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1. 发明授权

US6095750A Turbine nozzle assembly 失效
标题翻译：涡轮喷嘴总成
公开(公告)号：US6095750A
公开(公告)日：2000-08-01
申请号：US217660
申请日：1998-12-21
申请人： Steven A. Ross , Robert J. Albers , Edward P. Brill , Andrew D. Kemp , Larry W. Plemmons
发明人： Steven A. Ross , Robert J. Albers , Edward P. Brill , Andrew D. Kemp , Larry W. Plemmons
IPC分类号： F01D9/04
CPC分类号： F01D9/042
摘要： A turbine nozzle assembly includes a plurality of nozzle segments and a nozzle support for supporting the nozzle segments. Each nozzle segment includes an outer band, an inner band and at least two vanes disposed between the outer and inner bands. A retention flange extends radially inwardly from the inner band and has a first hole formed therein. The nozzle support includes a recess formed therein and a mounting flange extending therefrom. The mounting flange is disposed in contact with the retention flange and has a second hole formed therein. A pin is disposed in the first and second holes to position the flanges with respect to one another. A pin retainer is disposed in the recess and has a holding flange for retaining the pin in place. The nozzle support includes a substantially conical portion and an air seal integrally formed thereto.
摘要翻译：涡轮喷嘴组件包括多个喷嘴段和用于支撑喷嘴段的喷嘴支撑件。每个喷嘴段包括外带，内带和设置在外带和内带之间的至少两个叶片。保持凸缘从内带径向向内延伸并且具有形成在其中的第一孔。喷嘴支撑件包括形成在其中的凹部和从其延伸的安装凸缘。安装凸缘设置成与保持凸缘接触并且具有形成在其中的第二孔。销设置在第一和第二孔中以相对于彼此定位凸缘。销保持器设置在凹部中并且具有用于将销保持在适当位置的保持凸缘。喷嘴支撑件包括基本上圆锥形的部分和与其一体形成的空气密封件。

2. 发明授权

US5984630A Reduced windage high pressure turbine forward outer seal 失效
标题翻译：降低风挡高压汽轮机正向外密封
公开(公告)号：US5984630A
公开(公告)日：1999-11-16
申请号：US997833
申请日：1997-12-24
申请人： David A. Di Salle , Robert Proctor , Edward P. Brill , Steven A. Ross , Robert J. Albers , John C. Brauer , Gulcharan S. Brainch , Dean T. Lenahan
发明人： David A. Di Salle , Robert Proctor , Edward P. Brill , Steven A. Ross , Robert J. Albers , John C. Brauer , Gulcharan S. Brainch , Dean T. Lenahan
IPC分类号： F01D5/08 , F01D11/02 , F01D11/04 , F02C7/18 , F03B11/00
CPC分类号： F01D11/02 , F01D11/04
摘要： A blocker and swirl inducer hole configuration for use in connection with a high pressure turbine is described. In one embodiment, the blocker holes are oriented to a 45-degree tangential angle with respect to the direction of rotation of the seal, which results in pre-swirling the air before being injected into the swirl cavity. In addition, the number of blocker holes is reduced by as much as 50% of the number of blocker holes used in the known CFM56 turbine. Further, rather than injecting the air into the first swirl cavity as is known, the air is injected into a second swirl cavity. The combined effect of orienting the holes to the 45-degree tangential angle with respect to the direction of rotation of the seal, locating the holes to open into the second swirl cavity, and reducing the flow area by about 50%, results in an increase in blocker hole pressure ratio. Increasing the blocker hole pressure ratio results in a higher hole exit velocity which maximizes the cavity inlet swirl. The blocker holes therefore not only provide back-pressure, but also function as swirl-inducers. By inducing swirl into the air injected into the second swirl cavity, better turbine disk rim cooling effectiveness is provided. This result facilitates maintaining reasonable metal temperatures at increasingly severe cycle conditions without the normally expected engine performance penalties.
摘要翻译：描述了与高压涡轮机相关联使用的阻塞器和涡流诱导器孔构造。在一个实施例中，阻挡孔相对于密封件的旋转方向被定向成45度的切向角，这导致在注入到涡流腔内之前预先旋转空气。此外，阻塞孔的数量减少了已知CFM56涡轮机中使用的阻塞孔数量的多达50％。此外，如已知的那样，不是将空气注入到第一涡流腔中，所以空气被注入到第二涡流腔中。相对于密封件的旋转方向将孔定向到45度切向角的组合效果，将孔定位到第二涡流腔中，并将流动面积减少约50％，导致增加阻塞孔压力比。增加阻塞孔压力比导致更高的孔出口速度，这使空腔入口涡流最大化。因此，阻挡孔不仅提供背压，而且还起到旋流诱发器的作用。通过在注入到第二涡流腔中的空气中引起漩涡，提供更好的涡轮盘边缘冷却效果。该结果有助于在越来越严格的循环条件下保持合理的金属温度，而不会发生通常预期的发动机性能

3. 发明授权

US5169287A Shroud cooling assembly for gas turbine engine 失效
标题翻译：天然气发动机冷却组件
公开(公告)号：US5169287A
公开(公告)日：1992-12-08
申请号：US702549
申请日：1991-05-20
申请人： Robert Proctor , Larry W. Plemmons , Gulcharan S. Brainch , John R. Hess , Robert J. Albers
发明人： Robert Proctor , Larry W. Plemmons , Gulcharan S. Brainch , John R. Hess , Robert J. Albers
IPC分类号： F01D5/18 , F01D11/08 , F01D25/12 , F02C7/18
CPC分类号： F01D11/08 , F01D25/12 , F01D5/182 , F05D2260/201 , F05D2260/202
摘要： To cool the shroud in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow to baffle plenums and thence through baffle perforations to impingement cool the shroud rails and back surface. Impingement cooling air then flows through elongated, convection cooling passages in the shroud and exits to flow along the shroud front surface with the main gas stream to provide film cooling. The baffle perforations and the convection cooling passages are interactively located to achieve maximum cooling benefit and highly efficient cooling air utilization.

4. 发明授权

US5205115A Gas turbine engine case counterflow thermal control 失效
标题翻译：气体涡轮发动机箱流量控制
公开(公告)号：US5205115A
公开(公告)日：1993-04-27
申请号：US787498
申请日：1991-11-04
申请人： Larry W. Plemmons , Robert Proctor , Robert J. Albers , Donald L. Gardner
发明人： Larry W. Plemmons , Robert Proctor , Robert J. Albers , Donald L. Gardner
IPC分类号： F02C7/18 , F01D11/10 , F01D11/24 , F02C7/28 , F02C9/18
CPC分类号： F01D11/24
摘要： A thermal control apparatus is provided for gas turbine engine cases and particularly for thermal control of clearances between turbine rotors and surrounding shrouds. Thermal control of an annular case section or ring is provided by counterflowing two heat transfer fluid flowpaths in heat transfer communication with the section of engine casing. The flowpaths may be in parallel or series such that there is substantially no circumferential gradient in the mass flowrate weighted average temperature of the heat transfer fluid supplied by the two counterflowing fluid flowpaths. One embodiment provides forward and aft rings cooled by three spray tubes in each of two 180.degree. sectors whereby the forward and aft spray tubes flow thermal control air flowing in one circumferential direction and the middle spray tubes flows thermal control air in an opposite circumferential direction.

5. 发明授权

US5735671A Shielded turbine rotor 失效
标题翻译：屏蔽涡轮转子
公开(公告)号：US5735671A
公开(公告)日：1998-04-07
申请号：US759093
申请日：1996-11-29
申请人： John C. Brauer , David A. Di Salle , Edward P. Brill , Robert J. Albers , Dean T. Lenahan
发明人： John C. Brauer , David A. Di Salle , Edward P. Brill , Robert J. Albers , Dean T. Lenahan
IPC分类号： F01D5/08 , F01D5/28 , F01D5/30 , F01D11/00 , F01D25/00
CPC分类号： F01D11/008 , F01D5/081 , F01D5/288 , F05D2230/90 , F05D2260/231 , Y02T50/67 , Y02T50/673 , Y02T50/676
摘要： A turbine rotor includes a rotor disk having a plurality of dovetail slots defining therebetween respective disk posts. Each post has a top land and a plurality of tangs spaced radially therebelow inside adjacent ones of the slots. A plurality of turbine blades each having a dovetail are mounted in respective ones of the dovetail slots for radially retaining the blades. A platform is joined integrally with the dovetail and extends circumferentially to adjoin adjacent ones of the platforms to define a radially inner flowpath. An airfoil extends integrally from the platform for extracting energy from combustion gases flowable thereover. A thermal barrier coating is fixedly bonded to each of the disk post top lands for providing thermal insulation between the platforms and the disk posts for reducing disk post temperature.
摘要翻译：涡轮转子包括具有多个燕尾槽的转子盘，所述燕尾槽在其间限定各自的盘柱。每个柱具有顶部区域和在其中相邻的狭槽内部沿径向放置的多个柄脚。每个具有燕尾榫的多个涡轮叶片安装在各个燕尾槽中，用于径向保持叶片。平台与燕尾榫整体连接并且周向地延伸以邻接相邻的平台以限定径向内部的流动路径。机翼从平台一体地延伸，用于从其中可流动的燃烧气体提取能量。隔热涂层固定地粘合到每个盘柱顶部焊盘上，以在平台和盘柱之间提供热绝缘，以减少磁盘后端温度。

6. 发明授权

US5970716A Apparatus for retaining centerbody between adjacent domes of multiple annular combustor employing interference and clamping fits 失效
标题翻译：用于在多个环形燃烧器的相邻圆顶之间保持中心体的装置，其采用干涉和夹紧配合
公开(公告)号：US5970716A
公开(公告)日：1999-10-26
申请号：US942741
申请日：1997-10-02
申请人： James M. Forrester , Gregory A. Cimmarusti , David B. Legger , James N. Cooper , Robert J. Albers
发明人： James M. Forrester , Gregory A. Cimmarusti , David B. Legger , James N. Cooper , Robert J. Albers
IPC分类号： F23R3/28 , F23R3/10 , F23R3/42 , F23R3/46 , F23R3/50 , F23R3/60
CPC分类号： F23R3/60 , F23R3/10 , F23R3/50
摘要： A double annular combustor having concentrically disposed inner and outer annular combustors including an inner dome having an inner portion and an outer portion, an outer dome having an inner portion and an outer portion, wherein the outer dome inner portion is connected to the inner dome outer portion, and a substantially annular centerbody disposed between the inner dome and the outer dome. The centerbody includes a plurality of structurally independent arcuate segments, wherein each centerbody segment is retained in position via an interference fit between a first flange of such centerbody extending downstream and a hook in the inner dome outer portion and/or via a clamping fit of a second flange of the centerbody extending upstream to a flange of the inner dome outer portion.
摘要翻译：一种具有同心配置的内外环形燃烧器的双环形燃烧器，包括具有内部和外部的内圆顶，具有内部和外部的外圆顶，其中外圆顶内部连接到内圆顶外并且设置在内圆顶和外圆顶之间的大致环形的中心体。中心体包括多个结构上独立的弧形段，其中每个中心体段通过在下游延伸的这种中心体的第一凸缘与内圆顶外部部分中的钩和/或经由夹紧配合之间的过盈配合保持在适当位置中心体的第二凸缘在内拱顶外部的凸缘的上游延伸。

7. 发明授权

US06758477B2 Aspirating face seal with axially biasing one piece annular spring 有权
标题翻译：吸气面密封，轴向偏置一片环形弹簧
公开(公告)号：US06758477B2
公开(公告)日：2004-07-06
申请号：US10106759
申请日：2002-03-26
申请人： John C. Brauer , Robert J. Albers
发明人： John C. Brauer , Robert J. Albers
IPC分类号： F01D1102
CPC分类号： F16J15/164 , F01D11/02 , F05D2240/55 , F05D2240/70 , F16J15/3452 , F16J15/4476
摘要： A gas turbine engine aspirating face seal includes rotatable and non-rotatable engine members and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces are operably associated with the rotatable and non-rotatable engine members respectively and are circumscribed about and generally perpendicular to a centerline axis. A substantially fully annular pull off biasing element is operably disposed for urging the non-rotatable gas bearing face surface axially away from the rotatable gas bearing face surface and circumscribed about the centerline axis. The pull off biasing element may be at least one wave spring or one bellville washer. The non-rotatable gas bearing face surface may be on a face seal ring mounted on a translatable cylindrical piston which is axially movable and supported by the non-rotatable engine member.
摘要翻译：燃气涡轮发动机抽吸面密封件包括可旋转和不可旋转的发动机构件和它们之间的泄漏路径。环形大体上平面的可旋转和不可旋转的气体支承面表面分别可操作地与可旋转和不可旋转的发动机构件相关联，并且围绕中心线轴线并且大致垂直于中心线轴线。可操作地设置基本上完全环形的拉脱偏置元件，以便使不可旋转的气体支承面表面轴向地远离可旋转的气体支承面表面并围绕中心线轴线限定。拉脱偏置元件可以是至少一个波形弹簧或一个贝尔维尔洗衣机。不可旋转的气体支承面表面可以在安装在可平移的圆柱形活塞上的面密封环上，其可轴向移动并由不可旋转的发动机构件支撑。

8. 发明授权

US06644668B1 Brush seal support 有权
标题翻译：刷密封支持
公开(公告)号：US06644668B1
公开(公告)日：2003-11-11
申请号：US10170163
申请日：2002-06-13
申请人： Robert J. Albers , Randall C. Bauer , John C. Brauer , Scott Joseph Schmid , Kenneth M. Lewis
发明人： Robert J. Albers , Randall C. Bauer , John C. Brauer , Scott Joseph Schmid , Kenneth M. Lewis
IPC分类号： F16J1544
CPC分类号： F01D11/001 , F05D2240/56 , F16J15/3288 , Y02T50/671
摘要： A support arrangement for a brush seal positioned between a stationary and a rotatable component of a turbomachine. The brush seal has a downstream backing plate that includes an axially-extending lip adjacent its radially outermost end to minimize axial deflection of the seal as a result of a gas pressure differential acting across the seal.
摘要翻译：用于刷密封件的支撑装置，其位于涡轮机的固定部件和可旋转部件之间。刷密封具有下游背板，其包括邻近其径向最外端的轴向延伸的唇缘，以最小化作用在密封件上的气体压力差导致的密封件的轴向偏转。

9. 发明授权

US07487280B2 Enabling ports on a module received in a slot in a chassis 有权
标题翻译：启用在机箱中插槽中接收的模块上的端口
公开(公告)号：US07487280B2
公开(公告)日：2009-02-03
申请号：US11432912
申请日：2006-05-12
申请人： Edoardo Campini , Douglas P. Bogia , Robert J. Albers
发明人： Edoardo Campini , Douglas P. Bogia , Robert J. Albers
IPC分类号： G06F13/00
CPC分类号： G06F13/409 , H05K7/1459
摘要： Information is obtained from a module received in a slot in a chassis. The information includes a number of ports in one or more module connectors which route at least one communication channel associated with a communication interfaces on the module. A determination is made as to the number of ports the slot has a capability to route the at least one communication channel to one or more backplanes in the chassis and to another module received in another slot in the chassis. A given number of ports in the one or more module connectors are enabled to forward data from the communication interface on the module and through the at least one communication channel to the other module based on the determination.
摘要翻译：信息从在机箱中的插槽中接收的模块获得。该信息包括在一个或多个模块连接器中的多个端口，其中路由至少一个与模块上的通信接口相关联的通信信道。确定插槽具有将至少一个通信信道路由到机箱中的一个或多个背板的能力的端口数量以及在机箱中的另一个时隙中接收的另一个模块的端口数量。一个或多个模块连接器中的给定数量的端口能够基于该确定将来自模块上的通信接口的数据和通过至少一个通信信道转发到另一个模块。

10. 发明授权

US07458815B2 Module to couple to a plurality of backplanes in a chassis 有权
标题翻译：模块耦合到机箱中的多个背板
公开(公告)号：US07458815B2
公开(公告)日：2008-12-02
申请号：US11393389
申请日：2006-03-30
申请人： Hassan Fallah-Adl , Edoardo Campini , Robert J. Albers
发明人： Hassan Fallah-Adl , Edoardo Campini , Robert J. Albers
IPC分类号： H01R12/00
CPC分类号： H05K7/1451
摘要： A chassis includes a plurality of slots to receive modules. The chassis further includes a first backplane to couple to modules that are received in the plurality of slots. The modules are to couple to the first backplane via a first communication interface on each module. The chassis also includes a second backplane to couple to at least a subset of the modules via a second communication interface on each of the subset of modules. One of the backplanes may be located in an upper or lower air plenum and used to interconnect modules slid along the slots from opposite directions. Some of the module connectors may be retractable to enable the modules to move into the chassis. The interface may be electrical, optical inductive or capacitive.
摘要翻译：底盘包括多个槽以接收模块。底盘还包括耦合到在多个槽中接收的模块的第一背板。模块将通过每个模块上的第一个通信接口耦合到第一个背板。机箱还包括第二背板，以通过模块子集中的每一个上的第二通信接口耦合到模块的至少一个子集。背板中的一个可以位于上或下空气通风室中，并且用于将沿着槽从相反方向滑动的模块互连。一些模块连接器可以是可缩回的，以使得模块能够移动到底盘中。接口可以是电的，光学的或电容的。

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