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1. 发明授权

US07353647B2 Methods and apparatus for assembling gas turbine engines 有权
标题翻译：燃气轮机发动机组装方法及装置
公开(公告)号：US07353647B2
公开(公告)日：2008-04-08
申请号：US10845032
申请日：2004-05-13
申请人： Robert Joseph Orlando , Thomas Ory Moniz , John C. Brauer , John Leslie Henry , Raymond Felix Patt , Randy Marinus Vondrell , James Patrick Dolan , Erich Alois Krammer , David Cory Kirk
发明人： Robert Joseph Orlando , Thomas Ory Moniz , John C. Brauer , John Leslie Henry , Raymond Felix Patt , Randy Marinus Vondrell , James Patrick Dolan , Erich Alois Krammer , David Cory Kirk
IPC分类号： F02C3/04 , F02K3/04
CPC分类号： F02C3/13 , F02C3/04 , F05D2230/60
摘要： A method facilitates assembling a gas turbine engine including a compressor and a rotor assembly coupled in axial flow communication downstream from the compressor. The method comprises coupling a bypass system in flow communication with the compressor to channel a portion of flow discharged from the compressor towards the rotor assembly is channeled through the bypass system, and coupling a downstream end of the bypass system within the gas turbine engine such that the flow entering the bypass system flows past the rotor assembly and is discharged downstream from the rotor assembly.
摘要翻译：一种方法有利于组装燃气涡轮发动机，该燃气涡轮发动机包括压缩机和在压缩机下游的轴向流动连通中联接的转子组件。该方法包括将与压缩机流体连通的旁路系统联接以将从压缩机排出的一部分流向转子组件引导通过旁路系统，并将旁路系统的下游端连接在燃气涡轮发动机内，使得进入旁路系统的流量流过转子组件，并从转子组件的下游排出。

2. 发明授权

US06732502B2 Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor 有权
标题翻译：具有高整体压力比压缩机的反转式飞机燃气轮机
公开(公告)号：US06732502B2
公开(公告)日：2004-05-11
申请号：US10087428
申请日：2002-03-01
申请人： Jorge F. Seda , Lawrence W. Dunbar , Peter N. Szucs , John C. Brauer , James E. Johnson
发明人： Jorge F. Seda , Lawrence W. Dunbar , Peter N. Szucs , John C. Brauer , James E. Johnson
IPC分类号： F02K304
CPC分类号： F04D19/024 , F01D5/03 , F02K3/072 , F05D2240/12 , F05D2250/52 , Y02T50/672 , Y02T50/673
摘要： An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part rotatably disposed co-axially within a high pressure rotor and drivingly connected to first and second fan blade rows and first and second boosters respectively. A bypass duct radially bounded by a fan casing and an annular radially inner bypass duct wall surrounds the boosters axially located between the first and second fan blade rows. The engine has a high pressure compressor operable to produce an overall pressure ratio in a range of about 40-65 and a fan inlet hub to tip radius ratio in a range between 0.20 and 0.35, a bypass ratio in a range of 5-15, an operational fan pressure ratio in a range of 1.4-2.5, and a sum of operational fan tip speeds in a range of 1000 to 2500 feet per second.
摘要翻译：飞机燃气涡轮发动机包括高低压涡轮机，其具有相应的可反转的低压内转子和外转子，其中低压内和外转子部分可旋转地同轴地设置在高压转子内并且驱动地连接到第一和第二风扇叶片排和第一和第二增压器。由风扇壳体和环形径向内部旁路管道壁径向界定的旁路管道围绕轴向位于第一和第二风扇叶片排之间的增压器。发动机具有高压压缩机，其可操作以产生在大约40-65范围内的总体压力比和风扇入口毂与尖端半径比在0.20和0.35之间的范围内，旁路比在5-15的范围内，操作风扇压力比在1.4-2.5的范围内，以及在1000至2500英尺每秒的范围内的操作风扇叶尖速度的总和。

3. 发明授权

US06676369B2 Aspirating face seal with axially extending seal teeth 有权
标题翻译：带轴向延伸密封牙齿的吸气面密封
公开(公告)号：US06676369B2
公开(公告)日：2004-01-13
申请号：US10106401
申请日：2002-03-26
申请人： John C. Brauer , Christopher C. Glynn , Robert J. Albers
发明人： John C. Brauer , Christopher C. Glynn , Robert J. Albers
IPC分类号： F01D1102
CPC分类号： F16J15/442 , F01D11/025
摘要： A gas turbine engine aspirating face seal includes a rotatable engine member and a non-rotatable engine member and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces circumscribed about a centerline are operably associated the rotatable and non-rotatable engine members respectively. Radially inner and outer tooth rings axially extend away from a first one of the rotatable and non-rotatable gas bearing face surfaces across the leakage path and towards a second one of the gas bearing face surfaces. A pull off biasing means is used for urging the inner and outer tooth rings axially away from the second one of the gas bearing face surfaces. The rotatable engine member may be a side plate mounted on a rotor disk and the non-rotatable engine member is mounted on a translatable piston axially movably supported on a stationary face seal support structure.
摘要翻译：燃气涡轮发动机抽吸面密封件包括可旋转的发动机构件和不可旋转的发动机构件以及它们之间的泄漏路径。围绕中心线环绕的环形大致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。径向内齿和外齿环沿穿过泄漏路径并朝着气体支承面表面中的第二个轴向延伸远离可旋转和不可旋转的气体支承面表面中的第一个。使用拉脱偏压装置来推动内齿轮和外齿环轴向远离第二气体支承面表面。可旋转的发动机构件可以是安装在转子盘上的侧板，并且不可旋转的发动机构件安装在可移动地支撑在固定面密封支撑结构上的可平移活塞上。

4. 发明授权

US06471216B1 Rotating seal 有权
标题翻译：旋转密封
公开(公告)号：US06471216B1
公开(公告)日：2002-10-29
申请号：US09317244
申请日：1999-05-24
申请人： Gulcharan S. Brainch , John C. Brauer
发明人： Gulcharan S. Brainch , John C. Brauer
IPC分类号： F16J15447
CPC分类号： F01D11/02
摘要： Overall performance in enhanced in gas turbine engines by providing a rotating seal including a rotating member arranged to rotate about an axis and having at least one annular projection extending radially outwardly therefrom, and a stator element having a first surface arranged to contact the projection. The stator element includes at least one slot formed in the first surface, the slot axially traversing the projection so as to allow a flow of purge air to pass. More than one such slot can be used, and each slot is preferably angled circumferentially in the direction of rotation of the rotating member.
摘要翻译：通过提供旋转密封件来提高燃气涡轮发动机的整体性能，所述旋转密封件包括旋转部件，所述旋转部件布置成围绕轴线旋转并且具有至少一个从其径向向外延伸的环形突起，以及具有布置成接触突起的第一表面的定子元件。定子元件包括形成在第一表面中的至少一个槽，轴向穿过突出部，以允许净化空气流通过。可以使用多于一个这样的槽，并且每个槽优选地在旋转构件的旋转方向上圆周地成角度。

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

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。

7. 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。

8. 发明授权

US06619030B1 Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors 有权
标题翻译：具有涡轮机内引擎框架的飞机发动机支持反转低压涡轮转子
公开(公告)号：US06619030B1
公开(公告)日：2003-09-16
申请号：US10087681
申请日：2002-03-01
申请人： Jorge F. Seda , Lawrence W. Dunbar , Philip R. Gliebe , Peter N. Szucs , John C. Brauer , James E. Johnson , Thomas Moniz , Gregory T. Steinmetz
发明人： Jorge F. Seda , Lawrence W. Dunbar , Philip R. Gliebe , Peter N. Szucs , John C. Brauer , James E. Johnson , Thomas Moniz , Gregory T. Steinmetz
IPC分类号： F02K302
CPC分类号： F02K3/072 , F01D9/041 , F01D11/001 , F01D25/16 , F01D25/18 , F01D25/24 , F02C3/067 , F02C7/20 , F05D2240/56 , Y02T50/672
摘要： An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.
摘要翻译：飞机燃气涡轮发动机组件包括轴向位于高压和低压涡轮机之间的涡轮机间框架。低压涡轮机具有相对转动的低压内转子和外转子，其具有低压内外轴，其至少部分地可旋转地设置在高压转子内。涡轮机外框架包括径向间隔开的径向外部第一和第二结构环，所述第一和第二结构环围绕中心线共轴设置并且通过多个周向间隔开的支柱连接。具有前中心孔和后中心孔的前后贮槽构件固定地连接到涡轮机间框架的轴向间隔开的前部和后部。低压内转子和外转子由安装在船尾组件的后中心孔的第二涡轮机框架轴承可旋转地支撑。用于将发动机连接到飞行器的安装座位于第一结构环上。

9. 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

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