公开(公告)号：US20150226076A1

公开(公告)日：2015-08-13

申请号：US14343406

申请日：2012-09-06

申请人： NUOVO PIGNONE S.p.A.

发明人： Matteo Berti ,  Stefano Bresciani ,  Ravindranath Ps ,  Lorenza Sassolini ,  Alessandro Ciani

IPC分类号： F01D11/00 ,  F01D25/12 ,  F01D1/04 ,  F01D11/02

CPC分类号： F01D11/001 ,  F01D11/003 ,  F01D11/02 ,  F01D11/025 ,  F01D11/04 ,  F01D11/18 ,  F01D11/24 ,  F01D25/12 ,  F16J15/002 ,  F16J15/3404 ,  F16J15/447 ,  F16J15/4472

摘要： A rotary machine includes a machine rotor, a machine stator, a labyrinth seal disposed between the machine rotor and the machine stator, a dry gas seal disposed between the machine rotor and the machine stator, the dry gas seal being disposed downstream of the labyrinth seal, the labyrinth seal including a labyrinth seal rotor, and, a labyrinth seal stator, the labyrinth seal stator having a cavity containing a heat transfer medium configured to transfer heat between the labyrinth seal stator and a zone adjacent the labyrinth seal stator to cool or heat a pressurized process fluid before the process fluid bears against the dry gas seal.

摘要翻译： 旋转机械包括机器转子，机械定子，设置在机器转子和机器定子之间的迷宫式密封件，设置在机器转子和机器定子之间的干式气体密封件，干燥气体密封件设置在迷宫式密封件 ，迷宫式密封件包括迷宫式密封转子和迷宫式密封定子，迷宫式密封定子具有包含传热介质的空腔，该传热介质构造成在迷宫式密封定子与邻近迷宫式密封定子的区域之间传递热量，以冷却或加热 在加工流体承受干气密封之前的加压工艺流体。

公开(公告)号：US09097128B2

公开(公告)日：2015-08-04

申请号：US13407099

申请日：2012-02-28

申请人： Matthew Robert Piersall ,  Spencer Aaron Kareff

发明人： Matthew Robert Piersall ,  Spencer Aaron Kareff

IPC分类号： F01D11/00

CPC分类号： F01D11/001 ,  F01D5/3015 ,  F01D11/02 ,  F05D2250/38 ,  F05D2250/712 ,  F05D2300/175

摘要： A seal for a turbine engine is provided that includes a seal body disposed at a base of a turbine engine blade and a wing portion extending axially from the seal body. The wing portion has a first portion substantially parallel with a centerline of the engine and an angled upturn portion. The first portion extends between the seal body and the angled upturn portion. An angle between the engine centerline and the angled upturn portion is between about 0 degrees and about 90 degrees.

摘要翻译： 提供了一种用于涡轮发动机的密封件，其包括设置在涡轮发动机叶片的基部处的密封体和从密封体轴向延伸的翼部。 翼部具有基本上平行于发动机的中心线的第一部分和倾斜的上翘部分。 第一部分在密封体和倾斜的上翘部分之间延伸。 发动机中心线和倾斜上翻部分之间的角度在约0度和约90度之间。

公开(公告)号：US09074486B2

公开(公告)日：2015-07-07

申请号：US13018080

申请日：2011-01-31

申请人： Hrishikesh Vishvas Deo ,  Binayak Roy

发明人： Hrishikesh Vishvas Deo ,  Binayak Roy

IPC分类号： F16J15/447 ,  F16J15/44 ,  F01D11/02 ,  F01D11/00

CPC分类号： F01D11/003 ,  F01D11/02 ,  F01D11/025 ,  F05D2240/55 ,  F16J15/445 ,  F16J15/4472 ,  Y10T29/49826

摘要： The present disclosure relates to a seal assembly for a turbomachine that includes at least one arcuate plate, a biasing member, and at least one packing ring segment. The packing ring segment includes at least one barrier that restricts circumferential flow of a fluid along the packing ring segment. In addition, the seal assembly includes a plurality of arcuate teeth disposed intermediate to the packing ring segment and the rotor. The clearances of at least two of the arcuate teeth are different from one another.

摘要翻译： 本发明涉及一种用于涡轮机的密封组件，其包括至少一个弧形板，偏置构件和至少一个填料环段。 填料环段包括限制流体沿填料环段的周向流动的至少一个阻挡层。 此外，密封组件包括设置在填料环段和转子之间的多个弧形齿。 至少两个弓形齿的间隙彼此不同。

公开(公告)号：US20150184529A1

公开(公告)日：2015-07-02

申请号：US14146292

申请日：2014-01-02

申请人： General Electric Company

发明人： Xiaoqing Zheng ,  Thomas Joseph Farineau ,  Sacheverel Quentin Eldrid ,  Jason L. Bowers

IPC分类号： F01D9/04

CPC分类号： F01D9/045 ,  F01D5/08 ,  F01D9/06 ,  F01D9/065 ,  F01D11/003 ,  F01D11/005 ,  F01D11/02 ,  F01D25/12 ,  F01D25/24 ,  F05D2240/55 ,  Y10T29/49316

摘要： A steam turbine is provided. The steam turbine includes a housing and a steam inlet configured to discharge a primary steam flow within the housing. A stator is coupled to the housing and a rotor is coupled to the housing and located within the stator. The rotor and the stator are configured to define a primary flow path there between and in flow communication with the primary steam flow. The steam turbine includes a seal assembly coupled to the housing. The seal assembly includes a packing head and a plurality of seals. The packing head is configured to define a cooling flow path in flow communication with the rotor and configured to discharge a cooling steam flow toward the rotor. An anti-swirl device is coupled to the seal assembly and located between the rotor and the packing head.

摘要翻译： 提供蒸汽轮机。 蒸汽轮机包括壳体和构造成排出壳体内的主蒸汽流的蒸汽入口。 定子联接到壳体并且转子联接到壳体并且定位在定子内。 转子和定子构造成在其间限定主流动路径，并与主蒸汽流动流动连通。 蒸汽轮机包括联接到壳体的密封组件。 密封组件包括密封头和多个密封件。 包装头构造成限定与转子流动连通的冷却流动路径，并且构造成朝向转子排放冷却蒸汽流。 防旋转装置联接到密封组件并且位于转子和包装头之间。

公开(公告)号：US20150118080A1

公开(公告)日：2015-04-30

申请号：US14395528

申请日：2013-04-11

申请人： BorgWarner Inc.

发明人： Stephanie Dextraze

IPC分类号： F01D5/04 ,  F04D29/28 ,  F01D5/14 ,  F04D25/04

CPC分类号： F01D5/048 ,  F01D5/143 ,  F01D5/145 ,  F01D5/146 ,  F01D5/20 ,  F01D11/02 ,  F04D25/04 ,  F04D29/162 ,  F04D29/284 ,  F04D29/30 ,  F04D29/4213 ,  F04D29/685 ,  F05D2220/40 ,  F05D2240/307

摘要： A turbocharger (5) comprising a housing (10) including a compressor shroud (14) and a turbine shroud (12). The turbocharger (5) also includes a compressor wheel (18) and a turbine wheel (116, 216, 316, 416). The compressor wheel (18) includes a compressor hub (44) and a plurality of circumferentially spaced compressor blades (45, 46) extending radially from the compressor hub (44). The turbine wheel (116, 216, 316, 416) includes a turbine hub (124, 224, 324, 424) and a plurality of circumferentially spaced blades (126, 226, 326, 426) extending radially from the turbine hub (124, 224, 324, 424) with a hub surface (125, 225, 325, 425) extending between adjacent blades (126, 226, 326, 426). The turbine wheel (116, 216, 316, 416) also includes at least one surface discontinuity (135, 235, 335, 435) on the turbine hub surface (125, 225, 325, 425).

摘要翻译： 一种涡轮增压器（5），包括包括压缩机罩（14）和涡轮罩（12）的壳体（10）。 涡轮增压器（5）还包括压缩机叶轮（18）和涡轮机叶轮（116,216,316,416）。 压缩机叶轮（18）包括压缩机毂（44）和从压缩机毂（44）径向延伸的多个周向间隔开的压缩机叶片（45,46）。 涡轮机叶轮（116,216,316,416）包括涡轮机毂（124,224,324,424）以及从涡轮机毂（124,124,324,424）径向延伸的多个周向间隔开的叶片（126,226,326,426） 224,224,424），其具有在相邻叶片（126,226,326,426）之间延伸的轮毂表面（125,225,325,425）。 涡轮机叶轮（116,216,316,416）还包括在涡轮机毂表面（125,225,325,425）上的至少一个表面不连续（135,235,335,435）。

公开(公告)号：US20150086343A1

公开(公告)日：2015-03-26

申请号：US14395869

申请日：2013-04-26

申请人： Nuovo Pignone Srl

发明人： Emanuele Rizzo ,  Antonio Pelagotti

IPC分类号： F01D11/02 ,  F01D11/08

CPC分类号： F01D11/02 ,  F01D11/08 ,  F04D29/102 ,  F04D29/106 ,  F04D29/668 ,  F04D29/669 ,  F16J15/406 ,  F16J15/44 ,  F16J15/4472

摘要： A device for sealing a high pressure region in a turbomachine from a low pressure region; the turbomachine has one or more statoric parts and one or more rotoric parts; the device comprises a labyrinth seal having a first plurality of grooves and a second plurality of grooves; the first plurality of grooves is disposed in a helical pattern and the second plurality of grooves is disposed in a cylindrical pattern; the labyrinth seal is disposed between at least one of the one or more rotoric parts of the turbomachine and at least one of the one or more statoric parts of the turbomachine between the high pressure region and the low pressure region of the turbomachine; the helical pattern has a helix angle less than or equal to 10°, wherein a stabilization effect of the turbomachine is obtained and leakage due to the second plurality of grooves is negligible.

摘要翻译： 一种用于从低压区域密封涡轮机中的高压区域的装置; 涡轮机具有一个或多个定子部分和一个或多个转子部分; 所述装置包括具有第一多个凹槽和第二多个凹槽的迷宫式密封件; 所述第一多个凹槽以螺旋形图案设置，所述第二多个凹槽设置成圆柱形图案; 迷宫式密封件设置在涡轮机的一个或多个转子部分中的至少一个和涡轮机的高压区域和低压区域之间的涡轮机的一个或多个定子部分中的至少一个之间; 螺旋图案具有小于或等于10°的螺旋角，其中获得涡轮机的稳定效果，并且由于第二多个凹槽导致的泄漏可忽略。

公开(公告)号：US08985592B2

公开(公告)日：2015-03-24

申请号：US13359578

申请日：2012-01-27

申请人： Andrew G. Green ,  Daniel R. Leggett ,  Sachin R. Shinde

发明人： Andrew G. Green ,  Daniel R. Leggett ,  Sachin R. Shinde

IPC分类号： F16J15/02 ,  F16J15/08 ,  F01D9/02 ,  F01D11/00 ,  F01D11/02

CPC分类号： F16J15/0887 ,  F01D9/023 ,  F01D11/005 ,  F01D11/02 ,  F05D2240/57

摘要： A system (10) is provided for sealing a gap (12) between a transition exit frame (14) and a vane rail (18) at a turbine inlet (20). The system includes a seal (11) with a compliant seal member having a generally u-shaped profile to provide a sealing function in an axial direction. The compliant seal member includes a U-shaped inner sheet (28) securely pressed within a U-shaped outer sheet (26). The outer and inner sheets include spaced-apart segments (30, 32) in a lateral direction which are spaced-apart by misaligned slots (36, 38) to block passage of air there through. The system may also include wear resistant material (62) interposed between the seal and the vane rail. A lateral gap between adjacent exit frames may include a plurality of ribs defining valleys and tips, with crushable material disposed between the valleys and tips.

摘要翻译： 提供一种用于在涡轮机入口（20）处密封过渡出口框架（14）和叶片导轨（18）之间的间隙（12）的系统（10）。 该系统包括具有柔性密封构件的密封件（11），该密封件具有大致U形的轮廓，以在轴向方向上提供密封功能。 柔性密封构件包括牢固地压在U形外片（26）内的U形内片（28）。 外片和内片包括沿横向方向的间隔开的片段（30,32），它们被不对准的狭槽（36,38）间隔开，以阻止空气通过。 该系统还可以包括介于密封件和叶片导轨之间的耐磨材料（62）。 相邻出口框架之间的横向间隙可以包括限定谷部和尖端的多个肋条，其中可挤压材料设置在谷部和尖端之间。

公开(公告)号：US08967957B2

公开(公告)日：2015-03-03

申请号：US13288100

申请日：2011-11-03

申请人： Gary Michael Itzel ,  Christopher Michael Penny ,  Aaron Ezekiel Smith ,  Kevin Leon Bruce

发明人： Gary Michael Itzel ,  Christopher Michael Penny ,  Aaron Ezekiel Smith ,  Kevin Leon Bruce

IPC分类号： F04D29/08 ,  F01D11/02 ,  F01D5/28

CPC分类号： F01D11/02 ,  F01D5/288 ,  Y02T50/671

摘要： A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.

摘要翻译： 装备有一个或多个天使翼的旋转翼型零件，其阻止热工作流体进入其中安装该部件的涡轮机的内部区域。 该部件包括翼型件和用于安装部件以使部件在涡轮机内旋转的特征。 天使翼从部件突出以具有面向翼型的第一表面，面对安装特征的相对设置的第二表面以及其间的至少一个侧表面。 绝热涂层系统存在于第一表面上以抑制从工作流体传递到天使翼而不是在第二或侧面上的热传递，从而不会妨碍从天使翼的第二和侧面的热传递。

公开(公告)号：US20150003973A1

公开(公告)日：2015-01-01

申请号：US13930482

申请日：2013-06-28

申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, Jr. ,  John J. Marra ,  Christian X. Campbell

发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, Jr. ,  John J. Marra ,  Christian X. Campbell

IPC分类号： F01D11/02 ,  F01D5/18

CPC分类号： F01D11/02 ,  F01D5/082 ,  F01D5/18 ,  F01D5/187 ,  F01D11/04 ,  F05D2260/14

摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.

摘要翻译： 外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面 （74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。 抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。

公开(公告)号：US20150003963A1

公开(公告)日：2015-01-01

申请号：US14132738

申请日：2013-12-18

申请人： Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

发明人： Linnea Taketa ,  John Munson ,  Ted J. Freeman

IPC分类号： F01D11/00 ,  F01D11/02 ,  F01D5/28 ,  F01D9/04 ,  F01D17/14

CPC分类号： F01D11/005 ,  F01D5/28 ,  F01D9/041 ,  F01D11/00 ,  F01D11/02 ,  F01D11/025 ,  F01D11/122 ,  F01D17/148 ,  F01D17/162 ,  F01D17/165 ,  F04D19/02 ,  F04D27/002 ,  F04D27/0246 ,  F04D29/083 ,  F04D29/164 ,  F05B2240/571 ,  F05D2240/56 ,  F16J15/3288

摘要： A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be a variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.

摘要翻译： 公开了一种燃气涡轮发动机的涡轮机械部件，其具有减少燃气涡轮发动机的翼型构件和燃气涡轮发动机的壁之间的间隙流的影响的许多技术。 翼型构件可以是可变的，并且一种形式是可变涡轮叶片。 在一个实施例中，叶片和壁之间包括刷密封件。 在另一种形式中，磨损表面设置在叶片和壁之间。 在另一种形式中，能够被致动以改变位置的可移动构件可以设置在叶片和壁之间，以改变两者之间的间隙的尺寸。