公开(公告)号：US06521861B2

公开(公告)日：2003-02-18

申请号：US09683594

申请日：2002-01-23

Applicant: Marshall Gordon Jones ,  Carl Edward Erikson ,  Kamlesh Mundra

Inventor： Marshall Gordon Jones ,  Carl Edward Erikson ,  Kamlesh Mundra

IPC: B23K2624

CPC classification number: F01D5/005 ,  B23K1/0018 ,  B23K1/005 ,  B23K11/00 ,  B23K11/0013 ,  B23K11/34 ,  B23K26/211 ,  B23K26/26 ,  B23K26/34 ,  B23K26/342 ,  B23K26/60 ,  B23K2101/001 ,  B23P6/005 ,  F05D2200/23 ,  F05D2230/235 ,  F05D2230/80

Abstract: A method of lasing a filler wire to weld a first workpiece to a second workpiece comprising first and second materials, respectively, includes positioning a tip of the filler wire above an opening defined by the workpieces. The tip extends over a width of the opening and over a portion of each of the workpieces. The filler wire is preheated and melted by directing a laser beam at the tip. The laser beam is advanced along a length of the opening with the tip positioned under the laser beam to form a high aspect ratio weld between the workpieces. The high aspect ratio weld has an aspect ratio of at least about two. The energy and time required for the laser beam to melt the filler wire is reduced as the filler wire is preheated.

Abstract translation: 一种激光填充焊丝将第一工件焊接到包括第一和第二材料的第二工件的方法，包括将填充焊丝的尖端定位在由工件限定的开口的上方。 尖端在开口的宽度和每个工件的一部分上方延伸。 通过在顶端引导激光束来预热和熔化填充线。 激光束沿着开口的长度前进，其中尖端位于激光束下方，以在工件之间形成高纵横比焊缝。 高纵横比焊缝的纵横比至少约为2。 当填充线被预热时，激光束熔化填充线所需的能量和时间被减小。

公开(公告)号：US08678749B2

公开(公告)日：2014-03-25

申请号：US12654830

申请日：2010-01-05

Applicant: Takeo S. Saitoh

Inventor： Takeo S. Saitoh

IPC: F01D1/36

CPC classification number: F01D1/026 ,  F01D1/32 ,  F01D1/36 ,  F01D5/028 ,  F05D2200/23 ,  F05D2250/713 ,  Y02E10/34

Abstract: A centrifugal reverse flow disk turbine for power generation, comprising; a) a turbine shaft; b) a disk rotor disposed on said turbine shaft; c) a housing, having said turbine shaft and said disk rotor, bearings, seal devices, and at least one jet nozzle means; d) a plurality of radially engraved channel for transporting working fluid from entering ports, placed axially near said turbine shaft; e) a plurality of said channels having two curvatures; first curvature has a small radius, and concaved pertinent to rotational direction of said rotor, starting from the entering port to middle of its flow path, and the second curvature has a large radius, convexed pertinent to rotational direction of said rotor, positioned near the peripheral of said rotor; a plurality of a bucket attached at every flow channel, directing against nozzle disposed on said housing, thereby deriving impinging counter supersonic flow.

Abstract translation: 一种用于发电的离心式逆流盘式涡轮机，包括： a）涡轮轴; b）设置在所述涡轮轴上的盘转子; c）具有所述涡轮轴和所述盘转子，轴承，密封装置和至少一个喷嘴装置的壳体; d）多个径向雕刻通道，用于将工作流体从进入端口输送，轴向位于所述涡轮轴的附近; e）多个所述通道具有两个曲率; 第一曲率具有小的半径，并且与所述转子的旋转方向相关，从其流动通道的入口开始到中间，并且第二曲率具有与所述转子的旋转方向相关的凸起的大半径， 所述转子的周边; 在每个流动通道处附接有多个铲斗，引导设置在所述壳体上的喷嘴，从而导致冲击反超声波流。

公开(公告)号：US20120163988A1

公开(公告)日：2012-06-28

申请号：US13337109

申请日：2011-12-24

Applicant: Bronwyn Power

Inventor： Bronwyn Power

IPC: F01D5/20 ,  F01D5/14

CPC classification number: F04D29/324 ,  F01D5/141 ,  F04D29/544 ,  F05D2200/23 ,  F05D2240/301 ,  F05D2250/70 ,  Y02T50/673

Abstract: A gas turbine engine airfoil shaped component is disclosed including in one form a compressor blade or vane having a tip portion capable of producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow. In one form the tip portion includes a camber angle distribution that produces relatively large change in camber angle near the leading edge but relatively flat distribution for remainder of blade. In one form the tip portion includes relatively large change in camber angle near trailing edge.

Abstract translation: 公开了一种燃气涡轮发动机翼型部件，其包括一种形式的压缩机叶片或叶片，该压缩机叶片或叶片具有能够在尖端的前缘附近产生相对较低压力的顶端部分，以引起流动动量流的局部射流。 在一种形式中，尖端部分包括外倾角分布，其在前缘附近产生相对大的外倾角变化，但对于叶片的其余部分而言相对平坦。 在一种形式中，尖端部分包括在后缘附近的相对较大的外倾角变化。

公开(公告)号：US5937633A

公开(公告)日：1999-08-17

申请号：US867302

申请日：1997-06-02

Applicant: Lin-Shu Wang

Inventor： Lin-Shu Wang

IPC: F02C3/36 ,  F02C7/143

CPC classification number: F02C3/36 ,  F05D2200/23 ,  F05D2260/211

Abstract: The present invention includes an intercooled cycle gas turbine. The intercooled cycle gas turbine is supercharged to improve performance. Pereformance is defined in terms of thermal efficiency and mass specific power, the turbine defining a cycle with a peak cycle pressure and a peak cycle temperature. The turbine includes an intercooler for intercooling the turbine, wherein placement of the intercooler within the cycle divides the cycle into a first compression stage and a second compression stage. The intercooler placement r=1/2 ln P.sub.super /ln(P.sub.peak /P.sub.super). The first compression stage and the second compression stage have an unequal pressure ratio.

Abstract translation: 本发明包括中间循环燃气轮机。 中间循环燃气轮机被增压以提高性能。 性能是根据热效率和质量比功率定义的，涡轮限定了具有峰值循环压力和峰值循环温度的循环。 涡轮机包括用于中间冷却涡轮机的中间冷却器，其中中间冷却器在循环内的放置将循环分成第一压缩级和第二压缩级。 中间冷却器放置r = 1/2 ln Psuper / ln（Ppeak / Psuper）。 第一压缩级和第二压缩级具有不等压比。

公开(公告)号：US09309769B2

公开(公告)日：2016-04-12

申请号：US13337109

申请日：2011-12-24

Applicant: Bronwyn Power

Inventor： Bronwyn Power

IPC: F01D5/14 ,  F04D29/32

CPC classification number: F04D29/324 ,  F01D5/141 ,  F04D29/544 ,  F05D2200/23 ,  F05D2240/301 ,  F05D2250/70 ,  Y02T50/673

Abstract: A gas turbine engine airfoil shaped component is disclosed including in one form a compressor blade or vane having a tip portion capable of producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow. In one form the tip portion includes a camber angle distribution that produces relatively large change in camber angle near the leading edge but relatively flat distribution for remainder of blade. In one form the tip portion includes relatively large change in camber angle near trailing edge.

Abstract translation: 公开了一种燃气涡轮发动机翼型部件，其包括一种形式的压缩机叶片或叶片，该压缩机叶片或叶片具有能够在尖端的前缘附近产生相对较低压力的顶端部分，以引起流动动量流的局部射流。 在一种形式中，尖端部分包括外倾角分布，其在前缘附近产生相对大的外倾角变化，但对于叶片的其余部分而言相对平坦。 在一种形式中，尖端部分包括在后缘附近的相对较大的外倾角变化。

公开(公告)号：US4748805A

公开(公告)日：1988-06-07

申请号：US807

申请日：1987-01-06

Applicant: Jacques Rigault ,  Pierre Bonnet

Inventor： Jacques Rigault ,  Pierre Bonnet

IPC: F02C7/00 ,  F01D25/30 ,  F15D1/04

CPC classification number: F01D25/30 ,  F15D1/04 ,  F05D2200/23 ,  F05D2250/191

Abstract: A gas turbine exhaust device installed at the outlet from the guide vane stage (5) of the turbine and upstream from an exhaust duct (10), said device comprising a jet diffuser (20) having orifices (25) perforated therethrough, with the axis of the diffuser being the same as the axis of the turbine.

Abstract translation: 一种燃气轮机排气装置，其安装在所述涡轮机的导叶台（5）的出口处并且位于排气管道（10）的上游，所述装置包括喷射扩散器（20），喷射扩散器（20）具有穿过其的孔口（25） 的扩散器与涡轮机的轴线相同。

公开(公告)号：US4337617A

公开(公告)日：1982-07-06

申请号：US147119

申请日：1980-05-06

Applicant: Trevor S. Smith

Inventor： Trevor S. Smith

IPC: F02C9/32 ,  F02C9/16

CPC classification number: F02C9/32 ,  F05D2200/23

Abstract: A gas turbine engine fuel control system has a three-dimensional cam which is positioned by sensed values of engine compressor inlet and outlet pressures. The cam has two profiles which respectively indicate a desired ratio of the compressor pressures and a desired fuel flow. Interlinked cam followers engage the respective cam profiles and are also responsive to a device for setting a desired engine thrust. The cam follower linkage positions a variable metering device for the engine fuel supply.

Abstract translation: 燃气涡轮发动机燃料控制系统具有通过发动机压缩机入口和出口压力的感测值定位的三维凸轮。 凸轮具有两个轮廓，其分别表示压缩机压力和期望燃料流量的期望比率。 互连的凸轮从动件接合相应的凸轮轮廓并且还响应于用于设定期望的发动机推力的装置。 凸轮随动件联动装置用于发动机燃料供应的可变计量装置。

公开(公告)号：US20110277446A1

公开(公告)日：2011-11-17

申请号：US12777508

申请日：2010-05-11

Applicant: Sean S. Stroud ,  Michael J. Piovoso

Inventor： Sean S. Stroud ,  Michael J. Piovoso

IPC: B64G1/40 ,  G06F17/50 ,  G06F17/10 ,  F02K3/00

CPC classification number: F02K9/80 ,  F02K9/08 ,  F02K9/58 ,  F05D2200/23 ,  F05D2200/24 ,  F05D2270/12 ,  F05D2270/13 ,  F05D2270/701

Abstract: Rockets, rocket motors, methods of controlling a rocket and methods of evaluating a rocket design are disclosed. In some embodiments, a method of controlling a rocket may include measuring a combustion chamber pressure, calculating a logarithm of the measured combustion chamber pressure, and computing the difference between the logarithm of the measured combustion chamber pressure and the logarithm of a reference combustion chamber pressure value to generate an error signal. The method may further include filtering the error signal to generate a compensated signal in the logarithm domain, and exponentiating of the compensated signal in the logarithm domain to provide a compensated signal in the physical domain.

Abstract translation: 公开了火箭，火箭发动机，控制火箭的方法和评估火箭设计的方法。 在一些实施例中，控制火箭的方法可以包括测量燃烧室压力，计算所测量的燃烧室压力的对数，以及计算所测量的燃烧室压力的对数与参考燃烧室压力的对数之间的差 值产生错误信号。 该方法还可以包括对误差信号进行滤波以产生对数域中的经补偿的信号，以及对数域中的补偿信号的指数，以在物理域中提供经补偿的信号。

公开(公告)号：US06702552B1

公开(公告)日：2004-03-09

申请号：US10130946

申请日：2002-05-24

Applicant: Jayden David Harman

Inventor： Jayden David Harman

IPC: F04D2938

CPC classification number: F01D5/141 ,  B63H1/26 ,  F03B3/121 ,  F03D1/0608 ,  F04D29/384 ,  F05B2200/23 ,  F05B2240/30 ,  F05D2200/23 ,  F05D2240/30 ,  Y02E10/223 ,  Y02E10/721 ,  Y02T50/673 ,  Y10S416/02

Abstract: A single or multi-bladed rotor for use with a fluid flow generator or reactor, the rotor comprising a central hub which is adapted to be mounted to a rotatable shaft, the rotor further comprises at least one radial blade mounted at one end to the hub, wherein the at least one blade has a fluid reactive face which has the configuration of a logarithmic curve substantially conforming to the golden section, i.e. the order of growth of the radius of the curve which is measured at equiangular radii is constant and conforms to the ratio of 5:8.

Abstract translation: 用于与流体流动发生器或反应器一起使用的单叶片或多叶片转子，所述转子包括适于安装到可旋转轴的中心毂，所述转子还包括至少一个径向叶片，其一端安装到所述轮毂 ，其中所述至少一个叶片具有流体反应面，其具有基本上符合黄金部分的对数曲线的构型，即在等角半径处测量的曲线的半径的生长的次数是恒定的，并且符合 比例为5：8。

公开(公告)号：US5584660A

公开(公告)日：1996-12-17

申请号：US430948

申请日：1995-04-28

Applicant: David B. Carter ,  Michael A. Weisse

Inventor： David B. Carter ,  Michael A. Weisse

IPC: B23P15/04 ,  F01D5/14 ,  F01D5/18

CPC classification number: F01D5/147 ,  B23P15/04 ,  F05D2200/23 ,  Y02T50/671 ,  Y10S416/02 ,  Y10T29/49339

Abstract: A hollow airfoil (10) for a gas turbine engine having a leading edge (12), a trailing edge (14), a pressure side (20), and a suction side (22) includes a plurality of internal spanwise stiffening ribs (31-35) that are arranged in a logarithmic pattern. The particular arrangement of internal fibs (31-35) optimizes stiffness of the airfoil (10) without significantly increasing the weight thereof.

Abstract translation: 一种用于具有前缘（12），后缘（14），压力侧（20）和吸力侧（22）的燃气涡轮发动机的中空翼片（10）包括多个内翼展加强筋 -35），它们以对数模式排列。 内部纤维（31-35）的特定布置优化翼型件（10）的刚度，而不显着增加其重量。