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1. 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。

2. 发明授权

US07980812B2 Low pressure turbine rotor disk 有权
标题翻译：低压汽轮机转子盘
公开(公告)号：US07980812B2
公开(公告)日：2011-07-19
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： F03B11/06 , F04D29/10
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：一种用于小双轴卷烟气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，以允许可转动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，以允许插入工具以从转轴中移除转子盘。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。

3. 发明授权

US08235655B1 Variable inlet guide vane assembly 有权
标题翻译：可变入口导叶组件
公开(公告)号：US08235655B1
公开(公告)日：2012-08-07
申请号：US13072687
申请日：2011-03-26
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片式致动器安装在壳体的外部并且通过驱动连杆连接到同步环。

4. 发明授权

US07670116B1 Turbine vane with spar and shell construction 有权
标题翻译：涡轮叶片与翼梁和壳结构
公开(公告)号：US07670116B1
公开(公告)日：2010-03-02
申请号：US11243308
申请日：2005-10-04
申请人： Jack W. Wilson, Jr. , Wesley D Brown
发明人： Jack W. Wilson, Jr. , Wesley D Brown
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/189 , F01D5/20 , Y10T29/49327 , Y10T29/49339 , Y10T29/49341
摘要： The present invention is a vane for us in a gas turbine engine, in which the vane is made of an exotic, high temperature material that is difficult to machine or cast. The vane includes a shell made from either Molybdenum, Niobium, alloys of Molybdenum or Niobium (Columbium), Oxide Ceramic Matrix Composite (CMC), or SiC—SiC ceramic matrix composite, and is formed from a wire electric discharge process. The shell is positioned in grooves between the outer and inner shrouds, and includes a central passageway within the spar, and forms a cooling fluid passageway between the spar and the shell. Both the spar and the shell include cooling holes to carry cooling fluid from the central passageway to an outer surface of the vane for cooling. This cooling path eliminates a serpentine pathway, and therefore requires less pressure and less amounts of cooling fluid to cool the vane.
摘要翻译：本发明是一种用于燃气涡轮发动机的叶片，其中叶片由难以加工或铸造的外来高温材料制成。叶片包括由钼，铌，钼或铌（铌），氧化物陶瓷基复合材料（CMC）或SiC-SiC陶瓷基体复合材料制成的壳体，并由导线放电工艺形成。壳体定位在外护罩之间的凹槽中，并且在翼梁内部包括中心通道，并且在翼梁和壳体之间形成冷却流体通道。翼梁和壳都包括冷却孔，以将冷却流体从中心通道运送到叶片的外表面用于冷却。该冷却路径消除了蛇形通道，因此需要较少的压力和较少量的冷却流体来冷却叶片。

5. 发明授权

US07967565B1 Low cooling flow turbine blade 有权
标题翻译：低冷却流量涡轮叶片
公开(公告)号：US07967565B1
公开(公告)日：2011-06-28
申请号：US12408023
申请日：2009-03-20
申请人： Keith D Kimmel , Jack W. Wilson, Jr.
发明人： Keith D Kimmel , Jack W. Wilson, Jr.
IPC分类号： F01D5/14 , F01D5/18 , F01D5/28
CPC分类号： F01D5/187 , F01D5/147 , F01D5/28 , F05D2250/232 , F05D2300/131 , F05D2300/502
摘要： A turbine rotor blade made from a spar and a shell each having an airfoil cross sectional shape and each formed from a high temperature exotic material and formed by a wire EDM process to form a thin wall shell from Molybdenum and the spar from Waspalloy or IN100 in order to form a turbine blade that requires very low amounts of cooling air while allowing for high temperature use above what nickel super alloys can be exposed to. The spar and shell are secured to the platform by a bolt passing through the widest section of the hollow spar and connected at one end to a tip cap and to the other end to the platform and root piece of the blade.
摘要翻译：一种由翼梁和壳体制成的涡轮转子叶片，每个叶片和壳体均具有翼型截面形状，并且各自由高温外来材料形成，并通过线材EDM工艺形成，以从钼和来自Waspalloy或IN100的翼梁形成薄壁壳以形成涡轮叶片，其需要非常少量的冷却空气，同时允许高于镍超级合金可暴露于高温下的使用。翼梁和壳体通过穿过中空翼梁的最宽部分的螺栓固定到平台上，并且一端连接到顶盖，另一端连接到叶片的平台和根部部分。

6. 发明授权

US07677048B1 Turbine last stage blade with forced vortex driven cooling air 有权
标题翻译：涡轮机末级叶片带有强制涡流驱动冷却空气
公开(公告)号：US07677048B1
公开(公告)日：2010-03-16
申请号：US11439640
申请日：2006-05-24
申请人： Joseph Brostmeyer , Jack W. Wilson, Jr.
发明人： Joseph Brostmeyer , Jack W. Wilson, Jr.
IPC分类号： F02C7/12
CPC分类号： F01D5/081 , F05D2220/3215 , F05D2240/127 , F05D2260/2212
摘要： A gas turbine engine with a turbine section having at least a first stage turbine blade and a last stage turbine blade. The first stage turbine blade includes cooling fluid passages therein in which a compressed cooling fluid, usually from the compressor section of the gas turbine engine, is passed through for cooling of the first stage blade. The last stage turbine blade includes cooling fluid passages therein, but draws the cooling air from an outside ambient pressure source instead of from a compressor. The rotation of the last stage turbine blade and rotor disk provides for a centrifugal force to drive the cooling air into the blade and through the blade for cooling thereof. No additional compression of the last stage cooling fluid is required. A cover plate with a plurality of impellers covers a back side of the last stage rotor disk and provides for an additional means to pump the ambient cooling fluid into the last stage blade.
摘要翻译：具有涡轮部分的燃气涡轮发动机具有至少第一级涡轮叶片和最后级涡轮叶片。第一级涡轮机叶片包括其中的冷却流体通道，其中通常来自燃气涡轮发动机的压缩机部分的压缩冷却流体通过以冷却第一级叶片。最后一级的涡轮机叶片包括其中的冷却流体通道，但是从外部环境压力源而不是压缩机抽取冷却空气。最后一级涡轮机叶片和转子盘的旋转提供离心力，以驱动冷却空气进入叶片并通过叶片进行冷却。不需要对最后一级冷却液进行额外的压缩。具有多个叶轮的盖板覆盖最后一级转子盘的后侧，并提供用于将环境冷却流体泵入最后一级叶片的附加装置。

7. 发明授权

US07658588B1 Optimized blade tip clearance process for a rub tolerant design 有权
标题翻译：优化刀片间隙过程，实现耐磨设计
公开(公告)号：US07658588B1
公开(公告)日：2010-02-09
申请号：US11698382
申请日：2007-01-26
申请人： Cheryl A. Schopf , Jack W. Wilson, Jr.
发明人： Cheryl A. Schopf , Jack W. Wilson, Jr.
IPC分类号： F01D11/08
CPC分类号： F01D21/003 , F01D11/08 , F01D11/14 , F05D2230/50 , F05D2240/11 , F05D2260/80
摘要： A process for optimizing a blade tip clearance for a rub tolerate design in a gas turbine engine that includes evaluating a selection of candidate materials for galling and heat generation, selecting a subset of the candidate materials and analyze engine transient tip clearance for the subset materials, verifying the optimum material cooling and heat shielding for tip clearance and structures, and analyze and select an engine break-in procedure for the optimum tip clearance between turbine and compressor. If one of the subset materials results in a poor performance, than another material from the candidate materials is selected and reanalyzed until the best materials have been found. When the best materials are found, then a finite element method of analysis is performed from the blade and the static parts that form the tip clearance is performed to evaluate the materials for damage. If required, the blade and tip squealer configuration is altered to reduce stress, or blade tip coating is used. If a micro-crack in the static part will propagate, then the configuration of the hooks, scallops and the part thickness is reconfigured to reduce stress. Then, a #D analysis is performed for out-of-roundness, centerline bending and rotor sag. The design configuration and manufacturing is reiterated in order to optimize out-of-roundness.
摘要翻译：一种用于优化用于燃气涡轮发动机中的耐磨设计的叶片顶端间隙的方法，其包括评估用于磨损和产生热量的候选材料的选择，选择所述候选材料的子集并分析所述子集材料的发动机瞬态尖端间隙，验证顶端间隙和结构的最佳材料冷却和热屏蔽，并分析和选择用于涡轮机和压缩机之间的最佳顶端间隙的发动机启动程序。如果子集中的一个材料导致性能不佳，则选择和重新分析来自候选材料的另一种材料，直到找到最佳材料。当找到最好的材料时，从叶片进行有限元分析方法，并执行形成顶端间隙的静态部件，以评估材料的损坏。如果需要，刀片和尖端尖叫机配置被改变以减少应力，或者使用刀尖涂层。如果静态部分的微裂纹会传播，则重新配置钩，扇贝和部件厚度的配置以减轻应力。然后，对于不圆度，中心线弯曲和转子下垂进行#D分析。重申设计配置和制造，以优化不圆度。

8. 发明授权

US08534996B1 Vane segment tip clearance control 有权
标题翻译：叶片段顶端间隙控制
公开(公告)号：US08534996B1
公开(公告)日：2013-09-17
申请号：US12558705
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： F01D11/22
CPC分类号： F01D11/22 , F05D2260/56
摘要： A compressor stator vane and rotor blade tip clearance control assembly in which a plurality of stator vane segments each with vanes extending inward are connected to an annular sync ring through eccentric cranks so that circumferential movement of the sync ring will produce radial displacement of the vane segments and control the clearance between the blade tips. An actuator piston is rigidly fixed to the sync ring and forms an actuator chamber with stationary actuator housing. Bleed off pressure from one of the compressor stages is used to move the actuator piston, which moves the sync ring to radially displace the vane segments.
摘要翻译：压缩机定子叶片和转子叶片顶端间隙控制组件，其中每个具有向内延伸的叶片的多个定子叶片段通过偏心曲柄连接到环形同步环，使得同步环的周向运动将产生叶片段的径向位移并控制刀片尖端之间的间隙。致动器活塞刚性地固定到同步环上并形成具有固定致动器壳体的致动器室。从其中一个压缩机级排出的压力用于移动致动器活塞，致动器活塞使同步环移动以径向移动叶片段。

9. 发明授权

US08421263B2 Floating vertical axis wind turbine 有权
标题翻译：浮动垂直轴风力发电机
公开(公告)号：US08421263B2
公开(公告)日：2013-04-16
申请号：US12913023
申请日：2010-10-27
申请人： Jack W. Wilson, Jr. , John E. Ryznic , Joseph D. Brostmeyer
发明人： Jack W. Wilson, Jr. , John E. Ryznic , Joseph D. Brostmeyer
IPC分类号： F03D9/00
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。

10. 发明授权

US5354174A Backbone support structure for compressor 失效
标题翻译：压缩机的骨架支撑结构
公开(公告)号：US5354174A
公开(公告)日：1994-10-11
申请号：US19801
申请日：1992-11-09
申请人： James T. Balkcum , Jack W. Wilson, Jr.
发明人： James T. Balkcum , Jack W. Wilson, Jr.
IPC分类号： F01D25/24 , F04D29/64 , F04D29/60
CPC分类号： F04D29/644 , F01D25/246 , Y02T50/671
摘要： The backbone which is a load carrying support member of the aft end of the compressor of a gas turbine engine is fabricated from an annular disk-like element that is generally straight in cross section. The points of attachment permit circumferential thermal growth with radial restraint and snugness at judicious locations for minimizing scrubbing of the case-tied segmented inner stator case.
摘要翻译：作为燃气轮机的压缩机的后端的负载承载支承部件的骨架由截面为大致直线的环状的盘状元件制造。附着点允许在适当位置具有径向约束和舒适性的周向热增长，以最小化对盒式分段内定子壳体的擦洗。

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