公开(公告)号：US5314304A

公开(公告)日：1994-05-24

申请号：US745630

申请日：1991-08-15

申请人： David J. Wiebe

发明人： David J. Wiebe

IPC分类号： F01D11/12 ,  F01D11/08

CPC分类号： F01D11/127 ,  F01D11/122 ,  Y10T428/1234 ,  Y10T428/12611

摘要： In a gas turbine engine having a laybrinth seal between an annular rotor and stator therein, in which the stator is surmounted by a honeycomb structure and the rotor has a knife edge which is mounted to rotate in close annular proximity with said honeycomb structure, an improvement is provided wherein such labyrinth seal has a layer of abradeable coating atop the honeycomb structure for the rotor knife edge to rotate proximate thereto and to rub in, without substantially damaging the knife edge nor the honeycomb structure. In one embodiment the layer of abradeable coating is mounted on a metalic foil which is mounted in turn, atop the honeycomb structure. The abradeable coating thus provided, is more yieldable and less damaging to a rotor knife edge than is the honeycomb structure of the prior art, to better preserve rotor and stator and thus the labryrinth seal. Because of such protection, the rotor knife edge can be thinner and of lighter weight and the honeycomb structure can be made of larger cell sizes, again resulting in weight savings for each lab seal, which can have one or a plurality of rotor (knife edge)-stator pairs. Further, the abradable coating seals the top of the honeycomb structure and thus blocks air flow into the honeycomb cells beneath and behind the knife edge and thus reduces losses in seal efficiency.

摘要翻译： 在具有在其中的环形转子和定子之间具有底孔密封的燃气涡轮发动机中，其中定子被蜂窝结构覆盖，并且转子具有安装成与所述蜂窝结构紧密环接地旋转的刀刃，改进 其中这种迷宫式密封件具有在蜂窝状结构顶部的可磨蚀涂层，用于转子刀刃在其附近旋转并摩擦，而基本上不损坏刀刃和蜂窝结构。 在一个实施方案中，可磨蚀涂层是安装在依次安装在蜂窝结构顶上的金属箔上的。 如此提供的可磨损涂层比现有技术的蜂窝结构更可屈服并且对转子刀刃的损伤较小，以更好地保持转子和定子，从而更好地保持了实验室密封。 由于这样的保护，转子刀刃可以更薄和更轻的重量，并且蜂窝结构可以由更大的电池尺寸制成，这再次导致每个实验室密封件的重量节省，其可以具有一个或多个转子（刀刃 ）-stator对。 此外，可磨损涂层密封蜂窝结构体的顶部，从而阻挡在刀刃下方和后方的进入蜂窝状电池的空气流，从而减少密封效率的损失。

公开(公告)号：US09399926B2

公开(公告)日：2016-07-26

申请号：US13974147

申请日：2013-08-23

申请人： David J. Wiebe

发明人： David J. Wiebe

IPC分类号： F01D11/08 ,  F01D5/06 ,  F01D11/00 ,  F02C7/28

CPC分类号： F01D11/08 ,  F01D5/06 ,  F01D5/066 ,  F01D11/003 ,  F01D11/005 ,  F01D11/008 ,  F02C7/28

摘要： A circumferentially extending sealing band is located within sealing band receiving slots formed in adjacent turbine engine disks. The sealing band includes a plurality of seal strips forming overlap joints defined by overlapping end portions, each formed by a tongue portion extending from a seal face of one seal strip past a seal face of the adjacent seal strip, along a radially inward facing side of the adjacent seal strip. A joint gap is defined within at least one overlap joint between the seal face of the one seal strip and the seal face of the adjacent strip, and a spacer is affixed to the one seal strip and is located at a position within the joint gap between the seal faces to limit circumferential movement of the seal faces toward each other.

摘要翻译： 周向延伸的密封带位于形成在相邻的涡轮引擎盘中的密封带接收槽内。 密封带包括形成由重叠端部限定的重叠接头的多个密封条，每个密封条由从一个密封条的密封面延伸穿过相邻密封条的密封面的舌部形成，该舌部沿着径向向内的侧面 相邻密封条。 在一个密封条的密封面和相邻条的密封面之间的至少一个重叠接合部内限定了接合间隙，并且间隔件固定到一个密封条上，并且位于第一密封条之间的接合间隙内的位置 密封面面对以限制密封面朝向彼此的周向移动。

公开(公告)号：US09267689B2

公开(公告)日：2016-02-23

申请号：US13783857

申请日：2013-03-04

申请人： David J. Wiebe ,  Stephen A. Ramier ,  Robert H. Bartley ,  Daniel W. Garan ,  Erick J. Deane ,  Mark L. Adamson ,  Yadollah Naghian

发明人： David J. Wiebe ,  Stephen A. Ramier ,  Robert H. Bartley ,  Daniel W. Garan ,  Erick J. Deane ,  Mark L. Adamson ,  Yadollah Naghian

IPC分类号： F23R3/28 ,  F02C7/22 ,  F16L13/007 ,  F23R3/34 ,  F16L41/08

CPC分类号： F23R3/28 ,  F02C7/22 ,  F02C7/222 ,  F05D2300/50211 ,  F05D2300/50212 ,  F05D2300/506 ,  F16L13/007 ,  F16L15/006 ,  F16L19/061 ,  F16L25/0072 ,  F16L41/084 ,  F16L41/086 ,  F23K2301/20 ,  F23R3/283 ,  F23R3/286 ,  F23R3/34 ,  F23R2900/00005

摘要： A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall.

摘要翻译： 燃烧器装置限定了燃烧区域，其中空气和燃料被燃烧以产生高温燃烧产物。 燃烧器装置包括外壁，与其燃料入口相邻的外壁上的联接结构，燃料喷射系统，燃料供给组件和配件构件。 燃料喷射系统提供在燃烧区域燃烧的燃料。 燃料供给结构包括由第一材料形成的螺纹内表面。 所述燃料供给组件包括燃料供给管，所述燃料供给管延伸穿过所述外壁中的所述燃料入口，并且具有由所述第一材料形成并与所述燃料供给结构螺纹接合的出口部，以及固定到所述出口部的入口部 并由第二材料形成。 装配构件相对于外壁固定燃料供给组件。

公开(公告)号：US20150107264A1

公开(公告)日：2015-04-23

申请号：US14059521

申请日：2013-10-22

申请人： David J. Wiebe ,  Richard C. Charron ,  Jay A. Morrison

发明人： David J. Wiebe ,  Richard C. Charron ,  Jay A. Morrison

IPC分类号： F23R3/60 ,  F01D9/02

CPC分类号： F23R3/60 ,  F01D9/023 ,  F05D2260/30 ,  F23R3/46

摘要： A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.

摘要翻译： 一种燃气涡轮发动机管道装置（10），包括：环形室（14），其构造成容纳来自相应罐式燃烧器的多个不连续的燃烧气体流并且将离散流输送到涡轮机入口环，其中环形室 包括内径（52）和外径（60）; 外径安装装置（34）被构造成允许相对径向移动并且防止外径与涡轮叶片载体（20）之间的相对轴向和周向移动; 以及内径安装装置（36），其包括固定到所述涡轮机叶片承载件的支架（64），其中所述支架构造成允许所述内径径向与所述外径径向移动，并且防止所述内径相对于 外径。

公开(公告)号：US20140205447A1

公开(公告)日：2014-07-24

申请号：US13746486

申请日：2013-01-22

申请人： Harry Patat ,  Cheryl A. Schopf ,  Jerome H. Katy ,  Adam Wallace ,  David J. Wiebe

发明人： Harry Patat ,  Cheryl A. Schopf ,  Jerome H. Katy ,  Adam Wallace ,  David J. Wiebe

IPC分类号： F02C7/18 ,  F01D25/16 ,  F02C6/08

CPC分类号： F02C7/18 ,  F01D9/02 ,  F01D9/065 ,  F01D25/12 ,  F01D25/125 ,  F01D25/162 ,  F01D25/30 ,  F02C6/08 ,  F05D2240/15

摘要： A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.

摘要翻译： 具有外壳，内壳，限定在外流路壁和内流路壁之间的环形排气通道的涡轮机排气外壳以及从气体路径径向向外和径向向内定位的涡轮排气壳体腔。 多个结构支柱将内壳支撑到外壳，并且整流罩围绕在外流路壁和内流路壁之间延伸的区域中的每个支柱。 第一吹扫空气路径延伸穿过支柱中的至少一个，用于将吹扫冷却空气径向向内引导到内部壳体，并且第二吹扫空气路径延伸穿过支柱，以进一步将吹扫冷却空气径向向外引导以提供吹扫流 空气从外部流路壁向径向外侧排出到排气套管腔的位置。

公开(公告)号：US20130084163A1

公开(公告)日：2013-04-04

申请号：US13252429

申请日：2011-10-04

申请人： David J. Wiebe

发明人： David J. Wiebe

IPC分类号： F01D25/00

CPC分类号： F16D66/02 ,  F01D11/02 ,  F04D27/001 ,  F04D29/542 ,  F05D2260/83

摘要： A wear indication system for use in turbine engines to measure gap closure that indicates the amount of wear found on a compressor diaphragm outer hook to prevent contact between a compressor vane attached to the compressor diaphragm outer hook and an upstream compressor blade. The wear indication system enables the wear to be serviced before failure occurs. The wear indication system may be formed from a base mounting plate having one or more wearable material layers attached thereto. In one embodiment, the wear indication system may have multiple wearable material layers. The outermost wearable layer may have a cross-sectional area less than a wearable layer to which it is attached to enable visual determination of the amount of wear that has occurred. The wearable layers may be formed from a honeycomb shaped material enabling wear to occur without threatening downstream components with damage.

摘要翻译： 一种用于涡轮发动机的磨损指示系统，用于测量间隙闭合，其指示在压缩机隔膜外钩上发现的磨损量，以防止附接到压缩机隔膜外钩的压缩机叶片与上游压缩机叶片之间的接触。 磨损指示系统使磨损在发生故障之前得到维护。 磨损指示系统可以由具有附接到其上的一个或多个可穿戴材料层的基座安装板形成。 在一个实施例中，磨损指示系统可以具有多个可穿戴材料层。 最外面的可佩戴层可以具有小于其所连接的可佩戴层的横截面面积，以使得能够可视地确定所发生的磨损量。 可穿戴层可以由蜂窝状材料形成，从而能够在不损害下游部件的情况下发生磨损。

公开(公告)号：US20120275918A1

公开(公告)日：2012-11-01

申请号：US13096051

申请日：2011-04-28

申请人： David J. Wiebe

发明人： David J. Wiebe

IPC分类号： F01D5/32

CPC分类号： F01D5/3038 ,  F01D5/32 ,  F01D5/323

摘要： A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from radially inward and outward supports coupled together with a locking device. The inward and outward supports establish the desired spacing between adjacent blade supports. The locking device may include components that prevent the locking device from accidentally loosening during use.

摘要翻译： 一种用于填充涡轮发动机中的相邻部件之间的空隙的锁定间隔件组件。 在至少一个实施例中，锁定间隔件组件可构造成在涡轮叶片级组件中的盘槽中插入相邻的涡轮叶片之间。 锁定间隔件组件可以由与锁定装置联接在一起的径向向内和向外的支撑件形成。 向内和向外的支撑件在相邻的叶片支撑件之间建立所需的间隔。 锁定装置可以包括防止锁定装置在使用期间意外松动的部件。

公开(公告)号：US20110217179A1

公开(公告)日：2011-09-08

申请号：US12716548

申请日：2010-03-03

申请人： David J. Wiebe

发明人： David J. Wiebe

IPC分类号： F01D5/18

CPC分类号： F01D5/18

摘要： A cooling system for the fillet of a turbine blade is provided. The blade includes an airfoil transitioning to a platform having a flow path surface. The transition region is defined by a fillet. A cooling passage is formed in the platform and extends about at least a portion of the periphery of the airfoil. The cooling passage is located proximate to the flow path surface and is substantially aligned with at least a portion of the fillet. Coolant is delivered to the passage by a supply hole, which can reduce the temperature in the fillet region. As a result, thermal gradients in the fillet region can be minimized, which can reduce thermal stresses. An exhaust hole extends between the passage and the flow path surface of the platform. Thus, coolant discharged from the exhaust holes enters the flow path of the turbine.

摘要翻译： 提供了一种用于涡轮叶片的圆角的冷却系统。 叶片包括转变到具有流动路径表面的平台的翼型件。 过渡区域由圆角定义。 冷却通道形成在平台中并围绕翼型的周边的至少一部分延伸。 冷却通道位于流路表面附近，并且基本上与圆角的至少一部分对齐。 冷却液通过供应孔输送到通道，这可以降低圆角区域的温度。 因此，可以最小化圆角区域的热梯度，这可以降低热应力。 排气孔在平台的通道和流动通道表面之间延伸。 因此，从排气孔排出的冷却剂进入涡轮机的流路。

公开(公告)号：US20090214349A1

公开(公告)日：2009-08-27

申请号：US12035495

申请日：2008-02-22

申请人： David J. Wiebe ,  John W. Finneran ,  Jeffery W. Samuelson ,  Richard C. Charron

发明人： David J. Wiebe ,  John W. Finneran ,  Jeffery W. Samuelson ,  Richard C. Charron

IPC分类号： F01D5/32

CPC分类号： F01D5/3038 ,  F05D2260/30

摘要： An airfoil structure, shim and retention member combination is provided. The combination comprises an airfoil structure, a retention member and a shim. The airfoil structure may comprise a first recess. The retention member may comprising a second recess. The first and second recesses may define a cavity. The shim may comprise a main body and a plurality of first fins extending outwardly from a first side of the main body. The first fins may further extend transverse to a longitudinal axis of the main body. The shim may be positioned in the cavity such that the first fins extend in a direction substantially transverse to a longitudinal axis of the cavity.

摘要翻译： 提供翼型结构，垫片和保持构件组合。 该组合包括翼型结构，保持构件和垫片。 翼型结构可以包括第一凹部。 保持构件可以包括第二凹部。 第一和第二凹部可以限定空腔。 垫片可以包括主体和从主体的第一侧向外延伸的多个第一翅片。 第一散热片可以进一步横向于主体的纵向轴线延伸。 垫片可以定位在空腔中，使得第一翅片沿着基本上横向于腔的纵向轴线的方向延伸。

公开(公告)号：US5803710A

公开(公告)日：1998-09-08

申请号：US772838

申请日：1996-12-24

申请人： Douglas J. Dietrich ,  Alan W. Stoner ,  David J. Wiebe

发明人： Douglas J. Dietrich ,  Alan W. Stoner ,  David J. Wiebe

IPC分类号： F01D5/22 ,  F01D11/00 ,  F04D29/08 ,  F04D29/34 ,  F04D29/66

CPC分类号： F01D11/006 ,  F01D5/22 ,  F04D29/083 ,  F04D29/34 ,  F04D29/668 ,  Y10S416/50

摘要： A device for sealing between and damping of adjacent rotor blade platforms is provided which includes a forward seal member, a compliant center seal member, an aft seal member, a first damper, and a second damper. The first damper is disposed between the forward and compliant center seal members, and the second damper is disposed between the compliant center and aft seal members. The compliant center seal member is disposed between the first and second dampers. The compliant center seal member accommodates misalignment between adjacent rotor blade platforms by deflecting in response to centrifugal forces acting on the dampers.

摘要翻译： 提供了一种用于相邻转子叶片平台之间的密封和阻尼的装置，其包括前密封构件，顺应中心密封构件，后密封构件，第一阻尼器和第二阻尼器。 第一阻尼器设置在正向和顺应性中心密封构件之间，并且第二阻尼器设置在顺应性中心和后部密封构件之间。 柔性中心密封构件设置在第一和第二阻尼器之间。 柔性中心密封构件通过响应于作用在阻尼器上的离心力而偏转而适应相邻转子叶片平台之间的不对准。