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公开(公告)号：US10808547B2
公开(公告)日：2020-10-20
申请号：US15018155
申请日：2016-02-08
Applicant: General Electric Company
Inventor： Bridget Lucy Lessard , Bhanu Mahasamudram Reddy , Gaoqiu Zhu , Michael Jong Lee
Abstract: An apparatus and method of cooling an airfoil for a gas turbine engine includes a tip for the radially outer end of the airfoil with internal ribs defining cooling circuits within an interior of the airfoil. The ribs can be full-length, extending between a root and tip of the airfoil. A gap can be formed in the full-length ribs near the tip to form a thermal stress reduction structure for the full-length rib.
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Patent Agency Ranking
公开(公告)号：US10577943B2
公开(公告)日：2020-03-03
申请号：US15592300
申请日：2017-05-11
Applicant: General Electric Company
IPC: F01D5/18
Abstract: An apparatus and method for improving the heat transfer coefficient for an engine component for a turbine engine such as an airfoil. The airfoil can include an outer wall defining an interior. A cooling passage can be formed in the interior defining a flow direction. An insert can be provided in the cooling passage to occupy a volume of the cooling passage to maintain a threshold Mach number for an airflow passing through the cooling passage to improve the heat transfer coefficient.
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公开(公告)号：US09976424B2
公开(公告)日：2018-05-22
申请号：US14790243
申请日：2015-07-02
Applicant: General Electric Company
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F01D5/20 , F05D2220/323 , F05D2240/307 , F05D2250/185 , F05D2260/202 , Y02T50/676
Abstract: A turbine blade includes an airfoil having an internal cooling circuit. The cooling circuit includes a body cooling passage with at least one turn, and a tip cooling channel that forms a cooling barrier to thermally isolate the turn from at least a portion of the exterior surface of the airfoil.
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公开(公告)号：US20170226869A1
公开(公告)日：2017-08-10
申请号：US15018155
申请日：2016-02-08
Applicant: General Electric Company
Inventor： Bridget Lucy Lessard , Bhanu Mahasamudram Reddy , Gaoqiu Zhu , Michael Jong Lee
Abstract: An apparatus and method of cooling an airfoil for a gas turbine engine includes a tip for the radially outer end of the airfoil with internal ribs defining cooling circuits within an interior of the airfoil. The ribs can be full-length, extending between a root and tip of the airfoil. A gap can be formed in the full-length ribs near the tip to form a thermal stress reduction structure for the full-length rib.
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公开(公告)号：US20180328188A1
公开(公告)日：2018-11-15
申请号：US15592300
申请日：2017-05-11
Applicant: General Electric Company
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/188 , F05D2250/21 , F05D2250/23 , F05D2250/232 , F05D2260/201 , F05D2260/202
Abstract: An apparatus and method for improving the heat transfer coefficient for an engine component for a turbine engine such as an airfoil. The airfoil can include an outer wall defining an interior. A cooling passage can be formed in the interior defining a flow direction. An insert can be provided in the cooling passage to occupy a volume of the cooling passage to maintain a threshold Mach number for an airflow passing through the cooling passage to improve the heat transfer coefficient.
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公开(公告)号：US20170002664A1
公开(公告)日：2017-01-05
申请号：US14790243
申请日：2015-07-02
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F01D5/20 , F05D2220/323 , F05D2240/307 , F05D2250/185 , F05D2260/202 , Y02T50/676
Abstract: A turbine blade includes an airfoil having an internal cooling circuit. The cooling circuit includes a body cooling passage with at least one turn, and a tip cooling channel that forms a cooling barrier to thermally isolate the turn from at least a portion of the exterior surface of the airfoil.
Abstract translation: 涡轮叶片包括具有内部冷却回路的翼型件。 冷却回路包括具有至少一匝的主体冷却通道和形成冷却障碍物的顶部冷却通道，以将匝与翼型件的外表面的至少一部分热隔离。
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