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1.发明授权公开(公告)号：US10156142B2
公开(公告)日：2018-12-18
申请号：US14950081
申请日：2015-11-24
Applicant: General Electric Company
Inventor： Ariel Caesar Prepena Jacala , Fred Thomas Willett, Jr.
Abstract: A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.
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2.发明申请公开(公告)号：US20170145830A1
公开(公告)日：2017-05-25
申请号：US14950081
申请日：2015-11-24
Applicant: General Electric Company
Inventor： Ariel Caesar Prepena Jacala , Fred Thomas Willett, JR.
CPC classification number: F01D5/18 , B23B2215/81 , F01D5/005 , F01D5/186 , F01D5/225 , F05D2220/32 , F05D2230/10 , F05D2230/11 , F05D2230/14 , F05D2230/21 , F05D2230/80 , F05D2240/305 , F05D2240/306 , F05D2250/52 , F05D2260/20 , F05D2260/202
Abstract: A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.
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公开(公告)号：US20160024930A1
公开(公告)日：2016-01-28
申请号：US14340059
申请日：2014-07-24
Applicant: General Electric Company
Inventor： Kelvin Rono Aaron , Craig Allen Bielek , Ross James Gustafson , Ariel Caesar Prepena Jacala , Spencer Aaron Kareff , Matthew Robert Piersall , John Franklin Ryman
IPC: F01D5/14
CPC classification number: F01D5/16 , F01D5/141 , F05D2240/305 , F05D2250/711 , F05D2260/941 , Y02T50/673
Abstract: A turbomachine airfoil includes a base portion and a blade portion extending from the base portion to a tip portion defining a radial span dimension. The blade portion includes a leading edge, a trailing edge, a pressure side and a suction side. An axial chord dimension is defined between the leading edge and the trailing edge. At least one protuberance is provided on the pressure side. The at least one protuberance extends from about 10% of the axial chord dimension to about 90% of the axial chord dimension.
Abstract translation: 涡轮机翼型包括基部和从基部延伸到限定径向跨度尺寸的尖端部的叶片部分。 叶片部分包括前缘，后缘，压力侧和吸力侧。 在前缘和后缘之间限定轴向弦的尺寸。 在压力侧设置至少一个凸起。 至少一个突起从轴向弦尺寸的约10％延伸到轴向弦尺寸的约90％。
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公开(公告)号：US20150204237A1
公开(公告)日：2015-07-23
申请号：US14157581
申请日：2014-01-17
Applicant: General Electric Company
IPC: F02C3/04
CPC classification number: F02C3/04 , F01D5/187 , F05D2240/304 , F05D2260/2212 , Y02T50/673 , Y02T50/676 , Y10T29/49318
Abstract: A turbine blade comprises a cooling passage defined between a pressure side wall and a suction side wall. A pin is disposed within the cooling passage and includes a first end that is connected to the pressure side wall and a second end that is connected to the suction side wall. A radially oriented fillet having a maximum radius of curvature value is disposed along a periphery of at least one of the first end or the second end within a region of peak steady state stress. An axially oriented fillet having a maximum radius of curvature value is disposed along a periphery of at least one of the first end or second end within a region of peak vibratory stress. The maximum radius of curvature value of the axially oriented fillet is greater than the maximum radius of curvature value of the radially oriented fillet.
Abstract translation: 涡轮叶片包括限定在压力侧壁和吸力侧壁之间的冷却通道。 销设置在冷却通道内，并且包括连接到压力侧壁的第一端和连接到吸力侧壁的第二端。 具有最大曲率半径值的径向取向的圆角在峰值稳态应力的区域内沿着第一端或第二端中的至少一个的周边设置。 具有最大曲率半径值的轴向取向的圆角沿尖峰振动应力的区域内的第一端或第二端中的至少一个的周边设置。 轴向取向圆角的最大曲率半径值大于径向取向圆角的最大曲率半径值。
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公开(公告)号：US10443408B2
公开(公告)日：2019-10-15
申请号：US14844545
申请日：2015-09-03
Applicant: General Electric Company
Inventor： Spencer A. Kareff , Brian Denver Potter , Ariel Caesar Prepena Jacala
IPC: F01D5/22
Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially aligned with and axially spaced from a second end portion and a retention pin that is coaxially aligned with and disposed between the first end portion and the second end portion. The retention pin couples the first end portion to the second end portion. The damper pin further includes a plurality of rings coaxially aligned with and disposed along the retention pin between the first end portion and the second end portion. The first end portion, the second end portion and the plurality of rings define a generally arcuate outer surface of the damper pin that is configured to contact with a groove defined between the adjacent turbine blades.
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Patent Agency Ranking
公开(公告)号：US09796048B2
公开(公告)日：2017-10-24
申请号：US14472483
申请日：2014-08-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Paul Lacy , Ariel Caesar Prepena Jacala , Srikanth Chandrudu Kottilingam , David Edward Schick
IPC: B23K26/342 , B28B1/00 , F28F13/06 , B33Y80/00 , F28F3/02 , F28F3/04 , F28F13/08 , F01D5/18 , F01D9/06 , B22F3/105 , B22F7/00 , C22C1/04 , C22C33/02 , B23K101/00
CPC classification number: B23K26/342 , B22F3/1055 , B22F7/004 , B22F2999/00 , B23K2101/001 , B28B1/001 , B33Y80/00 , C22C1/0433 , C22C33/0285 , F01D5/187 , F01D9/065 , F05D2240/80 , F05D2260/2212 , F28F3/022 , F28F3/04 , F28F13/06 , F28F13/08 , Y02P10/295 , B22F3/1115
Abstract: An article and a process of producing an article are provided. The article includes a base material, a cooling feature arrangement positioned on the base material, the cooling feature arrangement including an additive-structured material, and a cover material. The cooling feature arrangement is between the base material and the cover material. The process of producing the article includes manufacturing a cooling feature arrangement by an additive manufacturing technique, and then positioning the cooling feature arrangement between a base material and a cover material.
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公开(公告)号：US10385701B2
公开(公告)日：2019-08-20
申请号：US14844317
申请日：2015-09-03
Applicant: General Electric Company
Inventor： Spencer A. Kareff , Brian Denver Potter , Ariel Caesar Prepena Jacala
IPC: F01D5/22
Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially spaced from a second end portion and a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion. The first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin. The top portion is configured to contact with a groove defined between the adjacent turbine blades.
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8.发明申请公开(公告)号：US20190093483A1
公开(公告)日：2019-03-28
申请号：US16188636
申请日：2018-11-13
Applicant: General Electric Company
Inventor： Ariel Caesar Prepena Jacala , Fred Thomas Willett, JR.
Abstract: A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.
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公开(公告)号：US20170067350A1
公开(公告)日：2017-03-09
申请号：US14844545
申请日：2015-09-03
Applicant: General Electric Company
Inventor： Spencer A. Kareff , Brian Denver Potter , Ariel Caesar Prepena Jacala
IPC: F01D5/22
CPC classification number: F01D5/22 , F05D2220/32 , F05D2250/141 , Y02T50/672
Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially aligned with and axially spaced from a second end portion and a retention pin that is coaxially aligned with and disposed between the first end portion and the second end portion. The retention pin couples the first end portion to the second end portion. The damper pin further includes a plurality of rings coaxially aligned with and disposed along the retention pin between the first end portion and the second end portion. The first end portion, the second end portion and the plurality of rings define a generally arcuate outer surface of the damper pin that is configured to contact with a groove defined between the adjacent turbine blades.
Abstract translation: 用于阻尼连接到转子轴的相邻涡轮机叶片的阻尼器销包括与第二端部轴向对准并与其轴向间隔开的第一端部和与第一端部与第二端部同轴对准并且设置在第二端部之间的固定销 端部。 保持销将第一端部连接到第二端部。 阻尼销进一步包括沿第一端部和第二端部之间的保持销共同对准并设置的多个环。 所述第一端部，所述第二端部和所述多个环限定所述阻尼器销的大致弧形的外表面，所述外表面构造成与限定在所述相邻涡轮叶片之间的凹槽接触。
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公开(公告)号：US20170067348A1
公开(公告)日：2017-03-09
申请号：US14844317
申请日：2015-09-03
Applicant: General Electric Company
Inventor： Spencer A. Kareff , Brian Denver Potter , Ariel Caesar Prepena Jacala
IPC: F01D5/22
CPC classification number: F01D5/22 , F05D2220/32 , F05D2250/25 , Y02T50/671 , Y02T50/673
Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially spaced from a second end portion and a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion. The first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin. The top portion is configured to contact with a groove defined between the adjacent turbine blades.
Abstract translation: 用于阻尼与转子轴连接的相邻涡轮机叶片的阻尼器销包括与第二端部轴向隔开的第一端部和从第一端部的内表面轴向延伸到第二端部的内表面的弹簧构件 端部。 第一端部，弹簧构件和第二端部限定阻尼销的大致弓形顶部。 顶部构造成与限定在相邻涡轮叶片之间的凹槽接触。
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