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1. 发明授权

US08292581B2 Air cooled turbine blades and methods of manufacturing 有权
标题翻译：风冷式涡轮叶片及其制造方法
公开(公告)号：US08292581B2
公开(公告)日：2012-10-23
申请号：US11971459
申请日：2008-01-09
申请人： Kin C. Poon , Malak F. Malak , Rajiv Rana , Ardeshir Riahi , David H. Chou
发明人： Kin C. Poon , Malak F. Malak , Rajiv Rana , Ardeshir Riahi , David H. Chou
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , B22C9/10 , B22C9/103 , B22D25/00 , F01D5/081 , F01D5/087 , F01D5/20 , F05D2240/121 , F05D2240/303 , F05D2260/201 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： An air-cooled turbine blade and methods of manufacturing the blade are provided. The blade includes a suction side flow circuit formed within its interior and defined at least by an interior surface of a convex suction side wall, a pressure side flow circuit formed within the blade interior and defined at least by an interior surface of a concave pressure side wall, and a center flow circuit including a first section and a second section, the first section disposed between the suction side flow circuit and the pressure side flow circuit, and the second section in flow communication with the first section and a plurality of openings of a leading edge wall and defined at least partially by an interior surface of the leading edge wall.
摘要翻译：提供一种风冷式涡轮叶片及其制造方法。叶片包括形成在其内部并且至少由凸起的吸入侧壁的内表面限定的吸入侧流动回路，压力侧流动回路形成在叶片内部并且至少由凹入压力侧的内表面限定壁和包括第一部分和第二部分的中心流动回路，第一部分设置在吸力侧流动回路和压力侧流动回路之间，第二部分与第一部分流动连通，并且多个开口前缘壁并且至少部分地由前缘壁的内表面限定。

2. 发明申请

US20090175733A1 AIR COOLED TURBINE BLADES AND METHODS OF MANUFACTURING 有权
标题翻译：空气冷却涡轮叶片及其制造方法
公开(公告)号：US20090175733A1
公开(公告)日：2009-07-09
申请号：US11971459
申请日：2008-01-09
申请人： Kin C. Poon , Malak F. Malak , Rajiv Rana , Ardeshir Riahi , David H. Chou
发明人： Kin C. Poon , Malak F. Malak , Rajiv Rana , Ardeshir Riahi , David H. Chou
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/187 , B22C9/10 , B22C9/103 , B22D25/00 , F01D5/081 , F01D5/087 , F01D5/20 , F05D2240/121 , F05D2240/303 , F05D2260/201 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： An air-cooled turbine blade and methods of manufacturing the blade are provided. The blade includes a suction side flow circuit formed within its interior and defined at least by an interior surface of a convex suction side wall, a pressure side flow circuit formed within the blade interior and defined at least by an interior surface of a concave pressure side wall, and a center flow circuit including a first section and a second section, the first section disposed between the suction side flow circuit and the pressure side flow circuit, and the second section in flow communication with the first section and a plurality of openings of a leading edge wall and defined at least partially by an interior surface of the leading edge wall.
摘要翻译：提供一种风冷式涡轮叶片及其制造方法。叶片包括形成在其内部并且至少由凸起的吸入侧壁的内表面限定的吸入侧流动回路，压力侧流动回路形成在叶片内部并且至少由凹入压力侧的内表面限定壁和包括第一部分和第二部分的中心流动回路，第一部分设置在吸力侧流动回路和压力侧流动回路之间，第二部分与第一部分流动连通，并且多个开口前缘壁并且至少部分地由前缘壁的内表面限定。

3. 发明授权

US08206108B2 Turbine blades and methods of manufacturing 有权
标题翻译：涡轮叶片及制造方法
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。

4. 发明申请

US20090148305A1 TURBINE BLADES AND METHODS OF MANUFACTURING 有权
标题翻译：涡轮叶片及制造方法
公开(公告)号：US20090148305A1
公开(公告)日：2009-06-11
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，以限定吸力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。

5. 发明申请

US20080166225A1 Turbine blade tip and shroud clearance control coating system 有权
标题翻译：涡轮叶片尖端和护罩间隙控制涂层系统
公开(公告)号：US20080166225A1
公开(公告)日：2008-07-10
申请号：US11227780
申请日：2005-09-14
申请人： Thomas E. Strangman , Derek Raybould , Paul Chipko , Malak F. Malak
发明人： Thomas E. Strangman , Derek Raybould , Paul Chipko , Malak F. Malak
IPC分类号： F01D5/20
CPC分类号： F01D11/122 , C23C26/02 , C23C28/321 , C23C28/3215 , C23C28/324 , C23C28/345 , C23C28/3455 , C23C30/00 , F01D5/20 , F05D2300/21 , F05D2300/2118
摘要： A turbine blade tip and shroud clearance control coating system comprising an abrasive blade tip coating and an abradable shroud coating are provided. The abrasive layer may comprise abrasive particles of cubic zirconia, cubic hafnia or mixtures thereof, and the abradable layer may be a nanolaminate thermal barrier coating that is softer than the abrasive layer. The invention further provides an alternate coating system comprising an abradable blade tip coating and an abrasive shroud coating.
摘要翻译：提供了一种涡轮叶片尖端和护罩间隙控制涂层系统，其包括研磨刀片涂层和可磨损的护罩涂层。研磨层可以包括立方氧化锆，立方铪或其混合物的磨料颗粒，并且可磨损层可以是比磨料层软的纳米级隔热涂层。本发明还提供了一种替代涂层系统，其包括可磨损的刀片末端涂层和磨料罩涂层。

6. 发明授权

US07510370B2 Turbine blade tip and shroud clearance control coating system 有权
标题翻译：涡轮叶片尖端和护罩间隙控制涂层系统
公开(公告)号：US07510370B2
公开(公告)日：2009-03-31
申请号：US11227780
申请日：2005-09-14
申请人： Thomas E. Strangman , Derek Raybould , Paul Chipko , Malak F. Malak
发明人： Thomas E. Strangman , Derek Raybould , Paul Chipko , Malak F. Malak
IPC分类号： F01D5/20
CPC分类号： F01D11/122 , C23C26/02 , C23C28/321 , C23C28/3215 , C23C28/324 , C23C28/345 , C23C28/3455 , C23C30/00 , F01D5/20 , F05D2300/21 , F05D2300/2118
摘要： A turbine blade tip and shroud clearance control coating system comprising an abrasive blade tip coating and an abradable shroud coating are provided. The abrasive layer may comprise abrasive particles of cubic zirconia, cubic hafnia or mixtures thereof, and the abradable layer may be a nanolaminate thermal barrier coating that is softer than the abrasive layer. The invention further provides an alternate coating system comprising an abradable blade tip coating and an abrasive shroud coating.
摘要翻译：提供了一种涡轮叶片尖端和护罩间隙控制涂层系统，其包括研磨刀片涂层和可磨损的护罩涂层。研磨层可以包括立方氧化锆，立方铪或其混合物的磨料颗粒，并且可磨损层可以是比磨料层软的纳米级隔热涂层。本发明还提供了一种替代涂层系统，其包括可磨损的刀片末端涂层和磨料罩涂层。

7. 发明授权

US07473072B2 Turbine blade tip and shroud clearance control coating system 有权
标题翻译：涡轮叶片尖端和护罩间隙控制涂层系统
公开(公告)号：US07473072B2
公开(公告)日：2009-01-06
申请号：US11218074
申请日：2005-08-31
申请人： Malak F. Malak , Derek Raybould , Thomas E. Strangman
发明人： Malak F. Malak , Derek Raybould , Thomas E. Strangman
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , C23C28/00 , C23C28/321 , C23C28/345 , C23C28/3455 , C23C28/347 , C23C28/42 , F01D11/125
摘要： A turbine blade tip and shroud clearance control coating system comprising a dense abrasive blade tip layer and an abradable shroud layer are provided. The dense abrasive coating may comprise cubic zirconia, hafnia or mixtures thereof and the abradable layer may be a nanolaminate thermal barrier coating that is softer than the dense abrasive layer.
摘要翻译：提供了一种包括致密研磨刀片尖端层和可磨损护罩层的涡轮叶片尖端和护罩间隙控制涂层系统。致密的磨料涂层可以包括立方氧化锆，铪或其混合物，并且可磨损层可以是比致密研磨层软的纳米级热障涂层。

8. 发明授权

US07448433B2 Rapid prototype casting 有权
标题翻译：快速原型铸造
公开(公告)号：US07448433B2
公开(公告)日：2008-11-11
申请号：US10949082
申请日：2004-09-24
申请人： Milton Ortiz , Malak F. Malak , Steve H. Halfmann
发明人： Milton Ortiz , Malak F. Malak , Steve H. Halfmann
IPC分类号： B22C9/00
CPC分类号： B22C9/04 , B22C7/00 , B22C9/24 , B33Y80/00
摘要： Methods for rapid prototype casting metal components, wherein the metal components are cast in a secondary ceramic mold, the secondary ceramic mold is cast in a primary mold, and the primary mold is formed by rapid prototyping or rapid manufacturing. The secondary ceramic mold may comprise a one-piece integral shell and core(s), and the metal components may have at least one hollow portion or void therein, such as a hollow airfoil for a gas turbine engine.
摘要翻译：用于快速成型铸造金属部件的方法，其中金属部件在二次陶瓷模具中铸造，二次陶瓷模具铸造在初级模具中，并且初级模具通过快速成型或快速制造形成。二次陶瓷模具可以包括一体式的整体壳体和芯部，并且金属部件可以在其中具有至少一个中空部分或空隙，例如用于燃气涡轮发动机的中空翼型件。

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