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公开(公告)号：US20200291801A1
公开(公告)日：2020-09-17
申请号：US16775653
申请日：2020-01-29
Applicant: General Electric Company
Inventor： Victor Hugo Silva Correia , Robert Francis Manning , George Joe-Kueng Chan , James Earl Kopriva
Abstract: The disclosure relates to a gas turbine engine and a method of controlling an upstream extent of a bow wave from an airfoil having a pressure side and a suction side in the turbine engine. In one aspect, the method includes forming a vortex at a leading edge of the airfoil.
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2.发明授权Device and method for preventing leakage of air between multiple turbine components 有权用于防止多个涡轮机部件之间的空气泄漏的装置和方法公开(公告)号：US09488110B2
公开(公告)日：2016-11-08
申请号：US13790965
申请日：2013-03-08
Applicant: General Electric Company
Inventor： George Joe-Kueng Chan , Victor Hugo Silva Correia , David Hannwacker , Robert Proctor
CPC classification number: F02C7/28 , F01D9/023 , F01D11/005 , F01D25/145 , F05D2230/642 , F05D2250/75 , F05D2260/941 , F05D2300/50211 , F05D2300/6033 , F16J15/0887 , F16J15/52 , F23R3/007 , F23R3/60 , F23R2900/00001 , F23R2900/00012 , F23R2900/00017 , Y02T50/672 , Y02T50/675 , Y10T403/217
Abstract: A turbine comprising a first turbine component being of a first material having a first coefficient of thermal expansion. A second turbine component being of a second material having a second coefficient of thermal expansion, said second turbine component adjacent said first turbine component. A space between said first and second turbine components. A seal assembly sealing said space, wherein at least a portion of said seal assembly has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.
Abstract translation: 一种涡轮机，包括具有第一热膨胀系数的第一材料的第一涡轮机部件。 第二涡轮机部件是具有第二热膨胀系数的第二材料，所述第二涡轮部件与所述第一涡轮部件相邻。 所述第一和第二涡轮机部件之间的空间。 一种密封所述空间的密封组件，其中所述密封组件的至少一部分的热膨胀系数基本上类似于所述第一或第二涡轮机部件中的至少一个，从而在所述第一或第二涡轮机部件的热膨胀或收缩期间保持所述空间中的密封 第一和第二涡轮机部件。
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Patent Agency Ranking
3.发明申请DEVICE AND METHOD FOR PREVENTING LEAKAGE OF AIR BETWEEN MULTIPLE TURBINE COMPONENTS 有权用于防止多个涡轮机组件之间的空气泄漏的装置和方法公开(公告)号：US20140250893A1
公开(公告)日：2014-09-11
申请号：US13790965
申请日：2013-03-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： George Joe-Kueng Chan , Victor Hugo Silva Correia , David Hannwacker , Robert Proctor
IPC: F02C7/28
CPC classification number: F02C7/28 , F01D9/023 , F01D11/005 , F01D25/145 , F05D2230/642 , F05D2250/75 , F05D2260/941 , F05D2300/50211 , F05D2300/6033 , F16J15/0887 , F16J15/52 , F23R3/007 , F23R3/60 , F23R2900/00001 , F23R2900/00012 , F23R2900/00017 , Y02T50/672 , Y02T50/675 , Y10T403/217
Abstract: A turbine comprising a first turbine component being of a first material having a first coefficient of thermal expansion. A second turbine component being of a second material having a second coefficient of thermal expansion, said second turbine component adjacent said first turbine component. A space between said first and second turbine components. A seal assembly sealing said space, wherein at least a portion of said seal assembly has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.
Abstract translation: 一种涡轮机，包括具有第一热膨胀系数的第一材料的第一涡轮机部件。 第二涡轮机部件是具有第二热膨胀系数的第二材料，所述第二涡轮部件与所述第一涡轮部件相邻。 所述第一和第二涡轮机部件之间的空间。 一种密封所述空间的密封组件，其中所述密封组件的至少一部分具有与所述第一或第二涡轮机部件中的至少一个基本相似的热膨胀系数，从而在所述第一或第二涡轮部件的热膨胀或收缩期间保持所述空间中的密封 第一和第二涡轮机部件。
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公开(公告)号：US10590781B2
公开(公告)日：2020-03-17
申请号：US15386000
申请日：2016-12-21
Applicant: General Electric Company
Inventor： Victor Hugo Silva Correia , Robert Francis Manning , George Joe-Kueng Chan , James Earl Kopriva
Abstract: An assembly for a turbine engine comprises a circumferential band defining an air flow path, a component having a leading edge and extending from the band into the flow path, and a trough located in a surface of the band along the leading edge.
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公开(公告)号：US20180171808A1
公开(公告)日：2018-06-21
申请号：US15386000
申请日：2016-12-21
Applicant: General Electric Company
Inventor： Victor Hugo Silva Correia , Robert Francis Manning , George Joe-Kueng Chan , James Earl Kopriva
Abstract: An assembly for a turbine engine comprises a circumferential band defining an air flow path, a component having a leading edge and extending from the band into the flow path, and a trough located in a surface of the band along the leading edge.
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公开(公告)号：US11466579B2
公开(公告)日：2022-10-11
申请号：US16775653
申请日：2020-01-29
Applicant: General Electric Company
Inventor： Victor Hugo Silva Correia , Robert Francis Manning , George Joe-Kueng Chan , James Earl Kopriva
Abstract: The disclosure relates to a gas turbine engine and a method of controlling an upstream extent of a bow wave from an airfoil having a pressure side and a suction side in the turbine engine. In one aspect, the method includes forming a vortex at a leading edge of the airfoil.
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公开(公告)号：US10221693B2
公开(公告)日：2019-03-05
申请号：US14901450
申请日：2014-07-03
Applicant: General Electric Company
Inventor： George Joe-Kueng Chan , Ronald Scott Bunker , Victor Hugo Silva Correia , Christopher Kanoa Hoffman
Abstract: An airfoil comprises at least one wall defining a leading edge, a trailing edge, a pressure side extending between the leading edge and the trailing edge, and a suction side extending between the leading edge and the trailing edge. The airfoil is curved in three dimensions and has one or more cavities defined by an interior surface of the at least one wall. A plurality of cooling film holes extending between the cavity and at least one cooling trench located on at least one of the pressure side and the suction side, spaced from the leading edge. The at least one trench has a floor spaced from an outer surface of the airfoil. The plurality of cooling film holes extend through the floor at an angle other than perpendicular.
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