公开(公告)号：US07625178B2

公开(公告)日：2009-12-01

申请号：US11513759

申请日：2006-08-30

申请人： Mark C. Morris ,  George W. Wolfmeyer ,  Luis A. Tapia ,  Vivek Agarwal ,  Kin Poon ,  Jason C. Smoke ,  William C. Baker ,  Henry M. Armstrong

发明人： Mark C. Morris ,  George W. Wolfmeyer ,  Luis A. Tapia ,  Vivek Agarwal ,  Kin Poon ,  Jason C. Smoke ,  William C. Baker ,  Henry M. Armstrong

IPC分类号： F01D5/08

CPC分类号： F01D5/187 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  F05D2230/211 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49341

摘要： An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.

摘要翻译： 本发明提供一种风冷式涡轮机叶片，其具有由凸形的吸入侧壁，凹入压力侧壁，前缘，后缘，根部和尖端形成的翼面形状，所述壁和端部各自包括内表面 其限定具有根部的内部，所述后缘包括形成在其上的多个狭槽。 叶片包括形成在其中的吸入侧流动回路，包括前进和后部流动回路。 叶片还包括尖端流动回路，其沿着尖端内表面延伸到至少一个后缘槽，并且包括第一和第二开口，第一开口与吸力侧向前流动回路出口流动连通， 打开与吸入侧后流道的交叉孔流动连通。 还提供了制造叶片的方法。

公开(公告)号：US20080056908A1

公开(公告)日：2008-03-06

申请号：US11513759

申请日：2006-08-30

申请人： Mark C. Morris ,  George W. Wolfmeyer ,  Luis A. Tapia ,  Vivek Agarwal ,  Kin Poon ,  Jason C. Smoke ,  William C. Baker ,  Henry M. Armstrong

发明人： Mark C. Morris ,  George W. Wolfmeyer ,  Luis A. Tapia ,  Vivek Agarwal ,  Kin Poon ,  Jason C. Smoke ,  William C. Baker ,  Henry M. Armstrong

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  F05D2230/211 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49341

摘要： An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.

摘要翻译： 本发明提供一种风冷式涡轮机叶片，其具有由凸形的吸入侧壁，凹入压力侧壁，前缘，后缘，根部和尖端形成的翼面形状，所述壁和端部各自包括内表面 其限定具有根部的内部，所述后缘包括形成在其上的多个狭槽。 叶片包括形成在其中的吸入侧流动回路，包括前进和后部流动回路。 叶片还包括尖端流动回路，其沿着尖端内表面延伸到至少一个后缘槽，并且包括第一和第二开口，第一开口与吸力侧向前流动回路出口流动连通， 打开与吸入侧后流道的交叉孔流动连通。 还提供了制造叶片的方法。

公开(公告)号：US20110299972A1

公开(公告)日：2011-12-08

申请号：US12794433

申请日：2010-06-04

申请人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

发明人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

IPC分类号： F01D1/00

CPC分类号： F01D3/025

摘要： An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.

摘要翻译： 公开了一种用于燃气涡轮发动机的叶轮或轴向级压缩机盘背面罩。 背面护罩包括但不限于具有表面的大致漏斗形的主体。 基本上漏斗形的主体构造成与叶轮或轴向级压缩机盘基本上同轴地静态地安装到燃气涡轮发动机。 当基本上漏斗形的主体与叶轮或轴向级压缩机盘同轴地安装并且与其轴向间隔开时，叶轮或轴向级压缩机盘的表面和背面形成空腔，该空腔将气流部分引导到涡轮机。 气流部分具有切向速度，并且背面护罩的表面中的凹槽通常横向于切向速度定向，以至少部分地干扰气流部分，从而影响空腔中的静压力。

公开(公告)号：US07093418B2

公开(公告)日：2006-08-22

申请号：US10830265

申请日：2004-04-21

申请人： Mark C. Morris ,  Alan G. Tiltman ,  Kin Poon ,  Bradley A. Volkmann

发明人： Mark C. Morris ,  Alan G. Tiltman ,  Kin Poon ,  Bradley A. Volkmann

IPC分类号： F02C7/28 ,  F02C7/06 ,  F02G3/00

CPC分类号： F01D25/125 ,  F01D25/18 ,  F02C7/28 ,  F05D2240/50 ,  F05D2260/231 ,  Y02T50/675

摘要： A gas turbine engine is configured to use relatively cool, low pressure air discharged from a low pressure compressor to supply buffer air to lubrication sump seals. The engine is further configured such that the lubrication sump is thermally layered by isolating relatively hot, high pressure compressor air from the sump by utilizing a warm vent mixing cavity, which is located radially between of the hot high pressure compressor air and the cool buffer air, which is located in a buffer cavity between the vent cavity and the sump.

摘要翻译： 燃气涡轮发动机被配置为使用从低压压缩机排放的相对冷却的低压空气将缓冲空气供应到润滑油底壳密封件。 发动机进一步构造成使得通过利用位于热高压压缩机空气和冷却缓冲空气之间的温热排气混合空腔来分离相对较热的高压压缩机空气，从而将润滑油池分层 ，其位于通气腔和贮槽之间的缓冲腔中。

公开(公告)号：US08801364B2

公开(公告)日：2014-08-12

申请号：US12794433

申请日：2010-06-04

申请人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

发明人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

IPC分类号： F01D3/00

CPC分类号： F01D3/025

摘要： An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.

摘要翻译： 公开了一种用于燃气涡轮发动机的叶轮或轴向级压缩机盘背面罩。 背面护罩包括但不限于具有表面的大致漏斗形的主体。 基本上漏斗形的主体构造成与叶轮或轴向级压缩机盘基本上同轴地静态地安装到燃气涡轮发动机。 当基本上漏斗形的主体与叶轮或轴向级压缩机盘同轴地安装并且与其轴向间隔开时，叶轮或轴向级压缩机盘的表面和背面形成空腔，该空腔将气流部分引导到涡轮机。 气流部分具有切向速度，并且背面护罩的表面中的凹槽通常横向于切向速度定向，以至少部分地干扰气流部分，从而影响空腔中的静压力。

公开(公告)号：US08292587B2

公开(公告)日：2012-10-23

申请号：US12338746

申请日：2008-12-18

申请人： Kin Poon ,  Rajiv Rana ,  Bob Mitlin ,  Ardeshir Riahi ,  David Chou ,  Steve Halfmann ,  Frank Mignano

发明人： Kin Poon ,  Rajiv Rana ,  Bob Mitlin ,  Ardeshir Riahi ,  David Chou ,  Steve Halfmann ,  Frank Mignano

IPC分类号： F01D11/00

CPC分类号： F01D5/187 ,  F01D5/225 ,  F05D2230/60 ,  F05D2240/81 ,  Y02T50/676

摘要： A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.

摘要翻译： 涡轮叶片组件包括翼型件，平台和第一盖板。 中心流动路径延伸穿过与从平台的第一侧延伸的翼型件的内部冷却回路连通的平台。 平台的第二侧与第一侧相对的平台。 平台的边缘在第一和第二侧面之间延伸，并且第一通道形成在第一和第二侧之间，并且包括第一入口和第一出口。 第一通道从中心流动路径延伸到平台边缘，并且第一凹槽形成在平台的第二侧上，并且从第一通道的第一出口朝向平台的边缘延伸。 第一盖板设置在覆盖第一凹槽的平台的第二侧上。

公开(公告)号：US08206108B2

公开(公告)日：2012-06-26

申请号：US11953489

申请日：2007-12-10

申请人： Ardeshir Riahi ,  Kin Poon ,  David Chou ,  Malak F. Malak

发明人： Ardeshir Riahi ,  Kin Poon ,  David Chou ,  Malak F. Malak

IPC分类号： F01D5/18

CPC分类号： F01D5/147 ,  F01D5/18 ,  F01D5/20 ,  F05D2230/10 ,  F05D2230/211 ,  F05D2240/307 ,  Y02T50/676

摘要： A turbine blade includes a convex suction side wall, a concave pressure side wall, a tip wall, an internal cooling circuit, and a plurality of tip edge channels. The tip wall is recessed from a first tip edge of the suction side wall and a second tip edge of the concave pressure side wall to define a suction side wall tip section and a pressure side wall tip section, and the suction side wall tip section is shorter than the pressure side wall tip section. The internal cooling circuit is formed at least partially between the convex suction side wall, the concave pressure side wall, and the tip wall. The plurality of tip edge channels formed through the first tip edge of the convex suction side wall extend to the internal cooling circuit. Methods of manufacturing turbine blades are also provided.

摘要翻译： 涡轮叶片包括凸吸入侧壁，凹压侧壁，尖端壁，内部冷却回路和多个尖端边缘通道。 顶壁从吸力侧壁的第一顶端边缘和凹压侧壁的第二顶端边缘凹入，以限定吸入侧壁顶端部分和压力侧壁顶端部分，并且吸力侧壁顶端部分是 比压力侧壁末端部分短。 内部冷却回路至少部分形成在凸吸入侧壁，凹压侧壁与顶壁之间。 通过凸形吸入侧壁的第一顶端边缘形成的多个尖端边缘通道延伸到内部冷却回路。 还提供制造涡轮叶片的方法。

公开(公告)号：US20100158700A1

公开(公告)日：2010-06-24

申请号：US12338746

申请日：2008-12-18

申请人： Kin Poon ,  Rajiv Rana ,  Bob Mitlin ,  Ardeshir Riahi ,  David Chou ,  Steve Halfmann ,  Frank Mignano

发明人： Kin Poon ,  Rajiv Rana ,  Bob Mitlin ,  Ardeshir Riahi ,  David Chou ,  Steve Halfmann ,  Frank Mignano

IPC分类号： F01D5/18 ,  B22D19/08

CPC分类号： F01D5/187 ,  F01D5/225 ,  F05D2230/60 ,  F05D2240/81 ,  Y02T50/676

摘要： A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.

摘要翻译： 涡轮叶片组件包括翼型件，平台和第一盖板。 中心流动路径延伸穿过与从平台的第一侧延伸的翼型件的内部冷却回路连通的平台。 平台的第二侧与第一侧相对的平台。 平台的边缘在第一和第二侧面之间延伸，并且第一通道形成在第一和第二侧之间，并且包括第一入口和第一出口。 第一通道从中心流动路径延伸到平台边缘，并且第一凹槽形成在平台的第二侧上，并且从第一通道的第一出口朝向平台的边缘延伸。 第一盖板设置在覆盖第一凹槽的平台的第二侧上。

公开(公告)号：US20050235651A1

公开(公告)日：2005-10-27

申请号：US10830265

申请日：2004-04-21

申请人： Mark Morris ,  Alan Tiltman ,  Kin Poon ,  Bradley Volkmann

发明人： Mark Morris ,  Alan Tiltman ,  Kin Poon ,  Bradley Volkmann

IPC分类号： F01D25/12 ,  F01D25/18 ,  F02C7/06 ,  F02C7/28

CPC分类号： F01D25/125 ,  F01D25/18 ,  F02C7/28 ,  F05D2240/50 ,  F05D2260/231 ,  Y02T50/675

摘要： A gas turbine engine is configured to use relatively cool, low pressure air discharged from a low pressure compressor to supply buffer air to lubrication sump seals. The engine is further configured such that the lubrication sump is thermally layered by isolating relatively hot, high pressure compressor air from the sump by utilizing a warm vent mixing cavity, which is located radially between of the hot high pressure compressor air and the cool buffer air, which is located in a buffer cavity between the vent cavity and the sump.

摘要翻译： 燃气涡轮发动机被配置为使用从低压压缩机排放的相对冷却的低压空气将缓冲空气供应到润滑油底壳密封件。 发动机进一步构造成使得通过利用位于热高压压缩机空气和冷却缓冲空气之间的温热排气混合空腔来分离相对较热的高压压缩机空气，从而将润滑油池分层 ，其位于通气腔和贮槽之间的缓冲腔中。

公开(公告)号：US06478535B1

公开(公告)日：2002-11-12

申请号：US09848844

申请日：2001-05-04

申请人： Vincent Chung ,  Milton Ortiz ,  Kin Poon

发明人： Vincent Chung ,  Milton Ortiz ,  Kin Poon

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676

摘要： A thin wall cooling system has multiple in-wall channels traversing a thin wall structure such as the wall of a gas turbine engine blade or vane. The blade has a hollow interior that may be divided into multiple cavities. Coolant is introduced into an entry opening of each in-wall channel and then discharged through exit openings into the vane cavities. The coolant then exits the cavities by through wall channels to discharge the coolant to form a cool air film on the external surface of the blade. This combination allows improved cooling control for structures that experience an elevated temperature environment, as for example, the flow of hot gas across the exterior surface of a gas turbine engine blade.