公开(公告)号：US10086934B2

公开(公告)日：2018-10-02

申请号：US15362424

申请日：2016-11-28

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Maresh ,  Frank Bradley Stamps ,  Patrick Ryan Tisdale ,  Robert Patrick Wardlaw ,  Andrew Haldeman ,  Drew Alan Sutton

IPC: B64C27/33 ,  B64C27/48 ,  B64C11/02 ,  B64C11/12 ,  B64C27/35

Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.

公开(公告)号：US10059064B2

公开(公告)日：2018-08-28

申请号：US15625598

申请日：2017-06-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Wardlaw ,  Werner Idler ,  John R. McCullough ,  Patrick Ryan Tisdale ,  Frank Bradley Stamps ,  James L. Braswell, Jr. ,  Ronald J. Measom ,  Paul K. Oldroyd

IPC: B29C70/30 ,  B29C70/20 ,  B32B37/02 ,  B32B37/16 ,  B32B37/18 ,  B32B5/12 ,  B32B5/26 ,  B64C11/02 ,  B64C11/04 ,  B64C11/12 ,  B64C27/33 ,  B64C27/48 ,  B29C70/38 ,  F01D5/02 ,  B32B38/18 ,  B32B5/22 ,  B64C27/32 ,  B29L31/08

CPC classification number: B29C70/30 ,  B29C70/202 ,  B29C70/38 ,  B29C70/382 ,  B29L2031/08 ,  B29L2031/082 ,  B32B5/12 ,  B32B5/22 ,  B32B5/26 ,  B32B37/02 ,  B32B37/16 ,  B32B37/18 ,  B32B38/1808 ,  B32B2603/00 ,  B64C11/02 ,  B64C11/04 ,  B64C11/12 ,  B64C27/32 ,  B64C27/33 ,  B64C27/48 ,  F01D5/02 ,  H05K999/99 ,  Y10T29/49316 ,  Y10T156/1062

Abstract: An apparatus comprising a soft in plane rotor yoke comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material having a plurality of first fibers oriented in a first direction, and a plurality of second layers formed of a second composite fabric material having a plurality of second fibers oriented in a second direction. Included is an apparatus comprising a soft in plane rotor comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material, and a plurality of second layers formed of a second composite fabric material, wherein the soft in plane rotor yoke does not comprise any narrow steered slit tape or filament windings.

公开(公告)号：US08012299B2

公开(公告)日：2011-09-06

申请号：US12920779

申请日：2009-03-05

Applicant: Mark Hancock

Inventor： Mark Hancock

IPC: B29C65/00 ,  B32B37/00 ,  B63H1/06 ,  B63H5/125 ,  B63H1/26 ,  B63H7/02 ,  B64C11/12 ,  B64C11/28 ,  B64C27/50 ,  B64C11/16 ,  B64C27/46 ,  F01D5/00 ,  F01D5/14 ,  F03B3/12 ,  F03B7/00 ,  F03D11/02

CPC classification number: F03D1/0675 ,  B29C65/18 ,  B29C65/30 ,  B29C65/483 ,  B29C65/4835 ,  B29C65/7841 ,  B29C66/54 ,  B29C66/721 ,  B29C66/80 ,  B29C66/8244 ,  B29K2105/203 ,  B29L2031/082 ,  F03D1/0641 ,  F03D13/10 ,  F05B2230/50 ,  F05B2230/61 ,  F05B2240/301 ,  Y02E10/721 ,  Y02P70/523 ,  Y10T29/49336 ,  Y10T156/10

Abstract: The invention provides a method of manufacturing a wind turbine blade comprising a spar and at least one airfoil section, where both the spar and the airfoil section comprise an outer surface which forms part of an aerodynamically active surface of the blade. The method comprises steps of providing a support structure, placing the spar at the support structure, providing a clamp adapted to be fixed to the outer surface of both the spar and the airfoil section, arranging the airfoil section relative to the spar, fixing the clamp to the outer surface of the spar and the airfoil section, and assembling the at least one airfoil section an the spar by a process including adhesion.

Abstract translation: 本发明提供了一种制造风力涡轮机叶片的方法，该风力涡轮机叶片包括翼梁和至少一个翼型段，其中翼梁和翼型段都包括形成叶片的空气动力学活动表面的一部分的外表面。 该方法包括以下步骤：提供支撑结构，将翼梁放置在支撑结构处，提供适于固定到翼梁和翼型部分的外表面的夹具，将翼型部相对于翼梁布置，固定夹具 到翼梁和翼型部分的外表面，并且通过包括粘合的工艺将至少一个翼型部分组装成翼梁。

公开(公告)号：US07494320B2

公开(公告)日：2009-02-24

申请号：US11167211

申请日：2005-06-28

Applicant: Petter Muren

Inventor： Petter Muren

IPC: B64C11/12 ,  B64C11/28 ,  B64C27/50

CPC classification number: B64C27/32 ,  A63H27/12 ,  B64C27/50

Abstract: A rotor (10) that enables an aircraft to become passively stable in hover. The inner part of the rotor blades (11) have a pitch angle fixed relative to a reference plane perpendicular to the rotor shaft (18) axis, and the tip of the rotor blades being connected to a ring (12) encircling the rotor. Each blade is connected to the rotor shaft by a separate hinge having a hinge axis perpendicular to both the rotor shaft axis and to the blade. Because the rotor blades can also easily twist the rotor can tilt freely in any direction. The rotor blades may be disconnected from the ring and folded up for easy transport.

Abstract translation: 一种使飞机能够在悬停中变得被动稳定的转子（10）。 转子叶片（11）的内部具有相对于垂直于转子轴（18）轴线的参考平面固定的俯仰角，并且转子叶片的尖端连接到环绕转子的环（12）。 每个叶片通过具有垂直于转子轴轴线和叶片的铰链轴的单独的铰链连接到转子轴。 因为转子叶片也可以容易地扭转，转子可以任意方向自由倾斜。 转子叶片可以与环分离，并折叠起来以便于运输。

公开(公告)号：US5240377A

公开(公告)日：1993-08-31

申请号：US841667

申请日：1992-02-25

Applicant: Jeffrey D. Farr

Inventor： Jeffrey D. Farr

IPC: B29C70/08 ,  B29C70/34 ,  B29C70/86 ,  B64C11/12 ,  F01D5/28 ,  F01D5/30

CPC classification number: F01D5/282 ,  B29C70/083 ,  B29C70/347 ,  B29C70/86 ,  B64C11/12 ,  F01D5/3053 ,  B29L2031/08 ,  Y02T50/66 ,  Y02T50/672 ,  Y02T50/673

Abstract: A composite fan blade comprises a blade portion (12) formed from a first set of unidirectional layers of fibers (110) wrapped around a wedge shape bushing (16). A blade platform (14) comprising a second set of unidirectional fiber layers (114) filled with a resin filler (116) is pressure molded with the blade (12) and bushing (16) to form a desired blade shape. The blade is then hinge mounted to a metallic blade support disk (18). The blade of the present invention provides a strong, lightweight fan blade for small, high speed propfan turbine engines.

Abstract translation: 复合风扇叶片包括由围绕楔形衬套（16）缠绕的第一组单向纤维层（110）形成的叶片部分（12）。 包括填充有树脂填料（116）的第二组单向纤维层（114）的叶片平台（14）用叶片（12）和衬套（16）进行加压模制以形成所需的叶片形状。 然后将刀片铰链安装到金属刀片支撑盘（18）上。 本发明的叶片为小型高速螺旋桨发动机提供了一种坚固，轻便的风扇叶片。

公开(公告)号：US09771801B2

公开(公告)日：2017-09-26

申请号：US13261565

申请日：2011-07-01

Applicant: Joerg Schumacher ,  Mario Scheckel

Inventor： Joerg Schumacher ,  Mario Scheckel

IPC: B63H1/06 ,  B64C11/12 ,  B64C11/28 ,  B64C27/50 ,  F01D5/12 ,  B63H1/26 ,  F01D5/02 ,  A61M1/10 ,  A61M1/12

CPC classification number: F01D5/02 ,  A61M1/101 ,  A61M1/1024 ,  A61M1/1034 ,  A61M1/12 ,  A61M1/122 ,  A61M1/125

Abstract: The invention relates to a rotor for a pump, having at least one blade, the rotor being able to be actuated to rotate about an axis of rotation in order to convey a fluid in the axial or radial direction, the rotor being able to be deformed reversibly elastically in the radial direction between a first, radially compressed state and a second, radially expanded state which the rotor adopts without the effect of external forces, and a third state of the rotor being provided in which, in pumping operation under fluid loading, the rotor is deformed from the first state to beyond the second state.

公开(公告)号：US09073625B1

公开(公告)日：2015-07-07

申请号：US13024732

申请日：2011-02-10

Applicant: Theodore W. Ingram, III ,  James L. Braswell, Jr. ,  Dharam J. Reddy

Inventor： Theodore W. Ingram, III ,  James L. Braswell, Jr. ,  Dharam J. Reddy

IPC: B64C11/12 ,  B64C27/33

CPC classification number: B64C11/12 ,  B64C27/33

Abstract: A helicopter rotor yoke includes a composite laminate having a plurality of plies of fibers disposed in a polymeric matrix. The polymeric matrix includes a toughened polymer at one of a location or zone that experiences high strain levels during use of the rotor yoke.

Abstract translation: 直升机转子轭包括具有设置在聚合物基质中的多层纤维的复合层压体。 聚合物基质包括在使用转子轭时经历高应变水平的位置或区域之一处的增韧聚合物。

公开(公告)号：US20120201678A1

公开(公告)日：2012-08-09

申请号：US13368795

申请日：2012-02-08

Applicant: David H. Hunter ,  Ryan Thomas Casey ,  Francis Edward Byrnes

Inventor： David H. Hunter ,  Ryan Thomas Casey ,  Francis Edward Byrnes

IPC: B64C11/12

CPC classification number: B64C27/33

Abstract: A rotor hub assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectible to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams.

Abstract translation: 用于直升机的转子轮毂组件包括可操作地连接到直升机的轴的转子轮毂。 一个或多个弯曲梁延伸穿过转子毂，每个柔性梁的每个端部可操作地连接到转子叶片。 一个或多个内部轴承位于转子毂处，以在转子毂中球形地支撑一个或多个弯曲梁。 用于直升机的转子组件包括可操作地连接到直升机的轴的转子毂。 延伸穿过转子轮毂和一个或多个内部轴承的一个或多个弯曲梁位于转子毂处，以在转子毂中球形地支撑一个或多个弯曲梁。 多个转子叶片可操作地连接到一个或多个柔性梁的端部。

公开(公告)号：US20110236209A1

公开(公告)日：2011-09-29

申请号：US13071366

申请日：2011-03-24

Applicant: Charles Louis ,  Matthieu Ferrant

Inventor： Charles Louis ,  Matthieu Ferrant

IPC: B64C11/12

CPC classification number: B64C27/51 ,  F16F1/3807

Abstract: The present invention relates to a damper (10) provided with an inner end strength member (20) and an outer end strength member (30) that are tubular and coaxial, a return member (40) being arranged between the inner end strength member (20) and the outer end strength member (30). The return member (40) includes an intermediate strength member (43) coaxial with the inner and outer end strength members (20, 30), said return member (40) having first and second return means (41, 42), said first return means (41) being arranged between the outer end strength member (30) and said intermediate strength member (43), said second return means (42) being arranged between the inner end strength member (20) and said intermediate strength member (43).

Abstract translation: 本发明涉及一种具有管状和同轴的内端强度件（20）和外端强度件（30）的阻尼器（10），一回转件（40） 20）和外端强度构件（30）。 返回构件（40）包括与内端和外端强度构件（20,30）同轴的中间强度构件（43），所述返回构件（40）具有第一和第二返回装置（41,42），所述第一返回 在外端强度构件（30）和中间强力构件（43）之间布置的装置（41），所述第二返回装置（42）设置在内端强度构件（20）和中间强力构件（43）之间， 。

公开(公告)号：US20100278648A1

公开(公告)日：2010-11-04

申请号：US12726564

申请日：2010-03-18

Applicant: Gerald KUNTZE-FECHNER ,  Martin SCHULZ

Inventor： Gerald KUNTZE-FECHNER ,  Martin SCHULZ

IPC: B64C11/12 ,  B23P17/00

CPC classification number: B64C27/33 ,  B29C70/545 ,  B29C2793/0045 ,  B29D99/0025 ,  B29L2031/06 ,  B29L2031/082 ,  B64C2027/4736 ,  Y10T29/49801

Abstract: A tension-torque-transmission element (3; 3′; 4) for a rotor blade of a rotary wing aircraft (helicopter), in particular for a fenestron blade of a tail rotor, with a connecting section on the blade side and a connecting section (30; 30′; 40) on the axis side, with a connecting eye (32) on each connecting section, and with a torque-transmission section (34; 34′; 44) that connects the connecting sections (30; 30′; 40), is improved in that the tension-torque-transmission element (3; 3′; 4) is designed in a fibre-reinforced composite design including several layers (A to G) of a textile fabric. A method for producing such a tension-torque-transmission element (3; 3′; 4) is also described.

Abstract translation: 一种用于旋转飞行器（直升机）的转子叶片的拉力扭矩传递元件（3; 3'; 4），特别是用于尾部转子的前叶片，在叶片侧具有连接部分， （30; 30'; 40），在每个连接部分上具有连接眼（32），以及扭矩传递部分（34; 34'; 44），其连接连接部分 改进了张力扭矩传递元件（3; 3'; 4）被设计成包括织物的几层（A至G）的纤维增强复合材料设计。 还描述了制造这种张力扭矩传递元件（3; 3'; 4）的方法。