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1. 发明授权

US07341429B2 Methods and apparatuses for cooling gas turbine engine rotor assemblies 有权
标题翻译：用于冷却燃气涡轮发动机转子组件的方法和装置
公开(公告)号：US07341429B2
公开(公告)日：2008-03-11
申请号：US11280439
申请日：2005-11-16
申请人： Julius John Montgomery , Robert Proctor , Nathan Gerard Cormier , Christopher Charles Glynn , Glen William Royal , Richard William Jendrix
发明人： Julius John Montgomery , Robert Proctor , Nathan Gerard Cormier , Christopher Charles Glynn , Glen William Royal , Richard William Jendrix
IPC分类号： F03B11/00
CPC分类号： F01D5/082 , F05D2250/70 , F05D2260/201
摘要： A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine mid-frame such that a cavity is defined between the rotor disk and the turbine mid-frame, and forming at least one opening extending through the turbine mid-frame to facilitate channeling cooling air into the gap, the opening configured to impart a high relative tangential velocity into the cooling air discharged from the opening.
摘要翻译：一种制造燃气涡轮发动机的方法包括提供涡轮机中间框架，将多个转子叶片耦合到转子盘，转子盘从涡轮机中间框架轴向后部被连接，使得在转子盘和涡轮机中间框架，并且形成延伸穿过涡轮机中间框架的至少一个开口，以便于将冷却空气引导到间隙中，该开口构造成将高的相对切向速度赋予从开口排出的冷却空气。

2. 发明授权

US07363762B2 Gas turbine engines seal assembly and methods of assembling the same 有权
标题翻译：燃气涡轮发动机密封组件及其组装方法
公开(公告)号：US07363762B2
公开(公告)日：2008-04-29
申请号：US11280440
申请日：2005-11-16
申请人： Julius John Montgomery , Robert Proctor , Nathan Gerard Cormier , Christopher Charles Glynn , Glen William Royal
发明人： Julius John Montgomery , Robert Proctor , Nathan Gerard Cormier , Christopher Charles Glynn , Glen William Royal
IPC分类号： F01D3/04
CPC分类号： F02C3/08 , F01D11/02 , F04D29/0516 , F04D29/083 , F04D29/284 , Y10T29/4932 , Y10T29/49323 , Y10T29/49895
摘要： A method of assembling a gas turbine engine includes providing a gas turbine engine including a compressor, a combustor downstream from the compressor, and a turbine coupled to the compressor, and coupling a seal assembly aft of the compressor such that air discharged through the seal assembly facilitates reducing the cavity pressure, and therefore reducing the axial forces induced to an aft side of the compressor.
摘要翻译：一种组装燃气涡轮发动机的方法包括提供包括压缩机，在压缩机下游的燃烧器和联接到压缩机的涡轮的燃气涡轮发动机，以及联接压缩机后部的密封组件，使得通过密封组件排出的空气有助于减小腔体压力，并且因此减小感应到压缩机的后侧的轴向力。

3. 发明授权

US06722137B2 Methods and apparatus for regulating turbine clearance control system airflow 有权
标题翻译：调节涡轮间隙控制系统气流的方法和装置
公开(公告)号：US06722137B2
公开(公告)日：2004-04-20
申请号：US09932596
申请日：2001-08-17
申请人： Robert Proctor , John William Hanify , Debra Lynn Prikkel , Michael Jay Epstein , Julius John Montgomery
发明人： Robert Proctor , John William Hanify , Debra Lynn Prikkel , Michael Jay Epstein , Julius John Montgomery
IPC分类号： F16K122
CPC分类号： F16K1/222 , F01D17/148
摘要： A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides.
摘要翻译：用于燃气涡轮发动机的蝶形阀包括阀轴和阀盘。阀盘具有延伸穿过阀盘的中心线。阀盘还包括轴开口，外周边，外表面，第一侧和第二侧。第一面与第二面相对。轴开口延伸穿过邻近中心线轴线的阀盘，并且其尺寸被设计成在其中容纳阀轴。盘外表面在第一和第二侧上延伸，并且在圆盘第一和第二面中的至少一个之间在外圆周和中心线轴线之间呈锥形。

4. 发明授权

US06550254B2 Gas turbine engine bleed scoops 有权
标题翻译：燃气涡轮发动机排气勺
公开(公告)号：US06550254B2
公开(公告)日：2003-04-22
申请号：US09932585
申请日：2001-08-17
申请人： Robert Proctor , Julius John Montgomery , Michael Jay Epstein , Roger Owen Barbe , Hai Buu Sam , James Bernar Ogzewalla , Andrew David Kemp , Bryan Keith Doloresco
发明人： Robert Proctor , Julius John Montgomery , Michael Jay Epstein , Roger Owen Barbe , Hai Buu Sam , James Bernar Ogzewalla , Andrew David Kemp , Bryan Keith Doloresco
IPC分类号： F02C608
CPC分类号： F01D9/041 , F01D17/105 , F02C6/08 , F04D29/542
摘要： A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.
摘要翻译：燃气涡轮发动机包括具有壳体和定子组件的压缩机。壳体围绕定子组件延伸，定子组件包括多个定子叶片和多个排出勺。邻近的定子叶片限定静态高压区域，至少部分地形成在高压区域内的排放勺。

5. 发明授权

US07048496B2 Turbine cooling, purge, and sealing system 有权
标题翻译：涡轮冷却，吹扫和密封系统
公开(公告)号：US07048496B2
公开(公告)日：2006-05-23
申请号：US10285891
申请日：2002-10-31
申请人： Robert Proctor , James Patrick Dolan , John Christopher Brauer , Christopher Charles Glynn , Kenneth Martin Lewis
发明人： Robert Proctor , James Patrick Dolan , John Christopher Brauer , Christopher Charles Glynn , Kenneth Martin Lewis
IPC分类号： F01D25/12
CPC分类号： F01D25/14 , F01D1/26 , F01D11/006 , Y02T50/675
摘要： A rotor system for a gas turbine engine is provided having an outer rotor which includes an annular outer spool that comprises at least one ring portion of increased thickness with respect to the remainder of the outer spool, attached to a relatively thinner, axially extending arm portion. A plurality of outer turbine blades are attached to the ring portion of the outer spool and extend radially inwardly into a working gas flowpath of the engine. A casing surrounds the outer spool and defines an annular cavity between the casing and the outer spool, which is sealed by forward and aft brush seals at the forward and aft ends thereof. At least one inlet port is formed through the casing for admitting a flow of cooling air to the annular cavity. Means are provided for directing this cooling air flow to the ring portion of the outer spool.
摘要翻译：提供了一种用于燃气涡轮发动机的转子系统，其具有外转子，该外转子包括环形外卷轴，该环形外卷轴包括相对于外卷轴的其余部分增加的厚度的至少一个环部分，附接到相对较薄的轴向延伸的臂部分。多个外涡轮叶片附接到外卷轴的环部分并且径向向内延伸到发动机的工作气体流动路径中。壳体围绕外部卷轴并且在壳体和外部卷轴之间限定出一个环形空腔，其在其前端和后端由前后刷密封件密封。通过壳体形成至少一个入口端口，用于允许冷却空气流进入环形空腔。提供了用于将该冷却空气流引导到外部卷轴的环部的装置。

6. 发明授权

US07935164B2 Vortex air-oil separator system 有权
标题翻译：涡旋空气 - 油分离器系统
公开(公告)号：US07935164B2
公开(公告)日：2011-05-03
申请号：US11946111
申请日：2007-11-28
申请人： Ning Fang , Duane Howard Anstead , Robert Proctor , Pradeep Hemant Sangli , Prasad Laxman Kane , Gary Paul Moscarino , Bala Corattiyil , Ray Harris Kinnaird , David William Pugh , Mark Eden Zentgraf
发明人： Ning Fang , Duane Howard Anstead , Robert Proctor , Pradeep Hemant Sangli , Prasad Laxman Kane , Gary Paul Moscarino , Bala Corattiyil , Ray Harris Kinnaird , David William Pugh , Mark Eden Zentgraf
IPC分类号： B01D46/18 , B01D46/30
CPC分类号： F01D25/18 , B01D45/14 , F01M2013/0422 , F16C33/6685 , F16C2360/23 , Y10S55/19
摘要： The present invention provides a vortex generator that may be used in systems for separating oil from air oil mixtures. The vortex generator comprises a rotating disk having a rim having a plurality of passages extending through it and a cavity formed by the rotating disk and a cavity wall wherein a vortex is created when there is a flow through the plurality of passages into the cavity.
摘要翻译：本发明提供了可用于从空气混合物中分离油的系统中的涡流发生器。涡流发生器包括旋转盘，其具有带有延伸穿过其的多个通道的边缘和由旋转盘形成的空腔和空腔壁，其中当流过多个通道进入空腔时产生涡流。

7. 发明授权

US06293554B1 Brush seal segment having bristle damping 失效
标题翻译：刷子密封段具有刷毛阻尼
公开(公告)号：US06293554B1
公开(公告)日：2001-09-25
申请号：US09451246
申请日：1999-11-29
申请人： Osman Saim Dinc , Yahya Dogu , Michael Eugene Battle , Robert Joseph Albers , Robert Proctor
发明人： Osman Saim Dinc , Yahya Dogu , Michael Eugene Battle , Robert Joseph Albers , Robert Proctor
IPC分类号： F16J15447
CPC分类号： F16J15/3288
摘要： A brush seal segment useful, when circumferentially arrayed with other such segments, to seal the gap between a rotor and a surrounding casing of a rotary machine such as a gas or steam turbine. Brush-seal bristles are positioned between a brush-seal back plate and a brush-seal front plate with the free end of each bristle extending beyond the edges of the plates. The front plate has a portion extending to the edge of the front plate with the portion spaced apart from the bristles. In one example, the portion has an array of through holes. In another example, the portion has a ledge projecting generally away from the bristles.
摘要翻译：当用其它这种部分周向排列时，用于密封旋转机器诸如气体或汽轮机的转子和周围壳体之间的间隙的刷密封段是有用的。刷密封刷毛位于刷密封背板和刷密封前板之间，每个刷毛的自由端延伸超过板的边缘。前板具有延伸到前板的边缘的部分，其中与刷毛间隔开的部分。在一个示例中，该部分具有通孔阵列。在另一个示例中，该部分具有大致远离刷毛突出的突出部。

8. 发明授权

US06139257A Shroud cooling assembly for gas turbine engine 有权
标题翻译：燃气轮机发动机护罩冷却组件
公开(公告)号：US06139257A
公开(公告)日：2000-10-31
申请号：US249205
申请日：1999-02-12
申请人： Robert Proctor , Edward P. Brill , Randall B. Rydbeck , John W. Hanify , Gregory A. White
发明人： Robert Proctor , Edward P. Brill , Randall B. Rydbeck , John W. Hanify , Gregory A. White
IPC分类号： F01D11/02 , F01D9/04 , F01D25/12 , F02C7/18 , F01D25/08
CPC分类号： F01D11/08 , F01D9/04 , F05D2260/201 , F05D2260/202
摘要： To cool the shroud assembly 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 rails and back surfaces of the shroud. Impingement cooling air then flows through elongated, convection cooling passages in the shroud sections and exits to flow along the shroud front surface with the main gas stream to provide film cooling. The aft rail of the shroud sections is provided with one or more cooling holes to impingement cool the annular retaining ring or C-clip retaining the shroud sections on the shroud hangers. This cooling air then travels aftward on the inboard side of the C-clip to provide convection cooling of the C-clip. In an alternative embodiment, cooling air is directed at the aft corners of the shroud base to avoid overheating.
摘要翻译：为了冷却燃气轮机发动机的高压涡轮机部分中的护罩组件，将高压冷却空气以计量流量导向挡板增压室，从而通过挡板穿孔冲击以冷却护罩的轨道和后表面。冲击冷却空气然后流过护罩部分中的细长的对流冷却通道并且离开以沿着护罩前表面与主气流一起流动以提供膜冷却。护罩部分的后导轨设置有一个或多个冷却孔，以将保持护罩部分的环形固定环或C形夹子冷却到护罩悬挂器上。然后，该冷却空气在C形夹的内侧向后行进，以提供C形夹的对流冷却。在替代实施例中，冷却空气被引导到护罩底座的后角以避免过热。

9. 发明授权

US5593277A Smart turbine shroud 失效
标题翻译：智能涡轮罩
公开(公告)号：US5593277A
公开(公告)日：1997-01-14
申请号：US467418
申请日：1995-06-06
申请人： Robert Proctor , David R. Linger , David A. Di Salle , Steven R. Brassfield , Larry W. Plemmons
发明人： Robert Proctor , David R. Linger , David A. Di Salle , Steven R. Brassfield , Larry W. Plemmons
IPC分类号： F01D11/18 , F01D11/24
CPC分类号： F01D11/18 , F01D11/24
摘要： A turbine shroud includes an annular outer casing having first and second radial flanges between which are suspended an adjoining annular shroud support and an annular shroud hanger. A plurality of shroud panels are joined to the shroud hanger and are positionable radially above turbine rotor blades to define a tip clearance therebetween. The four flanges are disposed in abutting contact with each other, and respective pluralities of circumferentially spaced apart first, second, and third recesses are disposed respectively between the casing first flange and the shroud flange, between the shroud flange and the hanger flange, and between the hanger flange and the casing second flange for providing radial flowpaths therebetween. The support flange and the hanger flange have respective pluralities of circumferentially spaced apart first and second metering holes extending axially therethrough for providing flow communication between the first, second, and third recesses for channeling compressor bleed air therethrough for controlling the tip clearance.
摘要翻译：涡轮机护罩包括具有第一和第二径向凸缘的环形外壳，在其之间悬挂有邻接的环形护罩支撑件和环形护罩悬挂器。多个护罩板连接到护罩悬挂器并且可径向地位于涡轮转子叶片上方以限定其间的顶端间隙。四个凸缘彼此邻接地设置，并且相应的多个周向间隔开的第一，第二和第三凹槽分别设置在壳体第一凸缘和护罩凸缘之间，护罩凸缘和悬挂器凸缘之间，以及衣架法兰和套管第二法兰，用于在其间提供径向流动路径。支撑凸缘和悬挂器法兰具有相应的多个周向间隔开的第一和第二计量孔，其轴向延伸穿过其中，以提供第一，第二和第三凹部之间的流动连通，用于引导压缩机排出空气通过其中以控制顶端间隙。

10. 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.

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