公开(公告)号：US07543633B2

公开(公告)日：2009-06-09

申请号：US11392284

申请日：2006-03-29

申请人： Donn J. Brown ,  Brown Lyle Wilson ,  Matthew R. Porter ,  Bruce Proctor

发明人： Donn J. Brown ,  Brown Lyle Wilson ,  Matthew R. Porter ,  Bruce Proctor

IPC分类号： E21B43/38

CPC分类号： E21B43/126 ,  E21B43/38

摘要： A progressing cavity pump is located within a well and has a gas separator for separating gas before reaching the pump. The pump has a rotor that is driven by a string of rods extending to the surface. A drive shaft for the gas separator is coupled to the rotor during pumping operation both for axial as well as rotational movement. The rotor assembly, when lowered through the tubing, stabs into engagement with the drive shaft of the gas separator in one version. In another version, the gas separator drive shaft is lowered through the tubing with the rotor and stabs into a hub sleeve in the gas separator.

摘要翻译： 进气腔泵位于井内，并具有用于在到达泵之前分离气体的气体分离器。 泵具有由延伸到表面的一串杆驱动的转子。 用于气体分离器的驱动轴在用于轴向和旋转运动的泵送操作期间联接到转子。 转子组件在通过管子下降时，以一种方式与气体分离器的驱动轴相接合。 在另一个版本中，气体分离器驱动轴通过具有转子的管子下降，并且刺入气体分离器中的轮毂套筒中。

公开(公告)号：US20150143815A1

公开(公告)日：2015-05-28

申请号：US14087060

申请日：2013-11-22

申请人： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III ,  Daniel F. Riveros

发明人： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III ,  Daniel F. Riveros

IPC分类号： F01D25/30

CPC分类号： F01D25/30 ,  F01D25/28 ,  F02C7/20 ,  Y10T29/49231

摘要： An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

摘要翻译： 具有模块化结构的集成单件式排气系统（SPEX），有助于设计更改，提高空气动力学，结构完整性或可维护性。 SPEX定义了花键或弯曲的排气路径表面，例如模拟曲线的一系列圆柱形和截头圆锥形截面。 构造的部分可以包括：（i）由圆锥形部分制造的尾锥组件，其锥形下游到减小的直径; 或（ii）与一排或多排涡轮支架轴向对准的面积划线的横截面; 或两个功能。 模块化的内径和外径入口唇缘增强了最后一排叶片和SPEX之间的过渡流，并增强了结构完整性。 模块化支柱套环在SPEX环形内径和外径流动表面之间具有大的半径分布，用于增强气流和恒定厚度的壁，以实现均匀的热传递和热膨胀。 扇形安装法兰增强了结构的完整性和使用寿命。

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：US09664062B2

公开(公告)日：2017-05-30

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： F01D9/04 ,  F01D25/14 ,  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.

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：US09644497B2

公开(公告)日：2017-05-09

申请号：US14087040

申请日：2013-11-22

申请人： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III

发明人： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III

IPC分类号： F01D25/30 ,  F01D25/24 ,  F01D9/04 ,  F01D11/00 ,  F01D25/16 ,  F01D5/14

CPC分类号： F01D25/30 ,  F01D5/143 ,  F01D9/041 ,  F01D11/001 ,  F01D25/162 ,  F01D25/243 ,  F05D2250/15

摘要： An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

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：US20150143816A1

公开(公告)日：2015-05-28

申请号：US14087086

申请日：2013-11-22

申请人： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III ,  Daniel F. Riveros

发明人： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III ,  Daniel F. Riveros

IPC分类号： F01D25/30

CPC分类号： F01D25/30 ,  F01D9/041 ,  F01D25/162 ,  F01D25/243 ,  F02K1/04 ,  F02K1/80 ,  F05D2230/51 ,  F05D2250/232

摘要： An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

摘要翻译： 具有模块化结构的集成单件式排气系统（SPEX），有助于设计更改，提高空气动力学，结构完整性或可维护性。 SPEX定义了花键或弯曲的排气路径表面，例如模拟曲线的一系列圆柱形和截头圆锥形截面。 构造的部分可以包括：（i）由圆锥形部分制造的尾锥组件，其锥形下游到减小的直径; 或（ii）与一排或多排涡轮支架轴向对准的面积划线的横截面; 或两个功能。 模块化的内径和外径入口唇缘增强了最后一排叶片和SPEX之间的过渡流，并增强了结构完整性。 模块化支柱套环在SPEX环形内径和外径流动表面之间具有大的半径分布，用于增强气流和恒定厚度的壁，以实现均匀的热传递和热膨胀。 扇形安装法兰增强了结构的完整性和使用寿命。

公开(公告)号：US20150143813A1

公开(公告)日：2015-05-28

申请号：US14087040

申请日：2013-11-22

申请人： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III

发明人： Anil L. Salunkhe ,  John A. Orosa ,  Yevgeniy Shteyman ,  Matthew R. Porter ,  Lijuan Han ,  Matthew J. Delisa, III

IPC分类号： F01D25/30

CPC分类号： F01D25/30 ,  F01D5/143 ,  F01D9/041 ,  F01D11/001 ,  F01D25/162 ,  F01D25/243 ,  F05D2250/15

摘要： An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

摘要翻译： 具有模块化结构的集成单件式排气系统（SPEX），有助于设计更改，提高空气动力学，结构完整性或可维护性。 SPEX定义了花键或弯曲的排气路径表面，例如模拟曲线的一系列圆柱形和截头圆锥形截面。 构造的部分可以包括：（i）由圆锥形部分制造的尾锥组件，其锥形下游到减小的直径; 或（ii）与一排或多排涡轮支架轴向对准的面积划线的横截面; 或两个功能。 模块化的内径和外径入口唇缘增强了最后一排叶片和SPEX之间的过渡流，并增强了结构完整性。 模块化支柱套环在SPEX环形内径和外径流动表面之间具有大的半径分布，用于增强气流和恒定厚度的壁，以实现均匀的热传递和热膨胀。 扇形安装法兰增强了结构的完整性和使用寿命。

公开(公告)号：US20150044039A1

公开(公告)日：2015-02-12

申请号：US13961920

申请日：2013-08-08

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： F01D25/30

CPC分类号： F01D25/30 ,  B23K31/003 ,  B23K33/006 ,  B23K2101/001 ,  F01D25/162 ,  F05D2230/232 ,  F05D2250/15 ,  Y10T29/49398

摘要： Manufacture of an arcuate diffuser shell (38A/38B) assembled from an axially forward portion (38A) and an axially aft portion (38B), the two portions welded to respective sides of an arcuate flange (58A) via two respective pairs of circumferential welds (70A/70B and 72A/72B or 80/84 and 82/86 or 80/88 and 82/90). Each pair of welds comprises first and second welds on opposed surfaces (58, 74) of the shell. The first and second welds compensate each other with respect to welding process shrinkage, eliminating weld warping (68) of the shell. The first and second welds may have equal cross sectional areas or equal masses over a circumferential span of the flange.

摘要翻译： 制造从轴向前部（38A）和轴向后部（38B）组装的弧形扩散器外壳（38A / 38B），两个部分通过两对相应的圆周焊接焊接到弓形凸缘（58A）的相应侧面 （70A / 70B和72A / 72B或80/84和82/86或80/88和82/90）。 每对焊缝包括在壳的相对表面（58,74）上的第一和第二焊缝。 第一和第二焊缝相对于焊接工艺收缩相互补偿，消除了外壳的焊缝翘曲（68）。 第一和第二焊缝在凸缘的圆周跨度上可以具有相等的横截面面积或相等的质量。