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1. 发明申请

US20120104762A1 Large floating vertical axis wind turbine 有权
标题翻译：大浮动垂直轴风力发电机
公开(公告)号：US20120104762A1
公开(公告)日：2012-05-03
申请号：US12913023
申请日：2010-10-27
申请人： Jack W. Wilson, JR. , John E. Ryznic
发明人： Jack W. Wilson, JR. , John E. Ryznic
IPC分类号： F03D9/00 , B23P17/00 , B23P17/04
CPC分类号： F03D3/061 , F03D13/25 , F03D80/70 , F05B2240/93 , F05B2250/86 , Y02E10/727 , Y02E10/74 , Y10T29/49229 , Y10T29/49826
摘要： A large floating vertical axis wind turbine with a floating inner cylinder having rotor blades that rotate together as an assembly, and a floating outer cylinder with a central opening in which the floating inner cylinder rotates for support against tipping. Outriggers with floating devices on the ends extend out from the floating outer cylinder for additional stability. The floating inner cylinder is partially supported by a top bearing on the outer cylinder to carry some of the load from the rotor blades.
摘要翻译：具有浮动内筒的大浮动垂直轴风力涡轮机，其具有作为组件一起旋转的转子叶片，以及具有中心开口的浮动外筒，浮动内筒旋转以支撑以防止倾翻。具有浮动装置的外伸支架从浮动外筒延伸出来以获得额外的稳定性。浮动内筒由外筒上的顶部轴承部分支撑，以承载来自转子叶片的一些载荷。

2. 发明授权

US07922445B1 Variable inlet guide vane with actuator 失效
标题翻译：可变入口导向叶片带执行机构
公开(公告)号：US07922445B1
公开(公告)日：2011-04-12
申请号：US12558901
申请日：2009-09-14
申请人： William W Pankey , Jack W. Wilson, Jr.
发明人： William W Pankey , Jack W. Wilson, Jr.
IPC分类号： F01B25/02
CPC分类号： F01D17/162 , F01D17/20 , F05D2200/33
摘要： A variable inlet guide vane assembly for a gas turbine engine, where the guide vanes are pivotably connected to a sync ring that is contained within an annular groove within the casing so that leakage through holes in the casing is minimized. The guide vanes include a slider mechanism on one of the ends that will allow for both an axial and a rotational movement of the guide vane pin when the guide vanes pivot about a fixed pin on an opposite end of the guide vanes. a round rotary vane actuator with a height much less than a diameter is mounted outside of the casing and connects to the sync ring through a driving linkage.
摘要翻译：一种用于燃气涡轮发动机的可变入口引导叶片组件，其中导向叶片可枢转地连接到容纳在壳体内的环形槽内的同步环，使得通过壳体中的孔的泄漏最小化。导向叶片包括在其中一个端部上的滑动机构，当导叶绕导向叶片的相对端上的固定销枢转时，该滑块机构将允许导叶销的轴向和旋转运动。具有远小于直径的高度的圆形旋转叶片致动器安装在壳体的外部并通过驱动连杆连接到同步环。

3. 发明申请

US20100284794A1 Low pressure turbine rotor disk 有权
标题翻译：低压涡轮转子盘
公开(公告)号：US20100284794A1
公开(公告)日：2010-11-11
申请号：US11975674
申请日：2007-10-19
申请人： Ryan C. McMahon , Jack W. Wilson, JR.
发明人： Ryan C. McMahon , Jack W. Wilson, JR.
IPC分类号： F01D11/00 , F01D1/24 , F01D5/08 , F01D5/02 , B23P15/04
CPC分类号： F01D5/026 , F16C3/023 , F16C2360/23 , Y02T50/671 , Y10S29/013 , Y10T29/4932
摘要： A low pressure turbine rotor disk for a small twin spool gas turbine engine in which the rotor disk includes a forward side cavity large enough to allow for the bearing assembly that rotatably supports the rotor disk to fit within the cavity in order to shorten the axial distance between the bearings that support the inner rotor shaft on which the turbine rotor disk is secured. Minimizing the bearings spacing allows for a high critical speed for the inner rotor shaft and therefore allows for the small twin spool gas turbine engine to operate at this small scale. The turbine rotor disk also includes a plurality of axial aligned cooling air holes to allow for cooling air from the bearings to flow out from the aft end of the rotor disk. The inner surface of the cavity is an annular surface that forms a seal with knife edges extending outward from the bearing support plate also located within the cavity. The rotor disk includes an annular groove facing outward and on the rear side of the disk to allow for a tool to be inserted for removing the rotor disk from the shaft. An axial central opening in the rotor disk allows for insertion of the shaft and is formed with a bearing race abutment surface on the forward side and a nut abutment surface of the aft side used to compress the rotor disk assembly on the inner rotor shaft.
摘要翻译：一种用于小型双卷轴燃气涡轮发动机的低压涡轮转子盘，其中转子盘包括足够大的前侧腔，以允许可旋转地支撑转子盘以装配在腔内的轴承组件，以缩短轴向距离在支撑涡轮转子盘固定在其上的内转子轴之间。最小化轴承间距允许内转子轴的高临界转速，从而允许小双轴卷烟机涡轮发动机以小规模运行。涡轮转子盘还包括多个轴向排列的冷却空气孔，以允许冷却来自轴承的空气从转子盘的后端流出。空腔的内表面是形成密封件的环形表面，刀片边缘也从也位于腔体内的轴承支撑板向外延伸。转子盘包括面向盘的外侧和后侧的环形槽，以允许插入工具以将转子盘从轴上移除。转子盘中的轴向中心开口允许轴插入，并且在前侧形成有轴承座抵接表面，并且在后侧形成用于压缩内转子轴上的转子盘组件的螺母邻接表面。

4. 发明授权

US07750492B1 Bearingless floating wind turbine 有权
标题翻译：无轴承浮动风力发电机
公开(公告)号：US07750492B1
公开(公告)日：2010-07-06
申请号：US12613305
申请日：2009-11-05
申请人： John E Ryznic , Joseph D Brostmeyer , Jack W Wilson, Jr.
发明人： John E Ryznic , Joseph D Brostmeyer , Jack W Wilson, Jr.
IPC分类号： F03D3/04
CPC分类号： F03D3/005 , F03D13/25 , F05B2220/7066 , F05B2220/7068 , F05B2240/212 , F05B2240/301 , F05B2240/61 , F05B2240/93 , F05B2240/95 , F05B2260/85 , F05B2260/90 , Y02E10/727 , Y02E10/74
摘要： A bearingless floating wind turbine has a tall and narrow main support structure with a center of buoyancy located well above the center of gravity to provide stability to the wind turbine while supported for rotation in a body of water, a vertical axis turbine blade extends from the main support structure and rotates together under a wind, and a non-rotating shaft extends through the main support structure with a vertical axis direct drive generator connected between the main support structure and the non-rotating shaft to produce electricity when the main support structure rotates. an anchor line connected to the non-rotating shaft prevents the floating wind turbine from drifting in a body of water.
摘要翻译：无轴承浮动风力涡轮机具有高而窄的主支撑结构，其浮力中心位于重心之上，以便在风力涡轮机同时被支撑以在水体中旋转时提供稳定性，垂直轴涡轮机叶片从主支撑结构并在风中一起旋转，并且非旋转轴通过主支撑结构延伸，其中垂直轴直接驱动发电机连接在主支撑结构和非旋转轴之间，以在主支撑结构旋转时产生电力。连接到非旋转轴的锚定线防止浮动风力涡轮机在水体中漂移。

5. 发明授权

US07748952B1 Snorkel tube for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的浮潜管
公开(公告)号：US07748952B1
公开(公告)日：2010-07-06
申请号：US12184885
申请日：2008-08-01
申请人： Cheryl A. Schopf , Jack W. Wilson, Jr.
发明人： Cheryl A. Schopf , Jack W. Wilson, Jr.
IPC分类号： F01D25/12
CPC分类号： F01D5/026 , F16C3/023 , F16C2360/23 , Y02T50/671 , Y10S29/013 , Y10T29/4932
摘要： A small twin spool gas turbine engine with a bearing support arrangement in which the bearings are dampened by O-rings secured between the bearing races and the support structure, and in which the bearings are arranged in series so that a cooling air can be passed through the bearings to prevent overheating. The aft end of the engine includes high speed and low speed ball bearings supported with preload springs to add additional damping capability. The fore and aft end bearing support assemblies forms a cooling air path for the cooling fluid to flow through a passage within one of the guide vanes, through the bearings and out through a hole in the low pressure turbine rotor disk. the bearing cooling air passage includes a snorkel tube that extends from a guide vane cooling air passage and into the bypass air channel to draw in the cooling air used for the bearings. The snorkel tube includes a slanted opening so that dirt particulates do not enter the bearing cooling air passage.
摘要翻译：一种具有轴承支撑装置的小型双阀芯燃气涡轮发动机，其中轴承被固定在轴承座和支撑结构之间的O形环夯实，并且其中轴承串联布置，使得冷却空气可以通过轴承防止过热。发动机的后端包括用预加载弹簧支撑的高速和低速球轴承，以增加额外的阻尼能力。前端和后端轴承支撑组件形成冷却空气路径，用于冷却流体流过一个导叶内的通道，穿过轴承并通过低压涡轮转子盘中的孔流出。轴承冷却空气通道包括从引导叶片冷却空气通道延伸到旁通空气通道中以吸入用于轴承的冷却空气中的吸管。浮潜管包括倾斜开口，使得污垢颗粒不进入轴承冷却空气通道。

6. 发明授权

US07736131B1 Turbine blade with carbon nanotube shell 失效
标题翻译：带碳纳米管壳的涡轮叶片
公开(公告)号：US07736131B1
公开(公告)日：2010-06-15
申请号：US12244368
申请日：2008-10-02
申请人： Jack W Wilson, Jr.
发明人： Jack W Wilson, Jr.
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , B82Y30/00 , F01D5/28 , F01D5/282 , F05D2300/224
摘要： A turbine blade for use in a gas turbine engine, where the turbine blade is made from a spar and shell construction in which a thin walled shell is formed from carbon or molybdenum nanotubes arranged in a direction such that the nanotubes are under tension when the blade is rotating in the engine. The carbon nanotubes are allotropes of carbon in which the length to diameter ratio exceeds 1,000,000 in order to produce very high tensile strength, unique electrical properties, and a very efficient conductor of heat. The nanotube shell includes a metal insert having a tear drop shape and the lower end of the shell wraps around the metal insert to form a wedge in which the shell is held in place against radial displacement between the platform and the attachment portion of the blade.
摘要翻译：一种用于燃气涡轮发动机的涡轮机叶片，其中涡轮叶片由翼梁和壳体构造制成，其中薄壁壳由碳或钼纳米管形成，所述碳或钼纳米管沿着使得当叶片在发动机中旋转。碳纳米管是长度比直径比超过1,000,000的碳的同素异形体，以产生非常高的拉伸强度，独特的电性能和非常有效的热导体。纳米管壳包括具有泪滴形状的金属插入物，并且壳的下端围绕金属插入物缠绕以形成楔，其中壳保持在适当位置，以防止平台与叶片的附接部分之间的径向位移。

7. 发明授权

US07665293B2 Low speed rotor shaft for a small twin spool gas turbine engine 有权
标题翻译：低速转子轴用于小型双卷轴燃气轮机
公开(公告)号：US07665293B2
公开(公告)日：2010-02-23
申请号：US11975671
申请日：2007-10-19
申请人： Jack W. Wilson, Jr. , Robert E. deLaneuville , Paul E. Orndoff , Ryan C. McMahon
发明人： Jack W. Wilson, Jr. , Robert E. deLaneuville , Paul E. Orndoff , Ryan C. McMahon
IPC分类号： F02C7/00 , F02K3/04
CPC分类号： F01D5/026 , F16C3/023 , F16C2360/23 , Y02T50/671 , Y10S29/013 , Y10T29/4932
摘要： An inner rotor shaft for use in a small twin spool gas turbine engine, the inner rotor shaft having a hollow middle section formed of a smaller diameter hollow section on a compressor end and a larger diameter hollow section on the turbine end of the shaft. Solid shaft end extend from the hollow section to form a forward solid shaft end to secure the fan rotor disk and an aft solid shaft end to secure the turbine rotor disk. A parabolic shaped transition section joins the forward shaft end to the smaller diameter hollow section, and a conical shaped transition section joins the aft shaft end to the larger diameter hollow section. A conical shaped transition piece joins the two hollow sections together to form an inner rotor shaft that can fit within a minimal space between the compressor rotor disk and the annular combustor assembly of the engine. The conical shaped transition section on the turbine end is so shaped in order to fit within a space formed inside the high pressure turbine rotor disk of the engine in order to minimize the axial spacing between the bearings that support the inner rotor shaft and raise the critical speed of the shaft to a safe level above the operating speed of the engine in order to make such a small twin spool gas turbine engine possible.
摘要翻译：一种用于小型双轴卷烟气发动机的内转子轴，内转子轴具有由压缩机端部的较小直径的中空部分形成的空心中部，在轴的涡轮机端部具有较大直径的中空部分。实心轴端从中空部分延伸以形成一个向前的实心轴端，以固定风扇转子盘和一个实心轴端，以固定涡轮转子盘。抛物线形过渡部分将前轴端连接到较小直径的中空部分，并且锥形过渡部分将后轴端连接到较大直径的中空部分。锥形过渡件将两个中空部分连接在一起以形成内转子轴，其可以装配在压缩机转子盘和发动机的环形燃烧器组件之间的最小空间内。涡轮机端部上的锥形过渡部分被成形以便装配在形成在发动机的高压涡轮机转子盘内部的空间内，以便最小化支撑内转子轴的轴承之间的轴向间距并且提高关键轴的转速达到高于发动机运行速度的安全水平，以便使这种小型双阀芯燃气涡轮发动机成为可能。

8. 发明授权

US07633175B1 Resonating blade for electric power generation 失效
标题翻译：谐振叶片用于发电
公开(公告)号：US07633175B1
公开(公告)日：2009-12-15
申请号：US12119549
申请日：2008-05-13
申请人： Jack W Wilson, III , Jack W Wilson, Jr.
发明人： Jack W Wilson, III , Jack W Wilson, Jr.
IPC分类号： F03B13/12 , F03B13/10 , H02P9/04
CPC分类号： F01D9/041 , F05D2220/60 , F05D2240/12
摘要： A process and an apparatus for generating electric current from a vibrating blade exposed to a fluid flow, in one embodiment, a plurality of blades are secured within a tail cone of a steam turbine and each blade includes a magnet and a coil associated with the magnet to produce electric current in the coil when the magnet moves across the coil. Each blade is designed to have a natural frequency so that the blade will resonate under the influence of the exhaust flow from the turbine in the tail cone. Abutment members are mounted on the blade or the fixed support to limit the range of motion of the vibrating blade so that it does not exceed the fatigue limit. The blades are made from a low damping material such as titanium so that a low frequency is produced.
摘要翻译：一种用于从暴露于流体流动的振动叶片产生电流的方法和装置，在一个实施例中，多个叶片被固定在蒸汽轮机的尾锥体内，并且每个叶片包括磁体和与磁体相关联的线圈当磁体穿过线圈移动时，在线圈中产生电流。每个叶片被设计成具有固有频率，使得叶片在来自尾锥体中的涡轮机的排气流的影响下将共振。基台部件安装在叶片或固定支架上，以限制振动叶片的运动范围，使其不超过疲劳极限。叶片由诸如钛的低阻尼材料制成，从而产生低频率。

9. 发明申请

US20090031732A1 Low speed rotor shaft for a small twin spool gas turbine engine 有权
标题翻译：低速转子轴用于小型双卷轴燃气轮机
公开(公告)号：US20090031732A1
公开(公告)日：2009-02-05
申请号：US11975671
申请日：2007-10-19
申请人： Jack W. Wilson, JR. , Robert E. deLaneuville , Paul E. Orndoff , Ryan C. McMahon
发明人： Jack W. Wilson, JR. , Robert E. deLaneuville , Paul E. Orndoff , Ryan C. McMahon
IPC分类号： F02C3/10 , F16C3/02
CPC分类号： F01D5/026 , F16C3/023 , F16C2360/23 , Y02T50/671 , Y10S29/013 , Y10T29/4932
摘要： An inner rotor shaft for use in a small twin spool gas turbine engine, the inner rotor shaft having a hollow middle section formed of a smaller diameter hollow section on a compressor end and a larger diameter hollow section on the turbine end of the shaft. Solid shaft end extend from the hollow section to form a forward solid shaft end to secure the fan rotor disk and an aft solid shaft end to secure the turbine rotor disk. A parabolic shaped transition section joins the forward shaft end to the smaller diameter hollow section, and a conical shaped transition section joins the aft shaft end to the larger diameter hollow section. A conical shaped transition piece joins the two hollow sections together to form an inner rotor shaft that can fit within a minimal space between the compressor rotor disk and the annular combustor assembly of the engine. The conical shaped transition section on the turbine end is so shaped in order to fit within a space formed inside the high pressure turbine rotor disk of the engine in order to minimize the axial spacing between the bearings that support the inner rotor shaft and raise the critical speed of the shaft to a safe level above the operating speed of the engine in order to make such a small twin spool gas turbine engine possible.
摘要翻译：一种用于小型双轴卷烟气发动机的内转子轴，内转子轴具有由压缩机端部的较小直径的中空部分形成的空心中部，在轴的涡轮机端部具有较大直径的中空部分。实心轴端从中空部分延伸以形成一个向前的实心轴端，以固定风扇转子盘和一个实心轴端，以固定涡轮转子盘。抛物线形过渡部分将前轴端连接到较小直径的中空部分，并且锥形过渡部分将后轴端连接到较大直径的中空部分。锥形过渡件将两个中空部分连接在一起以形成内转子轴，其可以装配在压缩机转子盘和发动机的环形燃烧器组件之间的最小空间内。涡轮机端部上的锥形过渡部分被成形以便装配在形成在发动机的高压涡轮机转子盘内部的空间内，以便最小化支撑内转子轴的轴承之间的轴向间距并且提高关键轴的转速达到高于发动机运行速度的安全水平，以便使这种小型双阀芯燃气涡轮发动机成为可能。

10. 发明授权

US07210899B2 Passive clearance control 有权
标题翻译：被动清关控制
公开(公告)号：US07210899B2
公开(公告)日：2007-05-01
申请号：US11101705
申请日：2005-04-08
申请人： Jack W. Wilson, Jr.
发明人： Jack W. Wilson, Jr.
IPC分类号： F01D11/08
CPC分类号： F01D11/18 , F05D2300/502 , Y02T50/672
摘要： The clearance between the tips of the rotor blades and the segmented shroud of a gas turbine engine is controlled by a passive clearance control that includes a support ring made from a low thermal expansion material supporting a retainer for the blade outer air seal that is slidable relative thereto so that the segments expand circumferentially and move radially to match the rate of change slope of the rotor during expansion and contraction for all engine operations. A leaf spring between the support ring and outer air seal biases the outer air seal in the radial direction and maintains the desired radial position during steady state operation of the gas turbine engine.
摘要翻译：转子叶片的尖端与燃气涡轮发动机的分段护罩之间的间隙通过被动间隙控制来控制，该自由间隙控制包括由支撑用于叶片外部空气密封件的保持器的低热膨胀材料制成的支撑环，所述保持器可相对滑动使得所述段在周向上扩展并且径向移动以匹配用于所有发动机操作的膨胀和收缩期间转子的变化率的斜率。支撑环和外部空气密封件之间的板簧在径向方向上偏压外部空气密封并且在燃气涡轮发动机的稳态操作期间保持期望的径向位置。

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