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51. 发明申请

US20130272882A1 AXIALLY-SPLIT RADIAL TURBINES AND METHODS FOR THE MANUFACTURE THEREOF 有权
标题翻译：轴向分散式涡轮机及其制造方法
公开(公告)号：US20130272882A1
公开(公告)日：2013-10-17
申请号：US13444070
申请日：2012-04-11
申请人： Don Mittendorf , David K. Jan , Jason Smoke , Amandine Miner
发明人： Don Mittendorf , David K. Jan , Jason Smoke , Amandine Miner
IPC分类号： F01D5/02 , B23P15/04 , F01D5/14
CPC分类号： F01D5/147 , B23P15/006 , F01D5/04 , F01D5/045 , F01D5/046 , F01D5/048 , F01D5/066 , F01D5/088 , F01D5/18 , F01D5/187 , F01D5/28 , F01D5/30 , F05D2230/60 , Y02T50/671 , Y02T50/676 , Y10T29/49321 , Y10T29/49323 , Y10T29/49341
摘要： Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.
摘要翻译：轴向分离的径向涡轮机的实施例，如用于制造轴向分离的径向涡轮机的方法的实施例。在一个实施例中，该方法包括以下步骤：将前叶片环连接到前盘，以产生正向涡轮转子，制造后涡轮转子，以及将正向涡轮转子和后涡轮转子设置在轴向邻接的旋转固定关系以产生轴向分离的径向涡轮机。

52. 发明授权

US08496438B2 Blade retaining device for turbo machine propeller 有权
标题翻译：涡轮增压机螺旋桨叶片固定装置
公开(公告)号：US08496438B2
公开(公告)日：2013-07-30
申请号：US12709793
申请日：2010-02-22
申请人： Laurent Lafont
发明人： Laurent Lafont
IPC分类号： F01D5/30
CPC分类号： F02K3/025 , B64C11/06 , F01D5/147 , F01D5/30 , F01D7/00 , F01D21/045 , F02K3/062 , F04D29/34 , F05D2260/30 , F05D2260/74 , F05D2260/79 , Y02T50/66 , Y02T50/673
摘要： The invention concerns an aircraft turbomachine propeller comprising a plurality of blades (1) each comprising a root (20) mounted on a hub (2) rotating about the rotation axis of the propeller (I-I), and its purpose is to reduce the risks of loss of the entire blade (1) following an impact by a foreign body.To achieve this, at least one blade (1) comprises a means (30) of retaining the blade in an outwards radial direction, said retaining means (30) being engaged in a housing (5) of said blade (1) opening radially inwards at the root of the blade (20), and fixed in translation in said outwards radial direction.
摘要翻译：本发明涉及一种包括多个叶片（1）的飞机涡轮机推进器，每个叶片包括安装在围绕螺旋桨（II）的旋转轴线旋转的轮毂（2）上的根部（20），并且其目的是降低整个叶片（1）在异物撞击后的损失。为了实现这一点，至少一个叶片（1）包括将叶片保持在向外径向的装置（30），所述保持装置（30）接合在所述叶片（1）的径向向内开口的壳体（5）中在叶片（20）的根部处，并且以所述向外的径向方向固定成平移。

53. 发明申请

US20130177428A1 BLADE CONNECTION OF A ROTOR BLADE OF A WIND TURBINE 有权
标题翻译：风力涡轮机转子叶片的叶片连接
公开(公告)号：US20130177428A1
公开(公告)日：2013-07-11
申请号：US13823799
申请日：2011-09-05
申请人： Lenz Simon Zeller , Markus Werner
发明人： Lenz Simon Zeller , Markus Werner
IPC分类号： F01D5/30
CPC分类号： F01D5/30 , F03D1/0658 , F03D80/30 , Y02E10/721
摘要： A fastening element (12) for arrangement in a receptacle of a rotor blade connection (17) of a rotor blade (5). The receptacle is formed on the rotor hub-side end of the, preferably flange-free, rotor blade (5). The fastening element (12) is arranged in the receptacle between an inner fastening side and an outer fastening side of the rotor blade (5) and the fastening element (12) introduced into the receptacle (10) is connected to the inner fastening side and the outer fastening side of the rotor blade (5). The fastening element (12) is formed tapered in the longitudinal extension thereof. The fastening element (12) has a connector (15) transverse, particularly perpendicular, to the longitudinal extension for a lightning protection conductor (18) of the rotor blade (5).
摘要翻译：一种用于设置在转子叶片（5）的转子叶片连接件（17）的插座中的紧固元件（12）。容器形成在优选不具法兰的转子叶片（5）的转子轮毂侧端部上。紧固元件（12）布置在转子叶片（5）的内紧固侧和外紧固侧之间的插座中，并且引入到容器（10）中的紧固元件（12）连接到内紧固侧，转子叶片（5）的外部紧固侧。紧固元件（12）在其纵向延伸部中形成为锥形。紧固元件（12）具有横向，特别垂直于用于转子叶片（5）的防雷导体（18）的纵向延伸部的连接器（15）。

54. 发明申请

US20130156594A1 COMPOSITE ROTOR AND VANE ASSEMBLIES WITH INTEGRAL AIRFOILS 有权
标题翻译：复合转子和带集成空气的风扇组件
公开(公告)号：US20130156594A1
公开(公告)日：2013-06-20
申请号：US13331418
申请日：2011-12-20
申请人： Nicholas Joseph Kray , Christopher Lee McAfee , Dong-Jin Shim
发明人： Nicholas Joseph Kray , Christopher Lee McAfee , Dong-Jin Shim
IPC分类号： F01D5/14 , B29C70/06
CPC分类号： F01D5/282 , B29B11/16 , B29C70/48 , B29L2031/08 , F01D5/30 , F01D5/34 , F01D9/042 , F05D2300/6034 , Y02T50/672
摘要： A composite gas turbine engine structure includes a retention ring with airfoils mounted on, integral with, and extending radially away from retention ring. Retention ring includes annular composite plies, a circumferentially segmented airfoil ring including airfoil ring segments disposed around one of outer and inner circumferences of retention ring. Airfoil ring segments include annular bases and radially extending clockwise and counter-clockwise airfoil segments at clockwise and counter-clockwise ends of annular base. Composite airfoils include circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments. A flowpath shell circumferentially disposed around segmented airfoil ring traps annular bases between flowpath shell and retention ring. Composite airfoils airfoils extend through slots in flowpath shell. Plies may be wrapped in a single spiral made from a continuous composite tape. Slots may be circumferentially angled. Circumferentially adjacent ones of clockwise and counter-clockwise airfoil segments may be stitched together.
摘要翻译：复合燃气涡轮发动机结构包括具有与保持环安装在一体并与径向远离保持环的翼型的保持环。保持环包括环形复合层，周向分段的翼型环，包括围绕保持环的外周和内周中的一个设置的翼型环段。翼型环段包括环形基座和在环形基座的顺时针和逆时针端部处的径向延伸的顺时针和逆时针的翼型段。复合翼型件包括沿周向相邻的顺时针和逆时针翼型段。围绕分段翼型环周向设置的流路外壳环流体流路外壳和保持环之间的环形基座。复合翼型翼型件延伸穿过流道外壳中的槽。层可以包裹在由连续的复合胶带制成的单个螺旋。槽可以是周向成角度的。沿顺时针方向和逆时针方向的翼型段可以缝合在一起。

55. 发明申请

US20130121834A1 FAN HUB DESIGN 有权
标题翻译：风扇设计
公开(公告)号：US20130121834A1
公开(公告)日：2013-05-16
申请号：US13297300
申请日：2011-11-16
申请人： BARRY BARNETT
发明人： BARRY BARNETT
IPC分类号： F01D5/02
CPC分类号： F01D5/30 , F01D5/02 , F01D5/14 , F02K3/06 , F05D2220/32 , F05D2240/20 , F05D2260/941
摘要： A fan rotor has a fan web and a plurality of circumferentially spaced-apart fan blades extending radially outwardly from an outer rim of the fan web. The outer rim is integrally connected to an inner rim through an axially facing web section. The web section has an inward concavature and extends aft of the center of gravity of the fan blades to shift the center of gravity of the hub rearwards while maintaining airfoil stress below critical levels. The rim section may have an inwardly projecting annular channel formed in a leading edge thereof and tuned to the 2M3ND mode of the fan hub.
摘要翻译：风扇转子具有风扇腹板和从风扇腹板的外缘径向向外延伸的多个周向间隔开的风扇叶片。外缘通过轴向面对的腹板部分整体连接到内缘。腹板部分具有向内的凹陷并且延伸到风扇叶片的重心的后方，以使桨毂的重心向后移动，同时保持翼型压力低于临界水平。边缘部分可以具有形成在其前缘中的向内突出的环形通道并且被调谐到风扇轮毂的2M3ND模式。

56. 发明申请

US20130115089A1 ROTATABLE COMPONENT WITH CONTROLLED LOAD INTERFACE 有权
标题翻译：具有受控负载接口的可旋转组件
公开(公告)号：US20130115089A1
公开(公告)日：2013-05-09
申请号：US13289161
申请日：2011-11-04
申请人： Michael G. McCaffrey
发明人： Michael G. McCaffrey
IPC分类号： F01D5/30 , B32B37/14 , B32B7/02
CPC分类号： F01D5/3061 , B23K1/0018 , B23K1/19 , B23K20/002 , B23K20/023 , B23K20/12 , B23K20/1205 , B23K20/129 , B23K20/233 , B23K2101/001 , B23K2103/18 , B23K2103/26 , B23K2103/42 , B23P6/002 , F01D5/005 , F01D5/22 , F01D5/30 , F01D21/04 , F05D2200/33 , Y02T50/671 , Y10T29/49318 , Y10T29/49968 , Y10T156/10 , Y10T428/24942
摘要： A rotatable component includes a first section and a second section that is located radially outwards of the first section with regard to an axis of rotation about which the sections are co-rotatable. These sections are attached together at a bonded interface. At a perimeter region of the bonded interface a perimeter portion of the first section has a first stiffness and a perimeter portion of the second section has a second stiffness that is greater than the first stiffness.
摘要翻译：可旋转部件包括第一部分和第二部分，所述第一部分和第二部分相对于旋转轴线位于第一部分的径向外侧，所述部分围绕其旋转。这些部分在粘合界面处连接在一起。在接合界面的周边区域，第一部分的周边部分具有第一刚度，并且第二部分的周边部分具有大于第一刚度的第二刚度。

57. 发明申请

US20120263596A1 ANNULUS FILLER SYSTEM 审中-公开
公开(公告)号：US20120263596A1
公开(公告)日：2012-10-18
申请号：US13427427
申请日：2012-03-22
申请人： Dale E. EVANS , Ian C.D. CARE
发明人： Dale E. EVANS , Ian C.D. CARE
IPC分类号： F01D11/00
CPC分类号： F01D5/30 , F01D5/28 , F01D5/3092 , F01D11/008 , F05D2300/603
摘要： An annulus filler system bridges the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine. The system includes an annulus filler having a lid which extends between the adjacent blades and defines an airflow surface for air being drawn through the engine. The filler also has a support body extending beneath the lid and terminating in an elongate foot which, in use, extends along a groove provided in the rim of the disc. The groove has a neck which prevents withdrawal of the foot through the neck in a radially outward direction of the disc. The system further includes a sleeve which, after installation of the filler, is slidably locatable into a gap between the foot and sides of the groove.

58. 发明申请

US20110299992A1 ROTOR ASSEMBLY FOR GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的转子总成
公开(公告)号：US20110299992A1
公开(公告)日：2011-12-08
申请号：US12794918
申请日：2010-06-07
申请人： Eric W. Malmborg , Matthew E. Bintz
发明人： Eric W. Malmborg , Matthew E. Bintz
IPC分类号： F01D5/14
CPC分类号： F01D5/02 , F01D5/025 , F01D5/06 , F01D5/14 , F01D5/30 , F01D5/3069
摘要： A rotor assembly for a gas turbine engine includes a rotor airfoil and a first rotor disk. The rotor airfoil extends along a radial axis. The first rotor disk includes an outer rim, a bore and a web extending between the outer rim and the bore. The first rotor disk is axially offset from the radial axis of the rotor airfoil.
摘要翻译：用于燃气涡轮发动机的转子组件包括转子翼型件和第一转子盘。转子翼型件沿着径向轴线延伸。第一转子盘包括外缘，孔和在外缘和孔之间延伸的腹板。第一转子盘与转子翼型件的径向轴线轴向偏移。

59. 发明申请

US20090304515A1 METHOD AND DEVICE FOR JOINING BY WAY OF INDUCTIVE HF PRESSURE WELDING A ROTOR BLADE WITH A ROTOR SUPPORT OF A GAS TURBINE WITH AUTOMATIC SUPPLY OF THE ROTOR BLADE 审中-公开
标题翻译：用于通过电感式HF压力焊接方式和装置的转子叶片，具有转子叶轮的转子支撑，具有自动供应的转子叶片
公开(公告)号：US20090304515A1
公开(公告)日：2009-12-10
申请号：US12293540
申请日：2007-03-14
申请人： Herbert Hanrieder , Alexander Gindorf , Reinhold Meier
发明人： Herbert Hanrieder , Alexander Gindorf , Reinhold Meier
IPC分类号： F01D5/30 , B23K13/01 , B23P15/04 , B23Q7/02
CPC分类号： B23K13/01 , B23K2101/001 , B23P6/005 , B23P15/006 , F01D5/005 , F01D5/30 , F01D5/3061 , Y10T29/37
摘要： A method and a device for joining at least one rotor blade or at least one part of a rotor blade with a rotor support of a gas turbine, in particular a rotor blade connection of the rotor support, is disclosed. Corresponding connecting surfaces of the rotor blade, the rotor blade part, the rotor support or the rotor blade connection of the rotor support are joined by inductive high-frequency pressure welding. In this case, at least one rotor blade or rotor blade part is automatically supplied from at least one rotor blade reservoir and/or rotor blade part reservoir and, in addition, the rotor support is automatically positioned in such a way that the connecting surfaces to be joined are positioned precisely with respect to one another for the joining process.
摘要翻译：公开了一种用于将至少一个转子叶片或转子叶片的至少一部分与燃气轮机的转子支撑件，特别是转子支架的转子叶片连接件接合的方法和装置。转子叶片，转子叶片部分，转子支撑件或转子叶片连接的相应的连接表面通过感应式高频压力焊接。在这种情况下，至少一个转子叶片或转子叶片部分自动地从至少一个转子叶片贮存器和/或转子叶片部分储存器供应，此外，转子支撑件被自动定位成使得连接表面被连接相对于彼此精确定位用于接合过程。

60. 发明授权

US07628581B2 Rotating machine 有权
标题翻译：旋转机
公开(公告)号：US07628581B2
公开(公告)日：2009-12-08
申请号：US11276360
申请日：2006-02-27
申请人： Andrea De Simone , Jonas Fältström , Holger Kiewel , Thomas Kramer , Markus Roland Wiebe
发明人： Andrea De Simone , Jonas Fältström , Holger Kiewel , Thomas Kramer , Markus Roland Wiebe
IPC分类号： F04D29/08
CPC分类号： F01D5/30 , F01D5/303 , F01D5/3038 , F01D11/001 , F05D2240/60 , F05D2250/14
摘要： A rotating machine (10), in particular a compressor or turbine, has a rotor shaft (11) which is rotatable about an axis (20) and is provided with at least one slot (14). The mechanical stresses in the region of the slot are reduced in that the at least one slot (14) has a slot bottom (17) with an elliptic cross-sectional contour (24).
摘要翻译：旋转机器（10），特别是压缩机或涡轮机具有转子轴（11），该转子轴可绕轴线（20）旋转并且设置有至少一个槽（14）。槽的区域中的机械应力减小，因为至少一个槽（14）具有具有椭圆形横截面轮廓（24）的槽底（17）。

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