
摘要： An electrical power generation system for a vehicle includes a prime mover, an electrical generator to generate electrical power and a gear box operably connected to the prime mover and the electrical generator to transfer rotational energy from the prime mover to the electrical generator. A braking mechanism is located at the gear box to selectably transfer rotational energy from the prime mover to the electrical generator for selective generation of electrical power. A method of electrical power generation for a vehicle includes generating rotational energy at a prime mover, transferring the rotational energy to an electrical power generator, generating electrical power via the rotational energy transfer to the electrical power generator, and periodically stopping and/or starting the transfer of rotational energy from the prime mover to the electrical power generator via a braking mechanism in operable communication with the electrical power generator.

3. 发明申请

US20160006375A1 DEVICE FOR CONTROLLING A NOZZLE OF VARIABLE CROSS-SECTION OF AN AIRCRAFT 审中-公开
标题翻译：用于控制飞机可变交叉部分的喷嘴的装置
公开(公告)号：US20160006375A1
公开(公告)日：2016-01-07
申请号：US14269809
申请日：2014-05-05
申请人： AIRBUS OPERATIONS (S.A.S.)
发明人： Guillaume BULIN , Armand RUGGERI
IPC分类号： H02P3/08 , F02K1/16
CPC分类号： H02P3/08 , F02K1/09 , F02K1/15 , F02K1/16 , F05D2260/40 , F05D2260/57 , F05D2260/84 , F05D2260/902 , Y02T50/677
摘要： The invention relates to a control device of a nozzle of variable cross-section of an aircraft suitable for providing a three-phase AC electrical power supply, the nozzle of variable cross-section comprising one or more movable parts which make it possible to modify the cross-section of the nozzle, the control device comprising a system for regulation of the engine connected to a control element which drives at least one electric motor which by a mechanical transmission system creates the movement of the movable part or parts, wherein the electric motor is configured to use directly the electrical power supply of the aircraft and in that the control element comprises analogue type structure to switch the phases of the electrical power supply to modify the direction of rotation of the electric motor.
摘要翻译：本发明涉及适用于提供三相交流电源的飞机的可变横截面的喷嘴的控制装置，该可变横截面的喷嘴包括一个或多个可移动部件，这使得可以修改喷嘴的横截面，所述控制装置包括用于调节连接到控制元件的发动机的系统，所述控制元件驱动至少一个电动机，所述电动机通过机械传动系统产生可移动部件的运动，其中所述电动机被配置为直接使用飞机的电源，并且控制元件包括用于切换电源的相位的模拟型结构，以改变电动机的旋转方向。

4. 发明申请

US20150285156A1 SYSTEMS AND METHODS FOR CHANGING A SPEED OF A COMPRESSOR BOOST STAGE IN A GAS TURBINE 有权
标题翻译：压缩机升压转速在气体涡轮机中的系统和方法
公开(公告)号：US20150285156A1
公开(公告)日：2015-10-08
申请号：US14744323
申请日：2015-06-19
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Ian A. MACFARLANE
IPC分类号： F02C7/36
CPC分类号： F02C7/36 , F05D2260/4023 , F05D2260/4031 , F05D2260/902 , F23R3/26
摘要： Systems and methods for changing a speed ratio between a compressor boost stage (12) and at least one power turbine (16) of a gas turbine engine (10) are described. Such a system may comprise a coupling device (20) configured to selectively transmit energy from the at least one power turbine (16) to the boost stage (12) according to at least a first speed ratio and a second speed ratio. The system may also comprise an auxiliary power device (22, 26) configured to cause a rotational speed of the boost stage (12) to change from a first speed corresponding substantially to the first speed ratio to a second speed corresponding substantially to the second speed ratio when the boost stage (12) is decoupled from the at least one power turbine (16).
摘要翻译：描述了用于改变压缩机升压级（12）和燃气涡轮发动机（10）的至少一个动力涡轮机（16）之间的速比的系统和方法。这样的系统可以包括被配置为根据至少第一速度比和第二速度比率将能量从至少一个动力涡轮机（16）有选择地传递到升压级（12）的联接装置（20）。该系统还可以包括辅助动力装置（22,26），其被配置为使升压级（12）的转速从基本上对应于第一速度比的第一速度变化到基本上对应于第二速度的第二速度增压级（12）与至少一个动力涡轮机（16）分离时的比例。

5. 发明授权

US08161727B2 System providing braking in a gas turbine engine in the event of the turbine shaft breaking 有权
标题翻译：在涡轮轴断裂的情况下，在燃气涡轮发动机中提供制动的系统
公开(公告)号：US08161727B2
公开(公告)日：2012-04-24
申请号：US12126648
申请日：2008-05-23
申请人： Jacques Rene Bart , Didier Rene Andre Escure , Claude Marcel Mons , Stephane Rousselin
发明人： Jacques Rene Bart , Didier Rene Andre Escure , Claude Marcel Mons , Stephane Rousselin
IPC分类号： F02K9/38 , F02G3/00 , F03D11/02
CPC分类号： F01D21/006 , F05D2230/90 , F05D2260/902 , F05D2300/21 , F05D2300/2102 , F05D2300/2118 , F05D2300/44 , F05D2300/601 , F05D2300/603 , F05D2300/611 , F05D2300/614
摘要： A device for, in a gas turbine engine, braking a turbine including a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking is disclosed. The device includes a first braking member provided with at least one abrasive element and a second braking member including a ring-shaped element (120A) made of a material capable of being eroded by the abrasive element. One of the two braking members being secured to the rotor and the other of the two braking members being secured to the stator. The braking members come into contact with one another through axial displacement of the rotor once the shaft has broken. The abrasive element of the first braking member eroding the ring-shaped element of the second braking member.
摘要翻译：公开了一种用于在燃气涡轮发动机中制动涡轮的装置，该涡轮机包括在所述轴断裂的情况下驱动能够相对于定子旋转的轴的转子。该装置包括设置有至少一个研磨元件的第一制动构件和包括由能够被研磨元件侵蚀的材料制成的环形元件（120A）的第二制动构件。两个制动构件中的一个固定到转子，并且两个制动构件中的另一个固定到定子。一旦轴已破裂，制动部件通过转子的轴向位移相互接触。第一制动构件的研磨元件侵蚀第二制动构件的环形元件。

6. 发明授权

US4141671A Tool gas turbine motor 失效
标题翻译：工具燃气轮机电机
公开(公告)号：US4141671A
公开(公告)日：1979-02-27
申请号：US789234
申请日：1977-04-20
申请人： Balazs K. Tarsoly
发明人： Balazs K. Tarsoly
IPC分类号： F01D1/34 , F01D9/02 , F01D15/06 , F01D5/00
CPC分类号： F01D9/02 , F01D1/34 , F01D15/06 , F05D2260/902 , Y10T408/65
摘要： In a preferred embodiment, a drill gas turbine motor in which the housing structure directs pressurized gas both radially inwardly and axially along the longitudinal axis of the elongated housing, against vanes arranged along a circumscribing surface of the revolvable (rotatable) rotor mounted within rotor space within the housing to effect rotation of the rotor, and a drivable shaft extending from an opening at one end of the housing, and a dampening-spring mechanism at an opposite end of the housing and rotor arranged to dampen pressure and movement of the rotor in a direction away from the end of the drivable shaft thereby reducing wear on bearings supporting the rotar at opposite ends thereof, together with brake mechanism for manually exerting braking pressure against the rotor, and key mechanism for locking the rotor in a non-revolvable state during change of chuck on the drivable shaft, and the drivable shaft having formed in a distal end thereof a female receptacle receivable of a male end of a chuck.
摘要翻译：在优选实施例中，一种钻井燃气涡轮马达，其中壳体结构沿着细长壳体的纵向轴线沿径向向内和轴向地引导加压气体，沿着安装在转子空间内的可旋转（可旋转）转子的外接表面布置的叶片在壳体内以实现转子的旋转，以及从壳体的一端处的开口延伸的可驱动轴，以及在外壳和转子的相对端处的阻尼弹簧机构，其布置成阻尼转子的压力和运动远离可驱动轴的端部的方向，从而减少在其相对端处支撑旋转体的轴承上的磨损，以及用于手动地向转子施加制动压力的制动机构以及用于将转子锁定在不可旋转状态的键机构在可驱动的轴上的卡盘的变化，以及在其远端形成有可插入的插座的可移动的轴 f是卡盘的公头。

7. 发明申请

US20180297567A1 METHOD AND SYSTEM FOR CONTROLLING THE BRAKING OF AN AIRCRAFT EQUIPPED WITH A THRUST-REVERSAL SYSTEM 审中-公开
公开(公告)号：US20180297567A1
公开(公告)日：2018-10-18
申请号：US16010868
申请日：2018-06-18
申请人： Safran Nacelles , Safran Landing Systems
发明人： Patrick GONIDEC , Hakim MAALIOUNE , François TAILLARD , Denis JONTEF , Marie-Laure DE-CRESCENZO , Jean-François HAMMANN
IPC分类号： B60T8/17 , B64C25/42 , F02K1/76 , B60T8/171 , B60T8/1761
CPC分类号： B60T8/1703 , B60T8/171 , B60T8/17616 , B64C25/42 , F02K1/76 , F05D2220/323 , F05D2260/90 , F05D2260/901 , F05D2260/902 , Y02T50/671
摘要： The present disclosure relates to a method of controlling the braking of an aircraft equipped with a landing gear bearing braked wheels, the aircraft being propelled by jet engines and equipped with a thrust reversal system, the method involving the steps of estimating the grip/adhesion of the braked wheels and activating the thrust-reversal system or modulating the reverse-thrust generated by the thrust-reversal system if this system is already activated, based on the estimated grip/adhesion.

8. 发明授权

US09593643B2 Device for driving actuators for a thrust reverser, selectively allowing motorised or manual driving 有权
标题翻译：用于驱动推力反向器的执行器的装置，选择性地允许电动或手动驱动
公开(公告)号：US09593643B2
公开(公告)日：2017-03-14
申请号：US14917224
申请日：2014-09-09
申请人： SAGEM DEFENSE SECURITE
发明人： Julien Tisseau
IPC分类号： F02K1/00 , F02K1/76 , F16H1/26
CPC分类号： F02K1/763 , F05D2230/72 , F05D2260/902 , F16H1/26
摘要： The invention relates to a device (3) for driving actuators (7-10) for a thrust reverser, comprising a motorized drive unit (15), a brake (16) and a manual drive unit (17) for rotatably driving a drive shaft, and a control part (44) which can be actuated by an operator, the control part (44) being mobile between a motorized drive position and a manual drive position, the movement of the control part (44) from the motorized drive position into the manual drive position causing the movement of a clutch part (40) into an engaged position in order to connect the manual drive unit (17) to the drive shaft (14), and the movement of the brake (16) into the loosened configuration in order to authorize the driving of the drive shaft (14) in rotation by the manual drive unit (17).
摘要翻译：本发明涉及一种用于驱动用于推力反向器的致动器（7-10）的装置（3），包括电动驱动单元（15），制动器（16）和手动驱动单元（17），用于可旋转地驱动驱动轴，以及可由操作者致动的控制部分（44），所述控制部分（44）在电动驱动位置和手动驱动位置之间移动，所述控制部分（44）从所述电动驱动位置移动到所述手动驱动位置导致离合器部分（40）移动到接合位置以将手动驱动单元（17）连接到驱动轴（14），并且制动器（16）移动到松动构造以便通过手动驱动单元（17）授权驱动轴（14）旋转驱动。

9. 发明授权

US09328667B2 Systems and methods for changing a speed of a compressor boost stage in a gas turbine 有权
公开(公告)号：US09328667B2
公开(公告)日：2016-05-03
申请号：US14744323
申请日：2015-06-19
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Ian A. MacFarlane
IPC分类号： F02C1/06 , F02C7/36 , F23R3/26
CPC分类号： F02C7/36 , F05D2260/4023 , F05D2260/4031 , F05D2260/902 , F23R3/26
摘要： Systems and methods for changing a speed ratio between a compressor boost stage (12) and at least one power turbine (16) of a gas turbine engine (10) are described. Such a system may comprise a coupling device (20) configured to selectively transmit energy from the at least one power turbine (16) to the boost stage (12) according to at least a first speed ratio and a second speed ratio. The system may also comprise an auxiliary power device (22, 26) configured to cause a rotational speed of the boost stage (12) to change from a first speed corresponding substantially to the first speed ratio to a second speed corresponding substantially to the second speed ratio when the boost stage (12) is decoupled from the at least one power turbine (16).

10. 发明授权

US09091216B2 Systems and methods for changing a speed of a compressor boost stage in a gas turbine 有权
标题翻译：用于改变燃气轮机中的压缩机增压级的速度的系统和方法
公开(公告)号：US09091216B2
公开(公告)日：2015-07-28
申请号：US13306095
申请日：2011-11-29
申请人： Ian A. Macfarlane
发明人： Ian A. Macfarlane
IPC分类号： F02C1/06 , F02C7/36
CPC分类号： F02C7/36 , F05D2260/4023 , F05D2260/4031 , F05D2260/902 , F23R3/26
摘要： Systems and methods for changing a speed ratio between a compressor boost stage (12) and at least one power turbine (16) of a gas turbine engine (10) are described. Such a system may comprise a coupling device (20) configured to selectively transmit energy from the at least one power turbine (16) to the boost stage (12) according to at least a first speed ratio and a second speed ratio. The system may also comprise an auxiliary power device (22, 26) configured to cause a rotational speed of the boost stage (12) to change from a first speed corresponding substantially to the first speed ratio to a second speed corresponding substantially to the second speed ratio when the boost stage (12) is decoupled from the at least one power turbine (16).
摘要翻译：描述了用于改变压缩机升压级（12）和燃气涡轮发动机（10）的至少一个动力涡轮机（16）之间的速比的系统和方法。这样的系统可以包括被配置为根据至少第一速度比和第二速度比率将能量从至少一个动力涡轮机（16）有选择地传递到升压级（12）的联接装置（20）。该系统还可以包括辅助动力装置（22,26），其被配置为使升压级（12）的转速从基本上对应于第一速度比的第一速度变化到基本上对应于第二速度的第二速度增压级（12）与至少一个动力涡轮机（16）分离时的比例。

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