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41. 发明授权

US08230688B2 Modular transvane assembly 有权
标题翻译：模块化透明组件
公开(公告)号：US08230688B2
公开(公告)日：2012-07-31
申请号：US12420149
申请日：2009-04-08
申请人： Jody W. Wilson , Raymond S. Nordlund , Richard C. Charron
发明人： Jody W. Wilson , Raymond S. Nordlund , Richard C. Charron
IPC分类号： F02C3/00
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F05D2250/324 , F23R3/425 , F23R3/46
摘要： An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades.
摘要翻译：用于将罐体环形燃气轮机内燃机的燃烧器的气体输送到包括第一排涡轮叶片的涡轮机第一级部分的装置，该装置包括用于每个燃烧器的流动导向结构，其中每个流动导向结构包括直线路径和环形室端部，其中环形室端部一起限定了用于将气流输送到涡轮机第一级段的环形室，其中气体通过相应的直线路径从相应的燃烧器流动，并且作为相应的直线气体流动，并且其中所述环形室被构造成沿着相应的剪切平面联合相应的直的气体流以形成奇异的环形气流，并且其中所述环形室被构造成在所述单个环形气流气流离开环形室到第一排叶片。

42. 发明申请

US20120003088A1 SHAFT SEAL WITH CONVERGENT NOZZLE 有权
标题翻译： SHAFT密封与转换喷嘴
公开(公告)号：US20120003088A1
公开(公告)日：2012-01-05
申请号：US13142578
申请日：2010-01-15
申请人： Inam Ui Haq
发明人： Inam Ui Haq
IPC分类号： F01D11/00 , F16J15/40
CPC分类号： F01D11/025 , F01D11/04 , F05D2240/55 , F05D2250/323 , F16J15/406
摘要： A turbomachine is disclosed that has a main fluid flowpath extending axially along the turbomachine with a rotating shaft partly enclosed in a casing, wherein the rotating shaft and casing are moveable relative to each other and define a clearance opening about the rotating shaft, whereby the main fluid flowpath fluidly communicates with an outside region, and an annular seal body defining a fluid passage having a primary fluid inlet configured to receive a pressurized fluid, a fluid outlet disposed proximate to the clearance opening, and a convergent chamber interposed therebetween, wherein the convergent chamber is configured to accelerate the pressurized fluid out of the fluid outlet so as to create a local reduced pressure at the clearance opening.
摘要翻译：公开了一种涡轮机，其具有沿着涡轮机轴向延伸的主流体流动路径，其中部分地封装在壳体中的旋转轴，其中旋转轴和壳体可相对于彼此移动并限定围绕旋转轴的间隙开口，由此主体流体流动路径与外部区域流体连通，以及环形密封体，其限定具有构造成接收加压流体的主要流体入口的流体通道，邻近间隙开口设置的流体出口和介于其间的会聚室，其中会聚腔室被配置为将加压流体加速到流体出口外，以便在间隙开口处产生局部减压。

43. 发明申请

US20100077719A1 Modular Transvane Assembly 有权
标题翻译：模块化Transvane装配
公开(公告)号：US20100077719A1
公开(公告)日：2010-04-01
申请号：US12420149
申请日：2009-04-08
申请人： Jody W. Wilson , Raymond S. Nordlund , Richard C. Charron
发明人： Jody W. Wilson , Raymond S. Nordlund , Richard C. Charron
IPC分类号： F23R3/46 , F01D9/04
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F05D2250/324 , F23R3/425 , F23R3/46
摘要： An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades.
摘要翻译：用于将罐体环形燃气轮机内燃机的燃烧器的气体输送到包括第一排涡轮叶片的涡轮机第一级部分的装置，该装置包括用于每个燃烧器的流动导向结构，其中每个流动导向结构包括直线路径和环形室端部，其中环形室端部一起限定了用于将气流输送到涡轮机第一级段的环形室，其中气体通过相应的直线路径从相应的燃烧器流动，并且作为相应的直线气体流动，并且其中所述环形室被构造成沿着相应的剪切平面联合相应的直的气体流以形成奇异的环形气流，并且其中所述环形室被构造成在所述单个环形气流气流离开环形室到第一排叶片。

44. 发明授权

US07475548B2 Vectorable nozzle with pivotable triangular panels 有权
标题翻译：可旋转的三角形面板的可向量喷嘴
公开(公告)号：US07475548B2
公开(公告)日：2009-01-13
申请号：US11223606
申请日：2005-09-09
申请人： Michael Jay Toffan , Arthur McCardle
发明人： Michael Jay Toffan , Arthur McCardle
IPC分类号： F02K1/00
CPC分类号： F02K1/12 , F02K1/008 , F05D2250/11 , F05D2250/323 , F05D2250/324
摘要： A vectorable nozzle includes convergent and divergent sections and a throat therebetween. Heightwise spaced apart upper and lower walls outwardly bound a nozzle flowpath and extend aftwardly through the convergent and divergent sections from the nozzle inlet to the nozzle outlet. The upper wall includes triangular left and right side convergent upper panels pivotably mounted to a triangular convergent upper ramp in the convergent section along left and right side convergent angled hinge lines respectively. The upper wall further includes triangular left and right side divergent upper panels pivotably attached to a triangular divergent upper ramp in the divergent section along left and right side divergent angled hinge lines respectively. The left and right side convergent upper panels are in sealing engagement with the left and right side divergent upper panels along left and right side upper interfaces, respectively.
摘要翻译：可向导的喷嘴包括收敛和发散部分以及其间的喉部。高度间隔开的上壁和下壁向外限定了喷嘴流动路径，并且通过从喷嘴入口到喷嘴出口的会聚和发散部分向后延伸。上壁包括分别沿左右侧收敛角铰链线可枢转地安装在收敛部分中的三角形会聚上斜面的三角形左右收敛上面板。上壁还包括三角形左右发散上面板，其分别沿着左右发散角度铰链线可枢转地附接到发散部分中的三角形发散上坡道。左右侧收敛上板分别沿着左右上侧接口与左侧和右侧发散上板密封接合。

45. 发明申请

US20080000238A1 HIGH EFFICIENCY THERMAL ENGINE 有权
标题翻译：高效热发动机
公开(公告)号：US20080000238A1
公开(公告)日：2008-01-03
申请号：US11557738
申请日：2006-11-08
申请人： Yves Ribaud , Joel Guidez , Jean-Paul Breteau , Thierry Courvoisier , Olivier Dessornes , Clement Dumand
发明人： Yves Ribaud , Joel Guidez , Jean-Paul Breteau , Thierry Courvoisier , Olivier Dessornes , Clement Dumand
IPC分类号： F02C3/06
CPC分类号： F23R3/42 , F01D13/00 , F02C3/02 , F02C3/05 , F02C3/14 , F02C3/305 , F02C6/003 , F02C7/27 , F02C7/272 , F05D2220/768 , F05D2250/323 , F05D2250/82 , F05D2250/84 , F05D2260/85 , F05D2300/5024 , F23C2900/03001 , Y02E20/16
摘要： The engine comprises a low pressure stage (1) and a high pressure stage (2) with two independent rotors (3,4) and associated fixed fluid preparation members (9,10,13,14), combining “compressor” means (15,16) and “expander” means (17,18) and at least one combustion chamber (19,20) in a central volume defined axially by the rotors (3,4) and laterally by three substantially cylindrical, coaxial walls (22,23,24), defining in pairs an outer duct (25) connecting the outlet of the LP compressor (15) to the inlet of the HP compressor (16) and an inner duct (26) connecting the outlet of the HP compressor (16) to the inlet of a first combustion chamber (19), whose outlet supplies the HP expander (18) with gases produced by combustion guided to the inlet of the LP expander (17), whose outlet is in communication with the outside via at least one exhaust opening (41) for the combustion gases.
摘要翻译：发动机包括具有两个独立转子（3,4）和相关联的固定流体制备构件（9,10,13,14）的低压级（1）和高压级（2），组合“压缩机”装置（15 ，16）和“膨胀器”（17,18）和至少一个燃烧室（19,20），所述燃烧室位于由转子（3,4）轴向限定并且由三个基本上圆柱形的同轴壁 23,24），成对地限定将LP压缩机（15）的出口连接到HP压缩机（16）的入口的外部管道（25）和连接HP压缩机（16）的出口的内部管道（26））连接到第一燃烧室（19）的入口，其第一燃烧室（19）的出口向HP膨胀器（18）供应由燃烧产生的气体引导到LP膨胀器（17）的入口，该出口通过至少与外部连通一个用于燃烧气体的排气口（41）。

46. 发明授权

US07204675B2 Cooled gas turbine engine vane 有权
标题翻译：冷却燃气轮机发动机叶片
公开(公告)号：US07204675B2
公开(公告)日：2007-04-17
申请号：US10916435
申请日：2004-08-12
申请人： Christophe Texier
发明人： Christophe Texier
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2250/141 , F05D2250/232 , F05D2250/292 , F05D2250/323 , F05D2250/70 , F05D2250/71 , F05D2260/201
摘要： A cooled gas turbine vane includes a cast part and a longitudinal sleeve obtained by shaping metal sheet The cast part includes a longitudinal body provided with a longitudinal cavity having a first opening and a second opening at the ends The sleeve is mounted in the cavity by being firmly affixed to the wall of the first opening, and one end part of which being free to slide in the second opening forming a guide. The end part includes a part having constricted dimensions relative to the transverse dimensions of the guide.
摘要翻译：冷却的燃气涡轮机叶片包括铸造部件和通过成形金属板而获得的纵向套筒。铸造部件包括纵向主体，纵向主体设置有纵向腔体，该纵向腔室在端部具有第一开口和第二开口。套筒通过牢固地固定在第一开口的壁上，其一端部在形成导向件的第二开口中自由滑动。端部包括相对于导向件的横向尺寸具有缩小尺寸的部分。

47. 发明授权

US06996973B2 Method of achieving jet separation of an un-separated flow in a divergent nozzle body of a rocket engine 失效
标题翻译：实现火箭发动机发散喷嘴体中未分离流动的喷射分离的方法
公开(公告)号：US06996973B2
公开(公告)日：2006-02-14
申请号：US10953447
申请日：2004-09-30
申请人： Christian François Michel Dujarric
发明人： Christian François Michel Dujarric
IPC分类号： F02K1/28
CPC分类号： F02K9/97 , F02K9/82 , F05D2250/323 , F05D2250/324
摘要： The invention relates to a rocket engine nozzle comprising a system for controlling jet separation of the flow in the nozzle, wherein said control system exhibits a plurality of separation triggering elements (5, 10) arranged in such a way as to generate, from mutually spaced initiation points (9), distinct zones (6) of jet separation, so as to form a three-dimensional separation of the flow.The flow control system can exhibit at least two triggering elements (5, 10).
摘要翻译：本发明涉及一种火箭发动机喷嘴，其包括用于控制喷嘴中的流动的喷射分离的系统，其中所述控制系统呈现多个分离触发元件（5,10），所述分离触发元件（5,10）以相互间隔起始点（9），喷射分离的不同区域（6），以形成流动的三维分离。

48. 发明申请

US20050210861A1 Axial divergent section slot nozzle 有权
标题翻译：轴向分歧槽口喷嘴
公开(公告)号：US20050210861A1
公开(公告)日：2005-09-29
申请号：US10811374
申请日：2004-03-26
申请人： Robert Bush , Sean Zamora , Harry Culver , Donald Peters
发明人： Robert Bush , Sean Zamora , Harry Culver , Donald Peters
IPC分类号： F02K1/00 , F02K1/12 , F02K1/36 , F02K1/80
CPC分类号： F02K1/805 , F02K1/008 , F02K1/1223 , F02K1/1292 , F02K1/46 , F05D2240/55 , F05D2250/323 , F05D2250/324 , F05D2260/50 , Y02T50/671
摘要： An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross sectional area of the nozzle in a throat region, and a bridge member positioned intermediate adjacent ones of the flaps. The bridge member includes a bridge bracket and a sealing element joined to the bridge bracket. The sealing element has an upper surface. The bridge bracket has a lower surface which diverges from the upper surface of the sealing element. In a preferred embodiment of the present invention, the bridge bracket has a shape which allows variable slot size depending on nozzle throat jet area.
摘要翻译：提供了一种用于发动机的轴向发散部分狭缝喷嘴。所述喷嘴具有多个间隔开的发散翼片，至少一个装置，用于移动所述发散翼片以改变所述喷嘴在喉部区域中的横截面积，以及定位在所述翼片之间的桥构件。桥构件包括桥架和与桥架相连的密封元件。密封元件具有上表面。桥架具有从密封元件的上表面发散的下表面。在本发明的优选实施例中，桥式支架具有允许根据喷嘴喉部喷射面积而变化的槽尺寸的形状。

49. 发明申请

US20050178127A1 Rocket engine nozzle comprising a jet separation control system 失效
标题翻译：火箭发动机喷嘴包括喷射分离控制系统
公开(公告)号：US20050178127A1
公开(公告)日：2005-08-18
申请号：US10953447
申请日：2004-09-30
申请人： Christian Dujarric
发明人： Christian Dujarric
IPC分类号： F02K9/82 , F02K9/97 , F02K1/00
CPC分类号： F02K9/97 , F02K9/82 , F05D2250/323 , F05D2250/324
摘要： The invention relates to a rocket engine nozzle comprising a system for controlling jet separation of the flow in the nozzle, wherein said control system exhibits a plurality of separation triggering elements (5, 10) arranged in such a way as to generate, from mutually spaced initiation points (9), distinct zones (6) of jet separation, so as to form a three-dimensional separation of the flow. The flow control system can exhibit at least two triggering elements (5, 10).
摘要翻译：本发明涉及一种火箭发动机喷嘴，其包括用于控制喷嘴中的流动的喷射分离的系统，其中所述控制系统呈现多个分离触发元件（5,10），所述分离触发元件（5,10）以相互间隔起始点（9），喷射分离的不同区域（6），以形成流动的三维分离。流量控制系统可以显示至少两个触发元件（5,10）。

50. 发明申请

US20050089395A1 Cooled gas turbine engine vane 有权
标题翻译：冷却燃气轮机发动机叶片
公开(公告)号：US20050089395A1
公开(公告)日：2005-04-28
申请号：US10916435
申请日：2004-08-12
申请人： Christophe Texier
发明人： Christophe Texier
IPC分类号： F01D9/02 , F01D5/18 , F02C7/18 , F01D5/14
CPC分类号： F01D5/188 , F05D2250/141 , F05D2250/232 , F05D2250/292 , F05D2250/323 , F05D2250/70 , F05D2250/71 , F05D2260/201
摘要： The cooled gas turbine vane of the invention comprises a cast part and a longitudinal sleeve obtained by shaping metal sheet; the cast part comprises a longitudinal body provided with a longitudinal cavity having a first opening and a second opening at the ends; the sleeve is mounted in the cavity by being firmly affixed to the wall of the first opening, and one end part of which being free to slide in the second opening forming a guide. Said end part comprises a part having constricted dimensions relative to the transverse dimensions of the guide.
摘要翻译：本发明的冷却燃气轮机叶片包括铸造件和通过成形金属板而获得的纵向套管; 所述铸造部件包括纵向本体，所述纵向本体设置有在所述端部具有第一开口和第二开口的纵向空腔; 通过牢固地固定在第一开口的壁上，将套筒安装在空腔中，其一端部在形成引导件的第二开口中自由滑动。所述端部包括相对于导向件的横向尺寸具有缩小尺寸的部分。

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