公开(公告)号：US20160332744A1

公开(公告)日：2016-11-17

申请号：US14599433

申请日：2015-01-16

申请人： Hamilton Sundstrand Corporation

发明人： David Everett Russ ,  Kanthi Gnanam Kannan

IPC分类号： B64D41/00 ,  H02K7/18 ,  F01D15/10

CPC分类号： B64D41/007 ,  F05B2220/31 ,  F05B2220/50 ,  F05D2220/34 ,  H02K7/1823 ,  H02K7/183 ,  Y02E10/725

摘要： A ram air turbine (RAT) mounting system includes a frame with a forward end having a first side, a second side disposed opposite the first side, a third side, and a fourth side disposed opposite the third side. The frame also includes an aft end. A first mounting element is connected to the forward end of the frame proximate the first side and the third side. A second mounting element is connected to the forward end of the frame proximate the first side and the fourth side. A first rod is connected to the forward end of the frame proximate the second side and the third side. A second rod is connected to the aft end of the frame.

摘要翻译： 冲压式空气涡轮机（RAT）安装系统包括具有前端的框架，其具有第一侧，与第一侧相对设置的第二侧，第三侧和与第三侧相对设置的第四侧。 该框架还包括一个后端。 第一安装元件连接到靠近第一侧和第三侧的框架的前端。 第二安装元件连接到靠近第一侧和第四侧的框架的前端。 第一杆连接到靠近第二侧和第三侧的框架的前端。 第二杆连接到框架的后端。

公开(公告)号：US20160229527A1

公开(公告)日：2016-08-11

申请号：US14505300

申请日：2014-10-02

申请人： John Hincks Duke

发明人： John Hincks Duke

IPC分类号： B64C23/06 ,  F03D9/00 ,  F03D1/06 ,  B64D27/02

CPC分类号： B64C23/065 ,  B64D27/02 ,  F03D1/0675 ,  F05B2220/31 ,  Y02E10/721 ,  Y02E10/726 ,  Y02T50/164

摘要： A fuel efficient aircraft propulsion system comprises a wingtip mounted ducted pusher fan with convergent backwash and a skewed conical engine nacelle. The system both mitigates wingtip vortex drag and converts a portion of vortex energy into propulsion force and lift force. The forward-tapering nacelle skews both downward and inward, so the lower nacelle surface is flush with the lower wing surface and the inboard nacelle surface does not alter flow over the upper wing surface. This firstly preserves lift at the outboard wing end. Secondly, air displacement by the nacelle accelerates flow only on the outboard and upper nacelle surfaces, and because the nacelle occupies the core of the nascent wingtip vortex, rotational air velocity is greatest on the upper nacelle surface. The resultant pressure drop on the upper nacelle surface contributes to aircraft lift. And because the nacelle surface tapers forward, this pressure drop does not exert backward-acting drag on the aircraft. Aft of the nacelle, the pusher fan hub surface conforms with the aft nacelle surface and tapers aft. Propulsion foils project from the forward portion of the pusher fan hub at an outward-aft angle, which directs convergent high pressure backwash flow along the aft tapering hub surface. This isolates aft-facing hub surfaces from drag-inducing vortex core pressure drop. Downstream fan backwash convergence then forms a central volume of high pressure flow where the low pressure trailing vortex core would otherwise develop. This is an efficient means to dissipate the cyclonic structure of the vortex, because vortex persistence requires low pressure core persistence. The direction of pusher fan rotation opposes the direction of wingtip vortex rotation as described in the prior art. This cross-flow interaction increases the effective power of the fan and also further counters vortex formation. An integral peripheral duct links the outer ends of the fan propulsion foils to provide thrust efficiency similar to that of a high bypass fanjet engine, but without the internal air friction within a bypass channel. In an alternative horizontal axis wind turbine embodiment, the same nacelle form supports secondary power-takeoff turbines mounted in high energy density flow at the turbine blade tips.

公开(公告)号：US20150329214A1

公开(公告)日：2015-11-19

申请号：US14280588

申请日：2014-05-17

申请人： HAMILTON SUNDSTRAND CORPORATION

发明人： DAVID RUSS ,  STEPHEN BORTOLI ,  RICHARD SCHULTZ

IPC分类号： B64D41/00 ,  F01D15/12

CPC分类号： B64D41/007 ,  F01D15/12 ,  F03D9/32 ,  F03D15/10 ,  F03D80/70 ,  F05B2220/31 ,  F05B2240/50 ,  F05B2240/57 ,  F05B2240/923 ,  F05B2260/4031 ,  F05D2210/12 ,  F05D2220/10 ,  F05D2220/50 ,  F05D2240/50 ,  F05D2240/55 ,  Y02E10/72

摘要： A ram air turbine includes a turbine with one or more blades, a strut removably coupled to the turbine and having a gearbox section and a drive section, a cover located at an end of the gearbox section of the strut with a test plug having a static seal, a turbine shaft and a bevel gear located in the gearbox section of the strut and a driveshaft and a pinion gear located in the drive section of the strut, wherein the pinion gear engages with the bevel gear. The turbine shaft may include a dynamic seal that provides sealing between the turbine shaft and the cover. The test plug may be a threaded plug. The cover may also utilize a dynamic seal. The turbine shaft may include a splined internal cavity for use with a ground test motor.

摘要翻译： 压头空气涡轮机包括具有一个或多个叶片的涡轮机，支撑件可拆卸地联接到涡轮机并具有齿轮箱部分和驱动部分，盖子位于支柱的齿轮箱部分的端部，具有静态的测试塞 密封件，位于支柱的齿轮箱部分中的涡轮轴和锥齿轮以及位于支柱的驱动部分中的驱动轴和小齿轮，其中小齿轮与锥齿轮啮合。 涡轮轴可以包括在涡轮轴和盖之间提供密封的动态密封件。 测试插头可以是螺纹插头。 盖也可以利用动态密封。 涡轮轴可以包括与地面测试电机一起使用的花键内腔。

公开(公告)号：US08960051B2

公开(公告)日：2015-02-24

申请号：US13599048

申请日：2012-08-30

申请人： Conor Riordan ,  David G. Bannon

发明人： Conor Riordan ,  David G. Bannon

IPC分类号： F16C3/04

CPC分类号： B64D41/007 ,  F02C7/32 ,  F05B2220/31 ,  F05D2220/34 ,  F05D2230/53 ,  Y10T74/211 ,  Y10T74/2183

摘要： A combination hub, counterweight and crank arm for a governor assembly in a ram air turbine is has a hub section with a cylindrical orifice, an annular collar section that surround the hub section, a counterweight section that extends out of the annular collar section and a crank arm section that extends out of the annular collar section, with all the sections formed in a single piece steel body.

摘要翻译： 用于冲压空气涡轮机中的调速器组件的组合轮毂，配重和曲柄臂具有带有圆柱形孔口的毂部分，围绕轮毂部分的环形套环部分，延伸出环形套环段的配重部分和 曲柄臂部分从环形套环部分延伸出来，其中所有部分形成在单件钢体中。

公开(公告)号：US20120301290A1

公开(公告)日：2012-11-29

申请号：US13114603

申请日：2011-05-24

申请人： John F. Justak

发明人： John F. Justak

IPC分类号： F04D29/44

CPC分类号： B64D41/007 ,  F03D1/04 ,  F03D9/00 ,  F03D9/25 ,  F03D9/32 ,  F03D15/20 ,  F03D80/70 ,  F03D80/82 ,  F05B2220/31 ,  Y02E10/72

摘要： A ram air turbine comprises a turbine housing which mounts a number of circumferentially spaced turbine blades that function predominantly as impulse turbine blades and a number of splitters, each located in between adjacent turbine blades, which function predominantly as a reaction turbine blade but are shorter in length than the turbine blades. The cross section of the turbine housing decreases between its forward and aft ends while the height of both the turbine blades and splitters increases in the same direction such that the tips of the turbine blades and splitters collectively form a substantially cylindrical shape.

摘要翻译： 压头空气涡轮机包括涡轮机壳体，其安装多个周向间隔开的涡轮机叶片，其主要作用为脉冲涡轮机叶片和多个分离器，每个分配器位于相邻的涡轮机叶片之间，其主要用作反应涡轮机叶片，但是较短 长度比涡轮叶片。 涡轮机壳体的横截面在其前端和后端之间减小，同时涡轮机叶片和分离器的高度在相同方向上增加，使得涡轮机叶片和分离器的尖端共同形成大致圆柱形的形状。

公开(公告)号：US08066481B2

公开(公告)日：2011-11-29

申请号：US12426316

申请日：2009-04-20

申请人： David G. Bannon

发明人： David G. Bannon

IPC分类号： F01D7/00

CPC分类号： F01D5/027 ,  B64D41/007 ,  F03D7/0224 ,  F03D9/00 ,  F05B2220/31 ,  F05D2220/34 ,  Y02E10/723 ,  Y02T50/673

摘要： A method of balancing a ram air turbine that has a turbine shaft with a turbine shaft axis, a rotor attached to the shaft, rotor blades attached to the rotor that move between a fine pitch and coarse pitch position, a spring-loaded governor for controlling the position of the blades that has its springing retained by a stationary outer spring seat and a movable inner yoke plate that slides on the turbine shaft and whose position determines blade pitch, comprises the steps of: pulling the yoke plate toward the spring seat to displace the yoke plate toward the spring seat sufficiently to cause the rotor blades to assume a desired degree of pitch; spinning the turbine shaft at a desired rotational speed; balancing the rotor to minimize vibration of the rotor with the desired rotor blade pitch and turbine shaft speed; and releasing the pull of the yoke plate toward the spring seat.

摘要翻译： 一种用于平衡具有涡轮机轴与涡轮机轴轴线的转子空气涡轮机的方法，附接到轴的转子，附接到转子的转子叶片，该转子叶片在细间距和粗俯仰位置之间移动，用于控制的弹簧加载调速器 具有由固定外弹簧座保持弹簧的叶片的位置和在涡轮轴上滑动并且其位置确定叶片间距的可移动内轭板包括以下步骤：将轭板拉向弹簧座以移位 轭板朝向弹簧座充分地使转子叶片呈现期望的俯仰程度; 以期望的转速旋转涡轮机轴; 平衡转子以最小化所需转子叶片间距和涡轮轴转速的转子振动; 并释放轭板朝向弹簧座的拉动。

公开(公告)号：US07074010B2

公开(公告)日：2006-07-11

申请号：US10964475

申请日：2004-10-12

申请人： William T. DeGroff ,  Harry R. Carter, Jr.

发明人： William T. DeGroff ,  Harry R. Carter, Jr.

IPC分类号： B64C11/32 ,  F03D7/04

CPC分类号： F03D9/25 ,  B64D41/007 ,  F03D1/06 ,  F03D9/32 ,  F03D80/70 ,  F05B2220/31 ,  F05B2240/50 ,  Y02E10/721

摘要： An improved ram air turbine for generating emergency aeronautical supplemental power with a plurality of concentric or nested linear bearings for supporting a speed governor yoke plate on a speed governor shaft comprising a movable sleeve that supports the yoke plate and rides on the governor shaft.

摘要翻译： 一种改进的冲压式空气涡轮机，用于产生具有多个同心或嵌套直线轴承的紧急航空辅助动力，用于在调速器轴上支撑调速器轭板，该调速器轴包括支撑轭板并骑在调速器轴上的可移动套筒。

公开(公告)号：US20030011198A1

公开(公告)日：2003-01-16

申请号：US09878066

申请日：2001-06-07

申请人： Honeywell International, Inc.

发明人： Steven R. Eccles ,  Wayne G. Schindler

IPC分类号： F03D009/00

CPC分类号： B64D41/007 ,  F03D9/00 ,  F03D9/25 ,  F03D80/60 ,  F05B2220/31 ,  F05B2220/50 ,  Y02E10/725 ,  Y02P80/158

摘要： A ram air turbine system provides liquid cooling of its generator by employing a closed loop liquid cooling line originating from a pump in the gearbox of the system. In the preferred embodiment the pump may be a pitot pump to which gearbox lubricating oil may be channeled along a trough that is located in the gearbox. At least a portion of the trough is immersed in the oil which travels along the trough toward the pump in response to turbine shaft rotation. The oil is directed into a cooling jacket which is integral to the generator and then to a heat exchanger exposed to airflow. The oil is then returned to the gearbox.

摘要翻译： 冲压式空气涡轮机系统通过采用源自系统的齿轮箱中的泵的闭环液体冷却管线来提供其发电机的液体冷却。 在优选实施例中，泵可以是皮托泵，齿轮箱润滑油可以沿着位于齿轮箱中的槽引导到皮托泵。 槽的至少一部分被浸入沿着槽沿着槽移动以响应于涡轮机轴旋转而向泵行进的油中。 油被引导到与发生器成一体的冷却套，然后被引导到暴露于气流的热交换器。 然后将油返回到变速箱。

公开(公告)号：US5505587A

公开(公告)日：1996-04-09

申请号：US369065

申请日：1995-01-05

申请人： Richard Ghetzler

发明人： Richard Ghetzler

IPC分类号： F01D15/10 ,  F01D17/10 ,  F03D7/00 ,  F03D9/00 ,  F01D17/00

CPC分类号： B64D41/007 ,  F01D15/10 ,  F01D17/105 ,  F03D7/00 ,  F03D9/00 ,  F05B2220/31 ,  F05D2220/34 ,  Y02E10/723

摘要： A ram air turbine generator comprises a cylindrical external fairing having bypass exhaust orifices adjacent the leading end and external exhaust ports adjacent the aft end. A central flow guide is coaxially mounted and has a contoured outer surface spaced from the external fairing. A valve tube is coaxial with, and intermediate, the external fairing and the central flow guide and extends between a nose end with openings nearest the leading end of the external fairing and an aft plate. The valve tube also has a plurality of aft internal exhaust ports generally coextensive with the aft external exhaust ports in the external fairing. The valve tube is spring biased to a first position at which its nose end is proximate the leading end of the fairing and blocks the bypass exhaust orifices such that air is caused to flow through an annular nozzle defined between the valve tube and the central flow guide, through a turbine wheel, then out to the surrounding region through the aft internal and external exhaust ports. Ram air is effective to move the valve tube to a second position so as to expose the bypass exhaust orifices enabling substantial flow of bleed air therethrough. Additionally, a nozzle flow control mechanism is operable in response to movement of the valve tube between the first and second positions.

摘要翻译： 冲压空气涡轮发电机包括具有邻近前端的旁通排气孔和邻近尾端的外部排气口的圆柱形外部整流罩。 中央流动引导件同轴安装并且具有与外部整流罩间隔开的轮廓外表面。 阀管与外部整流罩和中央流动引导件同轴并且在中间，并在最靠近外部整流罩前端的开口的鼻端与后板之间延伸。 阀管还具有与外部整流罩中的尾部外部排气口大致共同延伸的多个后部内部排气口。 阀管被弹簧偏置到第一位置，在该第一位置，其鼻端靠近整流罩的前端并阻塞旁路排气孔，使得空气流过限定在阀管和中心流动引导件之间的环形喷嘴 ，通过涡轮机叶轮，然后通过后部的内部和外部排气口输出到周围区域。 拉姆空气有效地将阀管移动到第二位置，以便露出旁路排气孔，使排出空气能够流过其中。 另外，喷嘴流量控制机构响应于阀管在第一和第二位置之间的移动而可操作。

公开(公告)号：US4991796A

公开(公告)日：1991-02-12

申请号：US271439

申请日：1988-11-14

申请人： Walter C. Peters ,  William E. Seidel

发明人： Walter C. Peters ,  William E. Seidel

IPC分类号： F03D9/00 ,  F03D11/02

CPC分类号： B64D41/007 ,  F03D15/00 ,  F03D9/00 ,  F05B2220/31 ,  Y02E10/72 ,  Y02T50/44

摘要： A drive system is provided between a ram air turbine (10) and at least a pair of accessory power units (38,40) of an aircraft, the ram air turbine being movable between stowed and deployed positions relative to the fuselage of the aircraft. The problems of providing a compact lightweight design which eliminates extraneous components in the airstream and a system which operates at optimum speeds are solved by the use of a drive shaft (28) extending between the ram air turbine and a first accessory power unit (38), such as a hydraulic pump, within the aircraft fuselage. First gears (30, 34) rotatably couple an outer end of the main drive shaft to the ram air turbine. Second gears (36,48) rotatably couple an inner end of the main drive shaft to the first accessory power unit. Third gears, in the form of a gear train (54), rotatably couple the first accessory power unit to a second accessory power unit (40), such as an electrical generator, within the aircraft fuselage. The pair of accessory power units have generally parallel drive shafts (44,52) rotatably coupled by the gear train.

摘要翻译： 驱动系统设置在冲压空气涡轮机（10）和飞行器的至少一对辅助动力单元（38,40）之间，该冲压空气涡轮机可在相对于飞行器的机身的收起位置和展开位置之间移动。 提供消除气流中的无关组件的紧凑轻型设计的问题和以最佳速度运行的系统通过使用在冲压空气涡轮机和第一辅助动力单元（38）之间延伸的驱动轴（28）来解决， ，如液压泵，在飞机机身内。 第一齿轮（30,34）将主驱动轴的外端可旋转地联接到冲压空气涡轮机。 第二齿轮（36,48）将主驱动轴的内端可旋转地联接到第一辅助动力单元。 齿轮系（54）形式的第三齿轮将飞行器机身内的第一辅助动力单元可转动地连接到诸如发电机的第二辅助动力单元（40）。 一对附件动力单元具有大致平行的驱动轴（44,52），其可旋转地由齿轮系联接。