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61. 发明申请

US20090113708A1 Method for joining components 审中-公开
标题翻译：连接组件的方法
公开(公告)号：US20090113708A1
公开(公告)日：2009-05-07
申请号：US11363741
申请日：2006-02-28
申请人： Joachim Bamberg , Wilhelm Satzger
发明人： Joachim Bamberg , Wilhelm Satzger
IPC分类号： B23P15/04
CPC分类号： F01D5/005 , B23K20/1205 , B23K20/129 , B23K20/16 , B23K20/233 , B23K2101/001 , B23K2103/14 , B23P6/005 , B23P15/006 , F01D5/30 , F01D5/3061 , F01D5/34 , F05B2230/239 , F05D2230/60 , F05D2230/80 , Y10T29/49321
摘要： A method for joining components, in particular for joining a rotor blade to a rotor base body in the manufacture and/or repair of an integrally bladed gas turbine rotor, is disclosed. The method includes the following steps: a) providing two components that are to be connected, i.e., joined together; b) providing a joining part; c) aligning the two components and the joining part that are to be joined together such that the joining part is arranged as an insert between the two components that are to be joined together; d) connecting the two components with the intermediate arrangement of the joining part by moving the joining part with respect to the two stationary components that are to be joined together and in particular by exerting a compression force on the joining zones between the two stationary components and the joining part via the two stationary components.
摘要翻译：公开了一种用于连接部件的方法，特别是用于在制造和/或修理整体叶片式燃气轮机转子时将转子叶片连接到转子基体上。该方法包括以下步骤：a）提供要连接的两个组件，即连接在一起; b）提供接合部分; c）将待接合在一起的两个部件和接合部件对准，使得接合部件被布置成两个待接合在一起的部件之间的插入件; d）通过使接合部分相对于要接合在一起的两个固定部件移动接合部分，特别是通过对两个固定部件之间的接合区域施加压缩力而将两个部件与接合部件的中间布置连接，以及通过两个固定部件连接部件。

62. 发明申请

US20090092494A1 DISK ROTOR AND METHOD OF MANUFACTURE 审中-公开
标题翻译：磁盘转子及其制造方法
公开(公告)号：US20090092494A1
公开(公告)日：2009-04-09
申请号：US11867346
申请日：2007-10-04
申请人： Ronald Ralph Cairo , Paul Stephen DiMascio
发明人： Ronald Ralph Cairo , Paul Stephen DiMascio
IPC分类号： F01D5/30
CPC分类号： F01D5/30 , F01D5/3061 , F01D5/34 , F05D2230/232 , F05D2230/25 , Y02T50/671
摘要： A disk rotor comprises a hub having a bore, and a plurality of spoke segments radially extending from the hub, each spoke segment including a base portion being attached to the hub and a rim portion, wherein the rim portion includes one or more airfoils integrally formed thereon, the plurality of spoke segments collectively forming a ring.
摘要翻译：盘转子包括具有孔的轮毂和从轮毂径向延伸的多个轮辐节段，每个轮辐节段包括附接到轮毂的基座部分和轮缘部分，其中轮缘部分包括一个或多个一体形成的翼面多个轮辐段共同形成环。

63. 发明申请

US20090068446A1 Layered structures with integral brazing materials 审中-公开
标题翻译：具有整体钎焊材料的分层结构
公开(公告)号：US20090068446A1
公开(公告)日：2009-03-12
申请号：US11799012
申请日：2007-04-30
申请人： Christopher J. Bischof , Michael J. Minor , Paul M. Pellet , Jason E. Huxol
发明人： Christopher J. Bischof , Michael J. Minor , Paul M. Pellet , Jason E. Huxol
IPC分类号： B32B15/00 , B21D53/78 , B32B5/00
CPC分类号： B23K1/0018 , B23K1/20 , B23K2101/001 , B23K2103/26 , F01D5/30 , Y10T29/49316 , Y10T29/49336 , Y10T428/265 , Y10T428/31678
摘要： A layered structure comprising a base structure having a major surface, and a brazing layer secured to the major surface of the base structure, where the brazing layer is applied to the major surface prior to positioning the layered structure in contact with a turbine engine component.
摘要翻译：一种层状结构，其包括具有主表面的基底结构和固定到基底结构的主表面的钎焊层，其中在将层状结构定位成与涡轮发动机部件接触之前，将钎焊层施加到主表面。

64. 发明授权

US07476083B2 Blade/disk dovetail backcut for blade/disk stress reduction (7FA+e, stage 1) 有权
标题翻译：用于刀片/盘片应力降低的刀片/盘燕尾背切（7FA + e，第1阶段）
公开(公告)号：US07476083B2
公开(公告)日：2009-01-13
申请号：US11476095
申请日：2006-06-28
申请人： Daniel David Snook , John Herbert Dimmick, III , Rachel Jane Obermeyer , Ariel Caesar Prepena Jacala , Robert Craig Akin
发明人： Daniel David Snook , John Herbert Dimmick, III , Rachel Jane Obermeyer , Ariel Caesar Prepena Jacala , Robert Craig Akin
IPC分类号： F01D5/30
CPC分类号： F01D5/30 , F05D2230/10
摘要： Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.
摘要翻译：可以转向燃气轮机盘上的叶片负载路径以提供显着的盘疲劳寿命益处。多个燃气轮机叶片可附接到燃气涡轮盘，其中每个燃气轮机叶片包括可接合在燃气涡轮盘中的相应形状的燕尾槽中的叶片燕尾榫。为了减少燃气轮机盘应力，根据叶片和/或盘几何形状来定义最佳材料去除面积，以最大化燃气轮机盘上的应力减小，燃气轮机叶片的使用寿命和维持或改进之间的平衡燃气轮机叶片的机械性能。从材料去除区域去除材料会最大化平衡。

65. 发明授权

US07458774B2 High pressure turbine disk hub with curved hub surface and method 有权
标题翻译：具有弯曲轮毂表面和方法的高压涡轮盘毂
公开(公告)号：US07458774B2
公开(公告)日：2008-12-02
申请号：US11306227
申请日：2005-12-20
申请人： Richard William Albrecht, Jr. , Craig William Higgins
发明人： Richard William Albrecht, Jr. , Craig William Higgins
IPC分类号： F01D5/02
CPC分类号： F01D5/00 , F01D5/02 , F01D5/06 , F01D5/08 , F01D5/30 , Y02T50/671 , Y02T50/676
摘要： A first stage turbine disk section for a gas turbine engine, including a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a convex, curved hub surface exposed to high pressure, high temperature compressor bleed and discharge gases during engine operation, and the convex, curved hub surface acts to reduce the axial constraint at the location of peak axial stress, thereby mitigating the formation of undesirable axial stress in the disk hub and allows separation of the peak axial and hoop stresses, thereby reducing the magnitude of the peak hub surface effective stress.
摘要翻译：用于燃气涡轮发动机的第一级涡轮盘部分，包括中心设置的盘毂，其具有终止于外端的一体形成的径向向外延伸的纤维网。盘毂具有在发动机运行期间暴露于高压，高温压缩机排气和放电气体的凸形弯曲毂表面，并且凸形弯曲毂表面用于减小在轴向应力峰值位置处的轴向约束，从而减轻在盘毂中形成不期望的轴向应力并允许峰值轴向和环向应力的分离，从而减小峰值毂表面有效应力的大小。

66. 发明申请

US20080273976A1 Variable rotor blade for gas turbine engine 有权
标题翻译：用于燃气轮机的可变转子叶片
公开(公告)号：US20080273976A1
公开(公告)日：2008-11-06
申请号：US11709013
申请日：2007-02-21
申请人： Gabriel L. Suciu , Craig A. Nordeen
发明人： Gabriel L. Suciu , Craig A. Nordeen
IPC分类号： F01D7/00
CPC分类号： F01D7/02 , F01D5/148 , F01D5/30 , F04D29/323 , F05D2220/36 , F05D2260/71 , F05D2260/74 , F05D2260/76 , F05D2260/79 , Y02T50/673 , Y10S416/05
摘要： A variable rotor blade mechanism for use in a gas turbine engine comprises a blade rotor, a blade, a harmonic drive system, a stepper motor and a bracket. The blade rotor rotates absolutely about an axial engine centerline during operation of the gas turbine engine. The blade extends radially from the blade rotor and is configured to be adjustable by rotation about a radial axis. The harmonic drive system is mounted to the blade rotor and connected to the blade to rotate the blade about the radial axis. The stepper motor drives the harmonic drive with relative rotational input with respect to the absolute rotation of the blade rotor. The bracket is disposed about the engine centerline and supports the stepper motor stationary with respect to the rotation of blade rotor such that the relative rotational input to the stepper motor is generated.
摘要翻译：用于燃气涡轮发动机的可变转子叶片机构包括叶片转子，叶片，谐波驱动系统，步进马达和支架。在燃气涡轮发动机的运行期间，叶片转子绝对围绕轴向发动机中心线旋转。叶片从叶片转子径向延伸并且构造成通过围绕径向轴线的旋转来调节。谐波驱动系统安装到叶片转子并连接到叶片以使叶片围绕径向轴线旋转。步进电机以相对于叶片转子的绝对转动的相对旋转输入驱动谐波驱动器。支架围绕发动机中心线设置，并且相对于叶片转子的旋转支撑步进马达固定，使得产生对步进马达的相对旋转输入。

67. 发明申请

US20080267784A1 Van Wheel of Turbine Comprising a Vane and at Least One Cooling Channel 有权
标题翻译：包括叶片和至少一个冷却通道的涡轮风轮
公开(公告)号：US20080267784A1
公开(公告)日：2008-10-30
申请号：US11632013
申请日：2005-06-13
申请人： Han-Thomas Bolms , Andreas Heselhaus , Roland Habel , Torsten Koch , Ralf Musgen
发明人： Han-Thomas Bolms , Andreas Heselhaus , Roland Habel , Torsten Koch , Ralf Musgen
IPC分类号： F01D5/18
CPC分类号： F01D5/30 , F01D5/081 , F01D25/12 , F05D2230/12 , F05D2240/127 , F05D2240/81 , F05D2250/291 , F05D2260/2212 , F05D2260/22141
摘要： There is described a vane wheel of a turbine comprising at least one vane, the footing thereof being held on a wheel disk. At least one cooling channel is arranged between the wheel disk and the vane footing. Said vane wheel having a plurality of turbulators is embodied on at least one of the walls of the cooling channel, said turbulators being configured in such a way that the turbulence and thus the heat transfer of a cooling fluid flowing through the cooling channel are increased.
摘要翻译：描述了一种涡轮机的叶轮，包括至少一个叶片，其叶片保持在轮盘上。至少一个冷却通道设置在轮盘和叶片基脚之间。具有多个紊流器的所述叶轮被实施在冷却通道的至少一个壁上，所述湍流器被构造成使得流过冷却通道的冷却流体的紊流和热传递增加。

68. 发明申请

US20080260534A1 BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (7FA+E, STAGE 1) 有权
标题翻译：刀片/碟片减速刀片（7FA + E，第1级）
公开(公告)号：US20080260534A1
公开(公告)日：2008-10-23
申请号：US11476095
申请日：2006-06-28
申请人： Daniel David Snook , John Herbert Dimmick , Rachel Jane Obermeyer , Ariel Caesar Prepena Jacala , Robert Craig Akin
发明人： Daniel David Snook , John Herbert Dimmick , Rachel Jane Obermeyer , Ariel Caesar Prepena Jacala , Robert Craig Akin
IPC分类号： F01D5/30
CPC分类号： F01D5/30 , F05D2230/10
摘要： Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.
摘要翻译：可以转向燃气轮机盘上的叶片负载路径以提供显着的盘疲劳寿命益处。多个燃气轮机叶片可附接到燃气涡轮盘，其中每个燃气轮机叶片包括可接合在燃气涡轮盘中的相应形状的燕尾槽中的叶片燕尾榫。为了减少燃气轮机盘应力，根据叶片和/或盘几何形状来定义最佳材料去除面积，以最大化燃气轮机盘上的应力减小，燃气轮机叶片的使用寿命和维持或改进之间的平衡燃气轮机叶片的机械性能。从材料去除区域去除材料会最大化平衡。

69. 发明申请

US20080057254A1 TURBINE ELEMENT REPAIR 审中-公开
标题翻译：涡轮机元件维修
公开(公告)号：US20080057254A1
公开(公告)日：2008-03-06
申请号：US11930564
申请日：2007-10-31
申请人： Robert Memmen , Igor Belousov , Anatoly Kuzmichev
发明人： Robert Memmen , Igor Belousov , Anatoly Kuzmichev
IPC分类号： B05C11/00 , B05C5/00 , B32B3/26
CPC分类号： B23P6/007 , C23C14/028 , C23C14/04 , C23C14/32 , F01D5/005 , F01D5/30 , F05D2230/30 , F05D2230/80 , Y10T29/49318 , Y10T29/49732 , Y10T428/20 , Y10T428/2495 , Y10T428/31504
摘要： Ion-enhanced physical vapor deposition is utilized to deposit repair material on Ti alloy turbine parts. Pulse modulation may be used to control a bias voltage and an ionization.
摘要翻译：利用离子增强物理气相沉积在Ti合金涡轮机零件上沉积修复材料。脉冲调制可用于控制偏置电压和电离。

70. 发明申请

US20080025843A1 Mounting disc 审中-公开
标题翻译：安装盘
公开(公告)号：US20080025843A1
公开(公告)日：2008-01-31
申请号：US11878878
申请日：2007-07-27
申请人： Philip Scope , Nicholas Bayley
发明人： Philip Scope , Nicholas Bayley
IPC分类号： F01D5/02
CPC分类号： F01D5/02 , F01D5/30 , F05D2250/711
摘要： Mounting discs (20, 30, 40, 50) are used in gas turbine engines to present turbine or compressor blades. These discs (20, 30, 40, 50) incorporate a bore or cob end 31, 41, 51 which in turn previously had a flat end face surface. Such flat end face surfaces are weight efficient but can lead to reduced component life and a limitation with regard to rotational speed due to Von-Mises stresses. By providing a deviation (39, 49, 59, 69) in the end face from a flat aspect, a reduction in axial stress is achieved with a marginal increase in hoop stress but with a net result that there is a reduction in the general operational Von-Mises stresses and therefore improvement in disc life or potential rotation speed capacity or both.
摘要翻译：安装盘（20,30,40,50）用于燃气涡轮发动机中以呈现涡轮或压缩机叶片。这些盘（20,30,40,50）包括一个孔或芯棒端部31,41,51，它们先前具有平坦的端面表面。这种平坦的端面表面具有重量效率，但是由于Von-Mises应力，可以减少部件寿命和对转速的限制。通过从平坦的方面在端面提供偏差（39,49,59,69），在环向应力稍微增加的同时实现轴向应力的减小，但是总体操作有所减少 Von-Mises压力因此提高了光盘寿命或潜在的转速能力或两者兼而有之。

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