公开(公告)号：US20140341713A1

公开(公告)日：2014-11-20

申请号：US14279753

申请日：2014-05-16

Applicant: GE AVIO S.r.l.

Inventor： Davide TORZO ,  Ennio SPANO

IPC: F01D1/04 ,  F01D9/02 ,  F01D25/24

CPC classification number: F01D1/04 ,  F01D9/02 ,  F01D9/04 ,  F01D25/24 ,  F02C7/24 ,  F02K1/827 ,  F05D2220/3215 ,  F05D2230/60 ,  F05D2260/96 ,  F05D2260/961 ,  Y10T29/49245

Abstract: A low pressure turbine, in particular for a gas turbine engine, extends along an axis, has an annular conduit for guiding a gas flow and is provided with a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of the stator arrays, considering the advancement direction of the gas flow, has a plurality of blades, which define a plurality of spaces between them in circumferential direction; the spaces are split by respective splitters into a radially outer conduit and into a radially inner conduit; the radial position of the splitters is in the neighborhood of a radial reference position such that at least one acoustic mode is of the cut-on type in the radially inner conduit.

Abstract translation: 特别是用于燃气涡轮发动机的低压涡轮机沿着轴线延伸，具有用于引导气流的环形导管，并且设置有多个叶片的定子阵列和多个叶片的转子阵列; 考虑到气流的前进方向，最后的定子排列具有多个叶片，它们在圆周方向上在它们之间限定多个空间; 空间由相应的分离器分裂成径向外部管道并进入径向内部管道; 分离器的径向位置在径向参考位置附近，使得至少一个声学模式在径向内部管道中具有切割型。

公开(公告)号：US20140333070A1

公开(公告)日：2014-11-13

申请号：US14349917

申请日：2012-09-27

Applicant: AKTIEBOLAGET SKF

Inventor： Andreas Clemens Van Der Ham ,  Frank Bartl

IPC: F01D15/10 ,  F16C37/00 ,  F01D1/04

CPC classification number: F01D15/10 ,  F01D1/04 ,  F04D29/05 ,  F16C35/00 ,  F16C37/00 ,  F16C41/004 ,  H02K7/1823

Abstract: A power generating bearing assembly comprising a bearing retained by a bearing housing is provided. The bearing housing includes a bearing cooling passage system comprising at least one integrated liquid cooling passage is integrated within the bearing housing. A turbine assembly is inserted within the integrated liquid cooling passage, wherein fluid flowing within the integrated liquid cooling passage causes a turbine blade subassembly within the turbine assembly to rotate. The rotation of the turbine blade subassembly rotates an electrical power generator to create electrical power. The turbine assembly can be integrated into any existing bearing assembly comprising a bearing cooling passage system. It is preferred to seat the turbine assembly within a cooling system port of the bearing cooling passage system.

Abstract translation: 提供一种发电轴承组件，其包括由轴承壳体保持的轴承。 轴承壳体包括轴承冷却通道系统，其包括集成在轴承壳体内的至少一个集成液体冷却通道。 涡轮机组件插入集成液体冷却通道内，其中在集成液体冷却通道内流动的流体使涡轮机组件内的涡轮叶片子组件旋转。 涡轮叶片子组件的旋转使发电机旋转以产生电力。 涡轮组件可以集成到包括轴承冷却通道系统的任何现有的轴承组件中。 优选将涡轮组件安置在轴承冷却通道系统的冷却系统端口内。

公开(公告)号：US20140169957A1

公开(公告)日：2014-06-19

申请号：US13719566

申请日：2012-12-19

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shezan Kanjiyani ,  Natalie Wali ,  Don Mittendorf ,  Lorenzo Crosatti

IPC: F01D1/04 ,  B23P11/00

CPC classification number: F01D1/04 ,  B23P11/00 ,  F01D9/041 ,  F01D9/042 ,  F05D2230/60 ,  F05D2260/941 ,  Y02T50/671 ,  Y10T29/49245

Abstract: Embodiments of a turbine nozzle are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring and a slip joint ring, which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots therein. A plurality of vanes is fixedly coupled to the support ring and extends radially therefrom into the plurality of slots. A plurality of radial slip joints is formed between the plurality of vanes and the plurality slots. Each slip joint extends around a different one of the plurality of vanes to permit relative radial movement between the plurality of vanes and the slip joint ring during operation of the turbine nozzle.

Abstract translation: 提供涡轮喷嘴的实施例，如制造涡轮喷嘴的方法的实施例。 在一个实施例中，涡轮喷嘴包括支撑环和滑动接头环，其与支撑环基本上同心并且与其径向间隔开。 滑接环在其中具有多个狭槽。 多个叶片固定地联接到支撑环并且从其径向延伸到多个狭槽中。 在多个叶片和多个槽之间形成多个径向滑动接头。 每个滑动接头围绕多个叶片中的不同的叶片延伸，以允许在涡轮喷嘴的操作期间在多个叶片和滑动接头环之间的相对径向移动。

公开(公告)号：US08753065B2

公开(公告)日：2014-06-17

申请号：US13758075

申请日：2013-02-04

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F01D1/24

CPC classification number: F02C7/36 ,  F01D1/04 ,  F01D9/041 ,  F01D25/162 ,  F02C3/04 ,  F02C7/00 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/50 ,  F05D2260/40311

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an axis and a speed reduction device in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps.

Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括除了别的以外的风扇部分，其包括可围绕轴线旋转的风扇和与风扇连通的减速装置。 减速装置包括具有至少1.5的星形齿轮比的星形驱动齿轮系。 风扇的风扇叶片尖端速度小于1400 fps。

公开(公告)号：US08702376B2

公开(公告)日：2014-04-22

申请号：US12902588

申请日：2010-10-12

Applicant: Thomas Mokulys ,  Vishal Borikar ,  Giorgio Zanazzi ,  Davor Kriz ,  Ludwig Boxheimer ,  Luca Ripamonti

Inventor： Thomas Mokulys ,  Vishal Borikar ,  Giorgio Zanazzi ,  Davor Kriz ,  Ludwig Boxheimer ,  Luca Ripamonti

IPC: F01D1/00

CPC classification number: F01D1/06 ,  F01D1/023 ,  F01D1/04 ,  F01D5/043 ,  F01D5/145 ,  F01D5/28 ,  F05D2210/43 ,  F05D2270/17

Abstract: The disclosure relates to a radially fed axial steam turbine with a cold inlet duct, axially displaced from a hot inlet duct such that is it further away from a first blade row than the hot inlet duct. The cold inlet duct receives a cold steam from a cold inlet spiral and directs it into the hot inlet duct in such a way that a boundary layer of cold steam is formed over the rotor circumferential surface between the outlet end of the cold inlet duct and the blade and vane rows. The rotor circumferential surface is also adapted to promote and maintain the boundary layer. In this way, a maximum temperature to which the rotor is exposed can be reduced.

Abstract translation: 本公开涉及具有冷入口管道的径向馈送的轴向蒸汽涡轮机，其从热入口管道轴向移位，使得其比热入口管道更远离第一叶片排。 冷入口管道接收来自冷入口螺旋的冷蒸汽并将其引导到热入口管道中，使得在冷入口管道的出口端和冷入口管道的出口端之间的转子圆周表面上形成冷蒸汽边界层 叶片和叶片行。 转子圆周表面也适于促进和保持边界层。 以这种方式，能够降低转子露出的最高温度。

公开(公告)号：US20130266439A1

公开(公告)日：2013-10-10

申请号：US13860173

申请日：2013-04-10

Applicant: FLODESIGN WIND TURBINE CORP.

Inventor： Rune Rubak ,  Carsten H. Westergaard ,  Søren Hjort

IPC: F01D1/04

CPC classification number: F01D1/04 ,  F03D1/04 ,  F05B2240/122 ,  F05B2240/123 ,  F05B2240/1231 ,  F05B2240/124 ,  F05B2240/133 ,  F05B2250/182 ,  Y02E10/72

Abstract: The present disclosure relates to fluid turbines having a turbine shroud assembly formed with mixing elements (e.g., both inwardly and outwardly curving elements) having airfoil cross sections. These airfoils form ringed airfoil shapes that provide a means of controlling the flow of fluid over the rotor assembly or over portions of the rotor assembly. The fluid dynamic performance of the ringed airfoils directly affects the performance of the turbine rotor assembly. The mass and surface area of the shrouds result in load forces on support structures. By delaying or eliminating the separation of the boundary layer over the ringed airfoils, boundary layer energizing members (e.g., vortex generators, flow control ports) on the ringed airfoils increase the power output of the fluid turbine system and allow for relatively shorter chord-length airfoil cross sections and therefore reduced mass and surface area of the shroud assemblies.

Abstract translation: 本公开涉及具有涡轮机护罩组件的流体涡轮机，该涡轮机护罩组件形成有具有翼型截面的混合元件（例如，向内和向外的弯曲元件）。 这些翼型件形成环形翼型，其提供控制流体在转子组件上或在转子组件的部分上方的流动的手段。 环形翼型件的流体动力学性能直接影响涡轮转子组件的性能。 护罩的质量和表面积导致支撑结构上的载荷力。 通过延迟或消除环形翼型件上的边界层的分离，环形翼型上的边界层通电构件（例如，涡流发生器，流量控制端口）增加了流体涡轮机系统的功率输出并且允许相对较短的弦长 机翼横截面因此降低了护罩组件的质量和表面积。

公开(公告)号：US08468797B2

公开(公告)日：2013-06-25

申请号：US13339972

申请日：2011-12-29

Applicant: Om P. Sharma ,  Michael F. Blair

Inventor： Om P. Sharma ,  Michael F. Blair

IPC: F04D29/38 ,  F02K3/00

CPC classification number: F02C3/14 ,  F01D1/04 ,  F01D5/142 ,  F02C7/18 ,  F05D2220/3212 ,  F05D2240/12 ,  F05D2260/202

Abstract: An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a ratio of a number of stages in the low-pressure turbine to a number of stages in the high-pressure turbine is 2.

Abstract translation: 示例性的燃气涡轮发动机包括涡轮机部分，其可操作以将旋转能量赋予压缩机部分。 涡轮部至少包括低压涡轮机和高压涡轮机，并且低压涡轮机中的级数与高压涡轮机中的级数的比率为2。

公开(公告)号：US20130136592A1

公开(公告)日：2013-05-30

申请号：US13304720

申请日：2011-11-28

Applicant: Paul Kendall Smith ,  Mary Virginia Holloway ,  San Jason Nguyen ,  Daniel Jackson Dillard

Inventor： Paul Kendall Smith ,  Mary Virginia Holloway ,  San Jason Nguyen ,  Daniel Jackson Dillard

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F01D1/04 ,  F01D5/142 ,  F05D2250/74

Abstract: A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

公开(公告)号：US20120093640A1

公开(公告)日：2012-04-19

申请号：US13073015

申请日：2011-03-28

Applicant: Hsiao-Wei D. Chiang ,  Chih-Neng Hsu ,  Shun-Yao Chuang ,  Chee-Chang Chen

Inventor： Hsiao-Wei D. Chiang ,  Chih-Neng Hsu ,  Shun-Yao Chuang ,  Chee-Chang Chen

IPC: F01D25/28

CPC classification number: F01D15/10 ,  F01D1/04 ,  F01D5/026 ,  F01D15/00 ,  F01D25/162 ,  F05D2220/20 ,  F05D2250/82

Abstract: The present invention discloses a micro turbine which can be a power source of a distributed pneumatic turbine generator and comprises: a first outer casing comprising a gas inlet, a first accommodating space and a first connecting part; a second outer casing comprising a second accommodating space, a second connecting part and a bearing seat, wherein the second outer casing is connected with the first outer casing by the connection between the second connecting part and the first connecting part; a stator being disposed in the first accommodating space; and a rotor being disposed in the second accommodating space and comprising a rotor body and a rotating shaft, wherein one end of the rotating shaft is pivotally coupled to the center of the stator, and another end of the rotating shaft being pivotally coupled to the center of the bearing seat of the second outer casing and extending toward the outside of the second outer casing.

Abstract translation: 本发明公开了一种微型涡轮，其可以是分布式气动涡轮发电机的动力源，包括：第一外壳，包括气体入口，第一容纳空间和第一连接部分; 第二外壳，包括第二容纳空间，第二连接部和轴承座，其中所述第二外壳通过所述第二连接部和所述第一连接部之间的连接与所述第一外壳连接; 定子被布置在所述第一容纳空间中; 并且转子设置在所述第二容纳空间中并且包括转子体和旋转轴，其中所述旋转轴的一端枢转地联接到所述定子的中心，并且所述旋转轴的另一端枢转地联接到所述中心 的第二外壳的轴承座并且朝向第二外壳的外侧延伸。

公开(公告)号：US20100115946A1

公开(公告)日：2010-05-13

申请号：US12291148

申请日：2008-11-07

Applicant: Ronald Edward Graf

Inventor： Ronald Edward Graf

IPC: F01K27/00

CPC classification number: F01D1/34 ,  F01D1/04 ,  F01K25/00 ,  F04D25/04

Abstract: An engine/heat pump is shown. Most of its parts rotate around the same central axis. It comprises two doubly connected chambers. Blades in each chamber substantially rotate with the chamber and may be firmly attached to the walls of the chamber, thus forming a modified centrifugal pump with axial input and discharge. An expandable fluid is rotated outward by one of the pumps and then heat is added for an engine of removed for a heat pump as the fluid is being sent to the outer part of the second pump. The fluid travels toward the center of the second pump, thus impelling the pump in the rotation direction. Then heat is removed for an engine or added for a heat pump as the fluid leaves the second pump and travels back to the first pump near the center of rotation. Rotation energy of the fluid is typically much larger than the circulation energy. A modified centrifugal pump with axial discharge having a casing rotating with the blades is also claimed.

Abstract translation: 显示发动机/热泵。 它的大部分部件围绕同一个中心轴旋转。 它包括两个双连接的腔室。 每个室中的叶片基本上与室一起旋转并且可以牢固地附接到室的壁，从而形成具有轴向输入和排出的改进的离心泵。 可膨胀流体由泵中的一个向外旋转，然后当流体被送到第二泵的外部时，加热用于热泵的去除的发动机。 流体朝向第二泵的中心移动，从而沿着旋转方向推动泵。 然后当发动机离开第二个泵并在旋转中心附近返回到第一个泵时，为发动机移除热量或加入热泵。 流体的旋转能量通常远大于循环能量。 还要求具有轴向排出的改进的离心泵，其具有与叶片一起旋转的壳体。