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1. 发明申请

US20120163994A1 GAS TURBINE ENGINE AND AIRFOIL 有权
标题翻译：气体涡轮发动机和气翼
公开(公告)号：US20120163994A1
公开(公告)日：2012-06-28
申请号：US13157420
申请日：2011-06-10
申请人： Okey Kwon
发明人： Okey Kwon
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , Y02T50/676
摘要： One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique turbine engine airfoil. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and airfoils. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
摘要翻译：本发明的一个实施例是独特的燃气涡轮发动机。另一个实施例是独特的涡轮发动机翼型。其他实施例包括用于燃气涡轮发动机和翼型的装置，系统，装置，硬件，方法和组合。本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。

2. 发明授权

US09085988B2 Gas turbine engine flow path member 有权
标题翻译：燃气涡轮发动机流路构件
公开(公告)号：US09085988B2
公开(公告)日：2015-07-21
申请号：US13335276
申请日：2011-12-22
申请人： Okey Kwon , Jeffrey F. Rhodes
发明人： Okey Kwon , Jeffrey F. Rhodes
IPC分类号： F01D25/12 , F01D5/20 , F01D5/18
CPC分类号： F01D5/187 , F01D5/20 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction.
摘要翻译：公开了一种燃气涡轮发动机流路构件，其包括能够接触涡轮发动机的表面的延伸端部。流路构件包括通过冷却流体以冷却延伸端部的开口。此外，流路构件可以使用各种方法制成。为了仅举出两个非限制性实例，流路构件可以铸造并且其可以是层压结构。

3. 发明申请

US20110052413A1 COOLED GAS TURBINE ENGINE AIRFLOW MEMBER 有权
标题翻译：冷却气体涡轮发动机气流构件
公开(公告)号：US20110052413A1
公开(公告)日：2011-03-03
申请号：US12550810
申请日：2009-08-31
申请人： Okey Kwon , Ted Freeman
发明人： Okey Kwon , Ted Freeman
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2250/70 , F05D2260/22141 , Y02T50/676
摘要： In one embodiment, a gas turbine engine turbine flow member is described that contains a passageway having a flow obstruction that forms a tortuous passageway for the passage of a cooling fluid. The flow obstruction can include flow structures disposed toward either side of the passageway. In one non-limiting embodiment a flow structure can have a V-shape, and in another non-limiting embodiment the flow structure can have an elongate shape. As cooling fluid flows through the passageway it is encouraged to flow up, down, and/or along portions of the flow obstruction.
摘要翻译：在一个实施例中，描述了一种燃气涡轮发动机涡轮流动构件，其包含具有形成用于冷却流体通过的曲折通道的流动阻塞的通道。流动阻塞可以包括朝向通道两侧设置的流动结构。在一个非限制性实施例中，流动结构可以具有V形，并且在另一个非限制性实施例中，流动结构可具有细长形状。当冷却流体流过通道时，鼓励其沿着流动障碍物的上下流动和/或沿其流动。

4. 发明申请

US20120189427A1 GAS TURBINE ENGINE FLOW PATH MEMBER 有权
标题翻译：气体涡轮发动机流路成员
公开(公告)号：US20120189427A1
公开(公告)日：2012-07-26
申请号：US13335276
申请日：2011-12-22
申请人： Okey Kwon , Jeffrey F. Rhodes
发明人： Okey Kwon , Jeffrey F. Rhodes
IPC分类号： F01D25/12 , F01D1/00
CPC分类号： F01D5/187 , F01D5/20 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction.
摘要翻译：公开了一种燃气涡轮发动机流路构件，其包括能够接触涡轮发动机的表面的延伸端部。流路构件包括通过冷却流体以冷却延伸端部的开口。此外，流路构件可以使用各种方法制成。为了仅举出两个非限制性实例，流路构件可以铸造并且其可以是层压结构。

5. 发明授权

US08961133B2 Gas turbine engine and cooled airfoil 有权
标题翻译：燃气涡轮发动机和冷却翼型
公开(公告)号：US08961133B2
公开(公告)日：2015-02-24
申请号：US13157420
申请日：2011-06-10
申请人： Okey Kwon
发明人： Okey Kwon
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D5/187 , F01D5/186 , Y02T50/676
摘要： An cooled airfoil for a gas turbine engine is disclosed. The airfoil includes an outer wall having a plurality cooling air exit openings and an inner wall having plurality of cooling air inlet openings. A plurality of flow migration dams extend between the inner wall and the outer wall to form a plurality of cooling passages and prevent cooling air from moving radially outward past the migration dams.
摘要翻译：公开了一种用于燃气涡轮发动机的冷却翼型件。翼型件包括具有多个冷却空气出口的外壁和具有多个冷却空气入口的内壁。多个流动迁移坝在内壁和外壁之间延伸以形成多个冷却通道并防止冷却空气径向向外移动通过迁移坝。

6. 发明授权

US08342797B2 Cooled gas turbine engine airflow member 有权
标题翻译：冷却燃气涡轮发动机气流构件
公开(公告)号：US08342797B2
公开(公告)日：2013-01-01
申请号：US12550810
申请日：2009-08-31
申请人： Okey Kwon , Ted Freeman
发明人： Okey Kwon , Ted Freeman
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2250/70 , F05D2260/22141 , Y02T50/676
摘要： In one embodiment, a gas turbine engine turbine flow member is described that contains a passageway having a flow obstruction that forms a tortuous passageway for the passage of a cooling fluid. The flow obstruction can include flow structures disposed toward either side of the passageway. In one non-limiting embodiment a flow structure can have a V-shape, and in another non-limiting embodiment the flow structure can have an elongate shape. As cooling fluid flows through the passageway it is encouraged to flow up, down, and/or along portions of the flow obstruction.
摘要翻译：在一个实施例中，描述了一种燃气涡轮发动机涡轮流动构件，其包含具有形成用于冷却流体通过的曲折通道的流动阻塞的通道。流动阻塞可以包括朝向通道两侧设置的流动结构。在一个非限制性实施例中，流动结构可以具有V形，并且在另一个非限制性实施例中，流动结构可具有细长形状。当冷却流体流过通道时，鼓励其沿着流动障碍物的上下流动和/或沿着其流动。

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