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1. 发明授权

US10107107B2 Gas turbine engine component with discharge slot having oval geometry 有权
公开(公告)号：US10107107B2
公开(公告)日：2018-10-23
申请号：US13598988
申请日：2012-08-30
申请人： Mark A. Boeke , Edwin Otero , Jeffrey J. DeGray , Tracy A. Propheter-Hinckley , Guillermo J. Fernandez , Sarah Riley
发明人： Mark A. Boeke , Edwin Otero , Jeffrey J. DeGray , Tracy A. Propheter-Hinckley , Guillermo J. Fernandez , Sarah Riley
IPC分类号： F01D5/18 , F01D9/06
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.

2. 发明申请

US20140000262A1 GAS TURBINE ENGINE COMPONENT WITH DISCHARGE SLOT HAVING OVAL GEOMETRY 审中-公开
标题翻译：气体涡轮发动机组件与排放槽具有OVAL几何
公开(公告)号：US20140000262A1
公开(公告)日：2014-01-02
申请号：US13598988
申请日：2012-08-30
申请人： Mark A. Boeke , Edwin Otero , Jeffrey J. DeGray , Tracy A. Propheter-Hinckley , Guillermo J. Fernandez , Sarah Riley
发明人： Mark A. Boeke , Edwin Otero , Jeffrey J. DeGray , Tracy A. Propheter-Hinckley , Guillermo J. Fernandez , Sarah Riley
IPC分类号： F01D9/02 , F02C3/06
CPC分类号： F01D5/187 , F01D9/065 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2240/81 , F05D2250/14
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘和后缘之间延伸的主体部分。前缘和后缘中的至少一个包括具有包括椭圆形几何形状的第一部分的至少一个排出槽。

3. 发明申请

US20130232991A1 AIRFOIL WITH IMPROVED INTERNAL COOLING CHANNEL PEDESTALS 有权
标题翻译：具有改进的内部冷却通道的AIRFOIL
公开(公告)号：US20130232991A1
公开(公告)日：2013-09-12
申请号：US13413969
申请日：2012-03-07
申请人： Edwin Otero
发明人： Edwin Otero
IPC分类号： F02C7/18 , F01D5/18
CPC分类号： F01D5/187 , F01D5/188 , F05D2240/304 , F05D2250/14 , F05D2250/231 , F05D2260/202 , F05D2260/2214
摘要： An airfoil for a turbine engine, the airfoil including a first side wall, a second side wall spaced apart from the first side wall, and an internal cooling channel formed between the first side wall and the second side wall. The internal cooling channel includes at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall. The internal cooling channel also includes a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end. At least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end.
摘要翻译：一种用于涡轮发动机的翼型件，所述翼型件包括第一侧壁，与第一侧壁间隔开的第二侧壁以及形成在第一侧壁和第二侧壁之间的内部冷却通道。内部冷却通道包括具有连接到第一侧壁的第一基座端和连接到第二侧壁的第二基座端的至少一个基座。内部冷却通道还包括在第一侧壁和第一基座端之间围绕第一基座端部的周边设置的第一圆角; 以及在所述第二侧壁和所述第二基座端之间围绕所述第二基座端部的周边设置的第二圆角。第一圆角和第二圆角中的至少一个包括在相应基座端的周边周围不均匀的轮廓。

4. 发明申请

US20130195665A1 TURBINE BLADE DAMPER SEAL 审中-公开
标题翻译：涡轮叶片阻尼器密封
公开(公告)号：US20130195665A1
公开(公告)日：2013-08-01
申请号：US13362552
申请日：2012-01-31
申请人： Daniel A. Snyder , Kyle Charles Lana , Jonathan Perry Sandoval , Scott Daniel Virkler , Jaimie Taraskevich , Edwin Otero
发明人： Daniel A. Snyder , Kyle Charles Lana , Jonathan Perry Sandoval , Scott Daniel Virkler , Jaimie Taraskevich , Edwin Otero
IPC分类号： F01D11/00 , F01D5/14
CPC分类号： F01D5/22 , F01D5/3007 , F01D11/006 , Y02T50/673
摘要： A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.
摘要翻译：根据本公开的示例性方面，容纳在位于平台和保持架阻尼器密封件之间的涡轮机叶片的空腔中的阻尼器密封件包括中心主体部分，其具有第一端部区域，相对的第二端部区域和宽度。阻尼器密封件还包括从中心主体部分的第一端部区域延伸的第一部分，并且第一部分的第一端部区域包括第一向外延伸的突片，其限定第一扩大部分，第一扩大部分具有大于中心主体部分和从中心主体部分的相对的第二端部区域延伸的第二部分。

5. 发明授权

US07441585B2 Apparatus and method for reducing operating stress in a turbine blade and the like 有权
公开(公告)号：US07441585B2
公开(公告)日：2008-10-28
申请号：US11654846
申请日：2007-01-18
申请人： Edwin Otero , Patrick Strong
发明人： Edwin Otero , Patrick Strong
IPC分类号： B22C9/10
CPC分类号： B22C9/04 , B22C9/10
摘要： A core for casting a metal part having a body with solid portions spaced apart by hollow portions. The body includes at least one support element extending between adjacent solid portions. The support element provides stiffness and strength for the casting core during the casting process. The support element has an optimized shape to prevent the core from fracturing during the casting process and to minimize operating stress in the metal part around the area formed by the support element.

6. 发明申请

US20070113999A1 Apparatus and method for reducing operating stress in a turbine blade and the like 有权
公开(公告)号：US20070113999A1
公开(公告)日：2007-05-24
申请号：US11654846
申请日：2007-01-18
申请人： Edwin Otero , Patrick Strong
发明人： Edwin Otero , Patrick Strong
IPC分类号： B22C9/10
CPC分类号： B22C9/04 , B22C9/10
摘要： A core for casting a metal part having a body with solid portions spaced apart by hollow portions. The body includes at least one support element extending between adjacent solid portions. The support element provides stiffness and strength for the casting core during the casting process. The support element has an optimized shape to prevent the core from fracturing during the casting process and to minimize operating stress in the metal part around the area formed by the support element.

7. 发明授权

US07216694B2 Apparatus and method for reducing operating stress in a turbine blade and the like 有权
公开(公告)号：US07216694B2
公开(公告)日：2007-05-15
申请号：US10763611
申请日：2004-01-23
申请人： Edwin Otero , Patrick Strong
发明人： Edwin Otero , Patrick Strong
IPC分类号： B22C9/00 , B22C9/10
CPC分类号： B22C9/04 , B22C9/10
摘要： A core for casting a metal part having a body with solid portions spaced apart by hollow portions. The body includes at least one support element extending between adjacent solid portions. The support element provides stiffness and strength for the casting core during the casting process. The support element has an optimized shape to prevent the core from fracturing during the casting process and to minimize operating stress in the metal part around the area formed by the support element.

8. 发明申请

US20070023157A1 APPARATUS AND METHOD FOR REDUCING OPERATING STRESS IN A TURBINE BLADE AND THE LIKE 有权
标题翻译：用于减少涡轮叶片中的操作应力的装置和方法
公开(公告)号：US20070023157A1
公开(公告)日：2007-02-01
申请号：US10763611
申请日：2004-01-23
申请人： Edwin Otero , Patrick Strong
发明人： Edwin Otero , Patrick Strong
IPC分类号： B22C9/04 , B22C9/10
CPC分类号： B22C9/04 , B22C9/10
摘要： A core for casting a metal part having a body with solid portions spaced apart by hollow portions. The body includes at least one support element extending between adjacent solid portions. The support element provides stiffness and strength for the casting core during the casting process. The support element has an optimized shape to prevent the core from fracturing during the casting process and to minimize operating stress in the metal part around the area formed by the support element.
摘要翻译：用于铸造具有主体的金属部件的芯部，其具有通过中空部分间隔开的实心部分。主体包括在相邻固体部分之间延伸的至少一个支撑元件。支撑元件在铸造过程中为铸芯提供刚度和强度。支撑元件具有优化的形状，以防止铸件在铸造过程中压裂，并使金属零件周围由支撑元件形成的区域的操作应力最小化。

9. 发明授权

US10113434B2 Turbine blade damper seal 有权
公开(公告)号：US10113434B2
公开(公告)日：2018-10-30
申请号：US13362552
申请日：2012-01-31
申请人： Daniel A. Snyder , Kyle Charles Lana , Jonathan Perry Sandoval , Scott Daniel Virkler , Jaimie Taraskevich , Edwin Otero
发明人： Daniel A. Snyder , Kyle Charles Lana , Jonathan Perry Sandoval , Scott Daniel Virkler , Jaimie Taraskevich , Edwin Otero
IPC分类号： F01D5/14 , F01D5/22 , F01D5/30 , F01D11/00
摘要： A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

10. 发明授权

US09297261B2 Airfoil with improved internal cooling channel pedestals 有权
标题翻译：翼型具有改进的内部冷却通道基座
公开(公告)号：US09297261B2
公开(公告)日：2016-03-29
申请号：US13413969
申请日：2012-03-07
申请人： Edwin Otero
发明人： Edwin Otero
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/188 , F05D2240/304 , F05D2250/14 , F05D2250/231 , F05D2260/202 , F05D2260/2214
摘要： An airfoil for a turbine engine, the airfoil including a first side wall, a second side wall spaced apart from the first side wall, and an internal cooling channel formed between the first side wall and the second side wall. The internal cooling channel includes at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall. The internal cooling channel also includes a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end. At least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end.
摘要翻译：一种用于涡轮发动机的翼型件，所述翼型件包括第一侧壁，与第一侧壁间隔开的第二侧壁以及形成在第一侧壁和第二侧壁之间的内部冷却通道。内部冷却通道包括具有连接到第一侧壁的第一基座端和连接到第二侧壁的第二基座端的至少一个基座。内部冷却通道还包括在第一侧壁和第一基座端之间围绕第一基座端部的周边设置的第一圆角; 以及在所述第二侧壁和所述第二基座端之间围绕所述第二基座端部的周边设置的第二圆角。第一圆角和第二圆角中的至少一个包括在相应基座端的周边周围不均匀的轮廓。

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