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公开(公告)号：US20170175573A1
公开(公告)日：2017-06-22
申请号：US14971478
申请日：2015-12-16
Applicant: General Electric Company
Inventor： Marc Lionel Benjamin , Benjamin Paul Lacy , Dipankar Pal , San Jason Nguyen
CPC classification number: F01D25/12 , F01D9/00 , F01D11/005 , F01D11/04 , F01D11/24 , F01D25/246 , F02C3/04 , F05D2230/12 , F05D2230/237 , F05D2240/11 , F05D2250/185 , F05D2260/204 , Y02T50/676
Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes at least one channel disposed within the body, wherein the at least one channel includes a first portion extending from upstream of the trailing edge towards the trailing edge in a first direction from the leading edge to the trailing edge, a second portion extending from the trailing edge to upstream of the trailing edge in a second direction from the trailing edge to the leading edge, and a third portion extending from upstream of the trailing edge towards the trailing edge in the first direction.
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公开(公告)号：US20140341720A1
公开(公告)日：2014-11-20
申请号：US13893729
申请日：2013-05-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dipankar Pal , Robert Walter Coign , Gary Michael Itzel , Kevin Thomas McGovern , Christopher Donald Porter
IPC: F01D25/00
CPC classification number: F01D11/005 , F01D11/006 , F05D2240/57
Abstract: Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.
Abstract translation: 公开了被配置为密封涡轮机的固定部件之间的接口/间隙并且在涡轮机操作期间操纵涡轮机部分周围的冷却剂流的系统和装置。 在一个实施例中，密封元件包括：成形为朝向涡轮的加压腔定向的第一表面; 第二表面，其定向成基本上与第一表面相对并且成形为密封地接合静态部件的接触表面; 以及设置在所述第二表面中的第一组角特征，所述第一组角特征将所述加压腔和所述涡轮的流路流体连接。
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公开(公告)号：US20140130514A1
公开(公告)日：2014-05-15
申请号：US13675281
申请日：2012-11-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dipankar Pal
Abstract: A turbine nozzle having a non-linear cooling conduit is disclosed. In one embodiment, a turbine nozzle includes: an airfoil, at least one endwall adjacent the airfoil, and a fillet region connecting the airfoil and the at least one endwall, the fillet region including an outer surface. The turbine nozzle also includes a non-linear cooling conduit located within the fillet region and adjacent the outer surface of the fillet region, the non-linear cooling conduit allows fluid flow through the fillet region. The non-linear cooling conduit spans substantially along an axial length of the airfoil between a leading edge of the airfoil and a trailing edge of the airfoil. Additionally, the non-linear cooling conduit includes an arc profile substantially similar to an arc profile of the airfoil.
Abstract translation: 公开了一种具有非线性冷却导管的涡轮喷嘴。 在一个实施例中，涡轮喷嘴包括：翼型件，与翼型件相邻的至少一个端壁和连接翼型件和至少一个端壁的圆角区域，该圆角区域包括外表面。 涡轮喷嘴还包括位于圆角区域内并邻近圆角区域的外表面的非线性冷却导管，非线性冷却导管允许流体流过圆角区域。 非线性冷却导管基本上沿翼型的轴向长度在翼型的前缘和翼型的后缘之间跨越。 另外，非线性冷却导管包括基本上类似于翼型的弧形轮廓的弧形轮廓。
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Patent Agency Ranking
4.发明申请公开(公告)号：US20140130354A1
公开(公告)日：2014-05-15
申请号：US13675293
申请日：2012-11-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dipankar Pal , Benjamin Paul Lacy
CPC classification number: B23P15/02 , B23H9/10 , B23H9/14 , F01D5/186 , F01D5/187 , Y10T29/4932 , Y10T29/49323 , Y10T408/03
Abstract: A method for manufacturing a turbine nozzle having a non-linear cooling conduit is disclosed. In one embodiment, a method includes: providing a turbine nozzle. The turbine nozzle includes: an airfoil, a cavity, having an inner surface, located within the airfoil, at least one endwall adjacent the airfoil, and a fillet region connecting the airfoil and the endwall. The fillet region also includes an outer surface. The method also includes: forming a non-linear cooling conduit within the fillet region and adjacent the outer surface of the fillet region of the turbine nozzle. The forming of the non-linear cooling conduit includes curved drilling through a portion of the outer surface of the fillet region of the turbine nozzle.
Abstract translation: 公开了一种用于制造具有非线性冷却导管的涡轮喷嘴的方法。 在一个实施例中，一种方法包括：提供涡轮喷嘴。 涡轮喷嘴包括：翼型件，空腔，具有内表面，位于翼型内，邻近翼型的至少一个端壁和连接翼型件和端壁的圆角区域。 圆角区域还包括外表面。 该方法还包括：在圆角区域内和邻近涡轮喷嘴的圆角区域的外表面处形成非线性冷却导管。 非线性冷却导管的形成包括通过涡轮喷嘴的圆角区域的外表面的一部分的弯曲钻孔。
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公开(公告)号：US09200534B2
公开(公告)日：2015-12-01
申请号：US13675281
申请日：2012-11-13
Applicant: General Electric Company
Inventor： Dipankar Pal
Abstract: A turbine nozzle having a non-linear cooling conduit is disclosed. In one embodiment, a turbine nozzle includes: an airfoil, at least one endwall adjacent the airfoil, and a fillet region connecting the airfoil and the at least one endwall, the fillet region including an outer surface. The turbine nozzle also includes a non-linear cooling conduit located within the fillet region and adjacent the outer surface of the fillet region, the non-linear cooling conduit allows fluid flow through the fillet region. The non-linear cooling conduit spans substantially along an axial length of the airfoil between a leading edge of the airfoil and a trailing edge of the airfoil. Additionally, the non-linear cooling conduit includes an arc profile substantially similar to an arc profile of the airfoil.
Abstract translation: 公开了一种具有非线性冷却导管的涡轮喷嘴。 在一个实施例中，涡轮喷嘴包括：翼型件，与翼型件相邻的至少一个端壁和连接翼型件和至少一个端壁的圆角区域，该圆角区域包括外表面。 涡轮喷嘴还包括位于圆角区域内并邻近圆角区域的外表面的非线性冷却导管，非线性冷却导管允许流体流过圆角区域。 非线性冷却导管基本上沿翼型的轴向长度在翼型的前缘和翼型的后缘之间跨越。 另外，非线性冷却导管包括基本上类似于翼型的弧形轮廓的弧形轮廓。
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公开(公告)号：US09581036B2
公开(公告)日：2017-02-28
申请号：US13893729
申请日：2013-05-14
Applicant: General Electric Company
Inventor： Dipankar Pal , Robert Walter Coign , Gary Michael Itzel , Kevin Thomas McGovern , Christopher Donald Porter
IPC: F01D11/00
CPC classification number: F01D11/005 , F01D11/006 , F05D2240/57
Abstract: Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.
Abstract translation: 公开了被配置为密封涡轮机的固定部件之间的接口/间隙并且在涡轮机操作期间操纵涡轮机部分周围的冷却剂流的系统和装置。 在一个实施例中，密封元件包括：成形为朝向涡轮的加压腔定向的第一表面; 第二表面，其定向成基本上与第一表面相对并且成形为密封地接合静态部件的接触表面; 以及设置在所述第二表面中的第一组角特征，所述第一组角特征将所述加压腔和所述涡轮的流路流体连接。
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公开(公告)号：US10309252B2
公开(公告)日：2019-06-04
申请号：US14971478
申请日：2015-12-16
Applicant: General Electric Company
Inventor： Marc Lionel Benjamin , Benjamin Paul Lacy , Dipankar Pal , San Jason Nguyen
Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes at least one channel disposed within the body, wherein the at least one channel includes a first portion extending from upstream of the trailing edge towards the trailing edge in a first direction from the leading edge to the trailing edge, a second portion extending from the trailing edge to upstream of the trailing edge in a second direction from the trailing edge to the leading edge, and a third portion extending from upstream of the trailing edge towards the trailing edge in the first direction.
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8.发明授权公开(公告)号：US09156114B2
公开(公告)日：2015-10-13
申请号：US13675293
申请日：2012-11-13
Applicant: General Electric Company
Inventor： Dipankar Pal , Benjamin Paul Lacy
CPC classification number: B23P15/02 , B23H9/10 , B23H9/14 , F01D5/186 , F01D5/187 , Y10T29/4932 , Y10T29/49323 , Y10T408/03
Abstract: A method for manufacturing a turbine nozzle having a non-linear cooling conduit is disclosed. In one embodiment, a method includes: providing a turbine nozzle. The turbine nozzle includes: an airfoil, a cavity, having an inner surface, located within the airfoil, at least one endwall adjacent the airfoil, and a fillet region connecting the airfoil and the endwall. The fillet region also includes an outer surface. The method also includes: forming a non-linear cooling conduit within the fillet region and adjacent the outer surface of the fillet region of the turbine nozzle. The forming of the non-linear cooling conduit includes curved drilling through a portion of the outer surface of the fillet region of the turbine nozzle.
Abstract translation: 公开了一种用于制造具有非线性冷却导管的涡轮喷嘴的方法。 在一个实施例中，一种方法包括：提供涡轮喷嘴。 涡轮喷嘴包括：翼型件，空腔，具有内表面，位于翼型内，邻近翼型的至少一个端壁和连接翼型件和端壁的圆角区域。 圆角区域还包括外表面。 该方法还包括：在圆角区域内和邻近涡轮喷嘴的圆角区域的外表面处形成非线性冷却导管。 非线性冷却导管的形成包括通过涡轮喷嘴的圆角区域的外表面的一部分的弯曲钻孔。
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