公开(公告)号：US20150301510A1

公开(公告)日：2015-10-22

申请号：US14258740

申请日：2014-04-22

申请人： Siegmund Düll ,  Mrinal Munshi ,  Sigurd Spieckermann ,  Steffen Udluft

发明人： Siegmund Düll ,  Mrinal Munshi ,  Sigurd Spieckermann ,  Steffen Udluft

IPC分类号： G05B15/02 ,  G06N3/08

CPC分类号： G06N3/08 ,  G05B13/027

摘要： For controlling a target system, operational data of a plurality of source systems are used. The data of the source systems are received and are distinguished by source system specific identifiers. By a neural network, a neural model is trained on the basis of the received operational data of the source systems taking into account the source system specific identifiers, where a first neural model component is trained on properties shared by the source systems and a second neural model component is trained on properties varying between the source systems. After receiving operational data of the target system, the trained neural model is further trained on the basis of the operational data of the target system, where a further training of the second neural model component is given preference over a further training of the first neural model component. The target system is controlled by the further trained neural network.

摘要翻译： 为了控制目标系统，使用多个源系统的操作数据。 源系统的数据被接收并由源系统特定标识符区分。 通过神经网络，在考虑到源系统特定标识符的基础上，基于接收到的源系统的操作数据来训练神经模型，其中第一神经模型分量被训练在源系统共享的属性上，第二神经模型 对源代码系统之间的属性进行训练。 在接收目标系统的操作数据之后，基于目标系统的操作数据进一步训练经过训练的神经模型，其中第二神经模型组件的进一步训练优先于第一神经模型的进一步训练 零件。 目标系统由进一步训练的神经网络控制。

公开(公告)号：US10094285B2

公开(公告)日：2018-10-09

申请号：US13746447

申请日：2013-01-22

申请人： Mrinal Munshi ,  John W. Finneran ,  Yevgeniy Shteyman ,  Daryl J. Graber ,  Matthew R. Porter ,  Jonathan M. Leagon

发明人： Mrinal Munshi ,  John W. Finneran ,  Yevgeniy Shteyman ,  Daryl J. Graber ,  Matthew R. Porter ,  Jonathan M. Leagon

IPC分类号： F01D9/06 ,  F01D25/14 ,  F01D25/16 ,  F02C7/12 ,  F01D25/12 ,  F01D25/30

摘要： A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct structure is provided and includes an inlet end in fluid communication with the channel outlet and includes an outlet end in fluid communication with an area of reduced pressure relative to the air duct structure inlet end. An exit cavity is located at the air duct structure outlet end, wherein the exit cavity effects a reduced pressure at the outlet end to draw air from the cooling channel into the air duct.

公开(公告)号：US20140286763A1

公开(公告)日：2014-09-25

申请号：US13746447

申请日：2013-01-22

申请人： Mrinal Munshi ,  John W. Finneran ,  Yevgeniy Shteyman ,  Daryl J. Graber ,  Matthew R. Porter ,  Jonathan M. Leagon

发明人： Mrinal Munshi ,  John W. Finneran ,  Yevgeniy Shteyman ,  Daryl J. Graber ,  Matthew R. Porter ,  Jonathan M. Leagon

IPC分类号： F02C7/12

CPC分类号： F02C7/12 ,  F01D9/065 ,  F01D25/12 ,  F01D25/145 ,  F01D25/162 ,  F01D25/30 ,  F05D2240/128 ,  F05D2240/15

摘要： A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct structure is provided and includes an inlet end in fluid communication with the channel outlet and includes an outlet end in fluid communication with an area of reduced pressure relative to the air duct structure inlet end. An exit cavity is located at the air duct structure outlet end, wherein the exit cavity effects a reduced pressure at the outlet end to draw air from the cooling channel into the air duct.

摘要翻译： 一种燃气涡轮发动机，其包括限定在外壳内的外壳和排气通道，用于从燃气涡轮发动机的涡轮部进行排气流。 冷却通道与外壳的外表面相关联，冷却通道具有通道入口和通道出口。 提供了一种空气管道结构，并且包括与通道出口流体连通的入口端，并且包括与相对于空气管道结构入口端部的减压区域流体连通的出口端。 出口腔位于空气管道结构出口端，其中出口腔在出口端处实现减压以将空气从冷却通道吸入空气管道。

公开(公告)号：US08608443B2

公开(公告)日：2013-12-17

申请号：US12813602

申请日：2010-06-11

申请人： Ching-Pang Lee ,  Jae Y. Um ,  Mrinal Munshi ,  Humberto A. Zuniga

发明人： Ching-Pang Lee ,  Jae Y. Um ,  Mrinal Munshi ,  Humberto A. Zuniga

IPC分类号： F01D9/06 ,  F01D5/18

CPC分类号： F01D5/186 ,  F01D5/288 ,  F01D25/12 ,  F05D2230/10 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2250/183 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2300/502 ,  F23R2900/03042 ,  Y10T29/49236

摘要： A component wall in a turbine engine. The component wall includes a substrate, a trench, and a plurality of cooling passages. The substrate has a first surface and a second surface opposed from the first surface. The trench is located in the second surface and is defined by a bottom surface between the first and second surfaces, a first sidewall, and a second sidewall spaced from the first sidewall. The first sidewall extends radially outwardly continuously from the bottom surface of the trench to the second surface. The first sidewall includes a plurality of first protuberances extending toward the second sidewall. The cooling passages extend through the substrate from the first surface to the bottom surface of the trench. Outlets of the cooling passages are arranged within the trench such that cooling air exiting the cooling passages is directed toward respective ones of the first protuberances.

摘要翻译： 涡轮发动机中的部件壁。 部件壁包括基板，沟槽和多个冷却通道。 基板具有与第一表面相对的第一表面和第二表面。 沟槽位于第二表面中，并且由第一和第二表面之间的底表面，第一侧壁和与第一侧壁间隔开的第二侧壁限定。 第一侧壁从沟槽的底表面连续径向向外延伸到第二表面。 第一侧壁包括朝向第二侧壁延伸的多个第一突起。 冷却通道从沟槽的第一表面延伸到底表面。 冷却通道的出口布置在沟槽内，使得离开冷却通道的冷却空气被引向第一突起中的相应的一个。

公开(公告)号：US09630277B2

公开(公告)日：2017-04-25

申请号：US12723880

申请日：2010-03-15

申请人： Ching-Pang Lee ,  Mrinal Munshi ,  Gm S. Azad ,  Jae Y. Um

发明人： Ching-Pang Lee ,  Mrinal Munshi ,  Gm S. Azad ,  Jae Y. Um

IPC分类号： F02C7/12 ,  B23P6/00 ,  F01D5/00 ,  F01D5/14 ,  F01D5/18

CPC分类号： B23P6/007 ,  F01D5/005 ,  F01D5/145 ,  F01D5/186 ,  F05D2230/30 ,  F05D2230/80 ,  F05D2240/81 ,  Y10T29/49318

摘要： A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform.

公开(公告)号：US20130302166A1

公开(公告)日：2013-11-14

申请号：US13467112

申请日：2012-05-09

申请人： CHING-PANG LEE ,  Mrinal Munshi

发明人： CHING-PANG LEE ,  Mrinal Munshi

IPC分类号： F01D5/08 ,  B23K31/02

CPC分类号： B23P6/002 ,  F01D5/005 ,  F01D5/18 ,  F01D5/20 ,  F01D11/14

摘要： A squealer tip usable in repair systems and formed from a pressure side outer weld rib and a suction side outer weld rib extending radially outward from a tip of the turbine blade and resting upon pressure side and suction side weld members separated by a mid-chord member is disclosed. The pressure and suction side outer weld ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure side outer weld rib may include a chamfered pressure side with film cooling holes having exhaust outlets positioned therein. The pressure and suction side weld members may be configured to retain the mid-chord member in position with over extending side surfaces.

摘要翻译： 一种可用于修理系统的起重机末端，由压力侧外部焊接肋和从涡轮机叶片的顶端径向向外延伸的吸入侧外部焊接肋形成，并位于压力侧，并且由中间弦构件分隔的吸入侧焊接构件 被披露。 压力和吸力侧外部焊接肋可以分别沿涡轮叶片的压力侧和吸力侧定位。 压力侧外部焊接肋可以包括倒角压力侧，其中具有定位在其中的排气出口的膜冷却孔。 压力和吸力侧焊接构件可以构造成将中弦构件保持在适当位置并且具有过度延伸的侧表面。

公开(公告)号：US20130149121A1

公开(公告)日：2013-06-13

申请号：US13746423

申请日：2013-01-22

申请人： Mrinal Munshi ,  John W. Finneran ,  Yevgeniy Shteyman ,  Daryl J. Graber ,  Matthew R. Porter ,  Jonathan M. Leagon

发明人： Mrinal Munshi ,  John W. Finneran ,  Yevgeniy Shteyman ,  Daryl J. Graber ,  Matthew R. Porter ,  Jonathan M. Leagon

IPC分类号： F01D25/08

CPC分类号： F01D25/08 ,  F01D25/14

摘要： An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment flange extending from a downstream edge and attached to a spring plate diffuser support structure and at least one attachment flange extending from side edges of the exhaust diffuser to couple sections of the exhaust diffuser together. The diffuser may also include a thermal barrier/cooling system for controlling a temperature of an outer case of the gas turbine engine. The thermal barrier/cooling system may form a flow path for an ambient air flow cooling.

摘要翻译： 公开了一种用于将燃气涡轮发动机中的涡轮机组件下游的至少一个排气扩散器附接的附接系统。 附接系统可以包括从下游边缘延伸并附接到弹簧板扩散器支撑结构的至少一个附接凸缘和从排气扩散器的侧边缘延伸以将排气扩散器的部分连接在一起的至少一个附接凸缘。 扩散器还可以包括用于控制燃气涡轮发动机外壳的温度的隔热/冷却系统。 隔热/冷却系统可以形成用于环境空气流冷却的流动路径。

公开(公告)号：US20150118040A1

公开(公告)日：2015-04-30

申请号：US14062925

申请日：2013-10-25

申请人： Ching-Pang Lee ,  Mrinal Munshi ,  Adam C. Pela ,  Paul Bradley Davis ,  Matthew H. Lang

发明人： Ching-Pang Lee ,  Mrinal Munshi ,  Adam C. Pela ,  Paul Bradley Davis ,  Matthew H. Lang

IPC分类号： F01D9/04

CPC分类号： F01D9/042 ,  F01D25/246 ,  F05D2230/80 ,  F05D2250/61

摘要： A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The forward wall extends generally radially outwardly from a forward side of the main body portion. The strong back plate spans between the forward wall and the aft hook and effects a reduction in dynamic displacement between the forward wall and the aft hook during operation of the engine.

摘要翻译： 在燃气涡轮发动机的发动机部分中的一排叶片的支撑环包括环形主体部分，用于为发动机部分中的一排叶片提供结构支撑，后钩，前壁和强背板 。 后钩从主体部分的后侧延伸并且联接到外部发动机壳体，用于在发动机部分中结构地支撑支撑环。 前壁从主体部分的前侧大致径向向外延伸。 强后背板在前壁和后钩之间跨越，并且在发动机操作期间实现前壁和后钩之间的动态位移的减小。

公开(公告)号：US20150044046A1

公开(公告)日：2015-02-12

申请号：US13961029

申请日：2013-08-07

申请人： Yevgeniy Shteyman ,  Matthew R. Porter ,  Mrinal Munshi ,  Douglas R. Roth ,  Timothy J. Stewart, JR.

发明人： Yevgeniy Shteyman ,  Matthew R. Porter ,  Mrinal Munshi ,  Douglas R. Roth ,  Timothy J. Stewart, JR.

IPC分类号： F01D25/08 ,  B22D31/00 ,  B22D25/02

CPC分类号： F01D25/08 ,  B22C9/22 ,  B22D25/02 ,  B22D31/00 ,  B22D31/002 ,  F01D25/162 ,  F01D25/30 ,  F05D2230/21 ,  F05D2230/232 ,  F05D2250/15 ,  Y10T29/49229

摘要： A method for casting a collar (44, 46) for a heat shield (36) of a strut (32) in a gas turbine exhaust section (20). A casting geometry (60, 70) is defined with extra wall thickness (56, 68) in an area of wall curvature (53, 54), which provides a flow path beyond a final geometry of the collar to facilitate a flow of molten metal in the mold (63, 64). The extra thickness is removed after casting, leaving the collar in its final geometry, which may have uniform wall thickness (T, T2). The extra thickness in the casting geometry may be provided by increased radius (R3) in the wall curvature and/or by casting feed portals (66, 68) that span the wall curvature between a tubular portion (50) and a flange (52) of the collar.

摘要翻译： 一种用于铸造用于燃气轮机排气部分（20）中的支柱（32）的隔热罩（36）的轴环（44,46）的方法。 铸造几何形状（60,70）在壁曲率（53,54）的区域中被限定为额外的壁厚（56,68），其提供超过套环的最终几何形状的流动路径，以促进熔融金属的流动 在模具（63,64）中。 在铸造之后移除额外的厚度，使套环处于其最终几何形状，其可具有均匀的壁厚（T，T2）。 铸造几何形状中的额外厚度可以通过在壁曲率上增加的半径（R3）和/或通过跨越管状部分（50）和凸缘（52）之间的壁曲率的浇铸进料口（66,68）来提供， 的衣领。

公开(公告)号：US20150040393A1

公开(公告)日：2015-02-12

申请号：US13961186

申请日：2013-08-07

申请人： Yevgeniy Shteyman ,  Matthew R. Porter ,  Mrinal Munshi ,  Douglas R. Roth ,  Timothy J. Stewart, Jr.

发明人： Yevgeniy Shteyman ,  Matthew R. Porter ,  Mrinal Munshi ,  Douglas R. Roth ,  Timothy J. Stewart, Jr.

IPC分类号： B23P15/00 ,  F01D25/30

CPC分类号： B23P15/00 ,  F01D25/162 ,  F01D25/243 ,  F01D25/30 ,  F05D2230/232 ,  F05D2230/54 ,  F05D2230/60 ,  F05D2240/15 ,  Y10T29/49236 ,  Y10T29/4932

摘要： Manufacture of a gas turbine exhaust diffuser shell (40A/40B) to achieve a final cross-sectional shell geometry by forming an opening (76) in the shell to receive a strut shield collar (46); forming a compensating outward bowing (78) of the shell around the opening that departs from a desired final shell geometry in an amount and shape that compensates for a welding shrinkage when welding the collar in the opening; and welding the collar in the opening. This produces the desired shell geometry after the welding. The collar may be welded proximate an edge (74) of the diffuser shell, such as along an intersection of an axial plane with the diffuser shell. A multi-bolt flange (68) may be welded to or otherwise formed along this edge for assembling an annular exhaust diffuser duct (38A-B, 40A/B) in an exhaust section (20) of a gas turbine engine.

摘要翻译： 制造燃气轮机排气扩散器壳体（40A / 40B），以通过在壳体中形成开口（76）以接收支柱屏蔽套环（46）来实现最终横截面壳体几何形状; 形成围绕开口的壳体的补偿向外弯曲（78），该弯曲部分以一定量和形状偏离期望的最终壳体几何形状，该量和形状在焊接开口中的套环时补偿焊接收缩; 并将套环焊接在开口中。 这在焊接后产生所需的外壳几何形状。 套管可以在扩散器壳体的边缘（74）附近焊接，例如沿着与扩散器壳体的轴向平面的交点。 多个螺栓法兰（68）可以沿着该边缘焊接或以其他方式形成，用于在燃气涡轮发动机的排气部分（20）中组装环形排气扩散器管道（38A-B，40A / B）。