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公开(公告)号：US20150040582A1
公开(公告)日：2015-02-12
申请号：US13961194
申请日：2013-08-07
Applicant: General Electric Company
Inventor： Zhirui Dong , Xiuhang James Zhang , Melbourne James Myers , Camilo Andres Sampayo
IPC: F01D5/18
Abstract: A cooling circuit for a turbine bucket having an airfoil portion includes a trailing edge cooling circuit portion provided with a first radially outwardly directed inlet passage intermediate leading and trailing edges of the airfoil portion of the bucket, extending from a platform portion of the bucket to a location adjacent a radially outer tip of the bucket, and connecting to a second radially inwardly directed passage extending from a location adjacent the radially outer tip to a location adjacent the platform portion. The second radially inwardly directed passage connects to a third trailing edge region passage, and a plurality of crossover passages connect a radially outer half of the second radially inwardly directed passage to a radially outer half of the third trailing edge region passage.
Abstract translation: 具有翼型部分的涡轮机叶片的冷却回路包括后缘冷却回路部分，该后缘冷却回路部分设置有从铲斗的平台部分延伸到铲斗的翼型部分的前缘和后缘之间的第一径向向外的入口通道 位于邻近所述铲斗的径向外部末端并且连接到从邻近所述径向外部末端的位置延伸到邻近所述平台部分的位置的第二径向向内指向的通道。 第二径向向内定向的通道连接到第三后缘区域通道，并且多个交叉通道将第二径向向内定向通道的径向外半部连接到第三后缘区域通道的径向外半部。
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公开(公告)号：US09334742B2
公开(公告)日：2016-05-10
申请号：US13645585
申请日：2012-10-05
Applicant: General Electric Company
Inventor： Xiuzhang James Zhang , Adebukola Benson , Zhirui Dong
CPC classification number: F01D5/20
Abstract: A rotor blade includes an airfoil having a tip plate that extends across an outer radial end. A rim extends radially outward from the tip plate and surrounds at least a portion of the airfoil and includes a concave portion opposed to a convex portion. A plurality of dividers extend between the concave and convex portions to define a plurality of pockets between the concave and convex portions at the outer radial end. A plurality of cooling passages through the tip plate provide fluid communication through the tip plate to the plurality of pockets. A first fluid passage in at least one divider provides fluid communication between adjacent pockets across the at least one divider.
Abstract translation: 转子叶片包括具有延伸穿过外径向端的顶板的翼型件。 边缘从顶板径向向外延伸并且包围翼型的至少一部分并且包括与凸部相对的凹部。 多个分隔件在凹部和凸部之间延伸以在外径向端部处在凹部和凸部之间限定多个凹穴。 通过顶板的多个冷却通道提供通过顶板到多个凹穴的流体连通。 至少一个分隔器中的第一流体通道提供穿过至少一个分隔器的相邻袋之间的流体连通。
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Patent Agency Ranking
公开(公告)号：US20150345303A1
公开(公告)日：2015-12-03
申请号：US14288748
申请日：2014-05-28
Applicant: General Electric Company
Inventor： Zhirui Dong , Xiuzhang James Zhang , Jason Adam Neville
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/085 , F01D5/187 , F05D2260/202 , F05D2260/2212 , Y02T50/676
Abstract: A rotor blade includes a mounting portion comprising a mounting body that is formed to receive a coolant therein. An airfoil portion extends substantially radially outwardly from the mounting body and includes an airfoil body. The mounting body and the airfoil body define a plurality of primary cooling passages that extend substantially radially therein for routing the coolant through the airfoil body. Each of the primary cooling passages includes a cooling flow outlet that is formed along a tip portion of the airfoil body. The airfoil body further defines a plurality of trailing edge cooling passages, each having a coolant outlet that is formed along a trailing edge portion of the airfoil body. At least a portion of the trailing edge cooling passages are formed along a radially outer portion of the trailing edge proximate to the tip portion of the airfoil body.
Abstract translation: 转子叶片包括安装部分，其包括形成为在其中容纳冷却剂的安装体。 机翼部分从安装体基本上径向向外延伸并且包括翼型体。 安装体和翼型体限定了多个基本上径向延伸的主冷却通道，用于使冷却剂穿过翼型体。 每个主冷却通道包括沿翼型本体的尖端部分形成的冷却流出口。 翼型体还限定多个后缘冷却通道，每个后缘冷却通道具有沿翼型本体的后缘部分形成的冷却剂出口。 尾缘冷却通道的至少一部分沿靠近翼型本体的尖端部分的后缘的径向外部部分形成。
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公开(公告)号：US09810072B2
公开(公告)日：2017-11-07
申请号：US14288748
申请日：2014-05-28
Applicant: General Electric Company
Inventor： Zhirui Dong , Xiuzhang James Zhang , Jason Adam Neville
CPC classification number: F01D5/186 , F01D5/085 , F01D5/187 , F05D2260/202 , F05D2260/2212 , Y02T50/676
Abstract: A rotor blade includes a mounting portion comprising a mounting body that is formed to receive a coolant therein. An airfoil portion extends substantially radially outwardly from the mounting body and includes an airfoil body. The mounting body and the airfoil body define a plurality of primary cooling passages that extend substantially radially therein for routing the coolant through the airfoil body. Each of the primary cooling passages includes a cooling flow outlet that is formed along a tip portion of the airfoil body. The airfoil body further defines a plurality of trailing edge cooling passages, each having a coolant outlet that is formed along a trailing edge portion of the airfoil body. At least a portion of the trailing edge cooling passages are formed along a radially outer portion of the trailing edge proximate to the tip portion of the airfoil body.
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公开(公告)号：US10808538B2
公开(公告)日：2020-10-20
申请号：US16176275
申请日：2018-10-31
Applicant: General Electric Company
Inventor： Melbourne James Myers , Sylvain Pierre , Michael Gordon Sherman , Luke C Sponseller , Zhirui Dong , Le Trong Tran
Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.
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公开(公告)号：US20200131912A1
公开(公告)日：2020-04-30
申请号：US16176275
申请日：2018-10-31
Applicant: General Electric Company
Inventor： Melbourne James Myers , Sylvain Pierre , Michael Gordon Sherman , Luke C. Sponseller , Zhirui Dong , Le Trong Tran
Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.
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公开(公告)号：US20140099193A1
公开(公告)日：2014-04-10
申请号：US13645585
申请日：2012-10-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Xiuzhang James Zhang , Adebukola Benson , Zhirui Dong
CPC classification number: F01D5/20
Abstract: A rotor blade includes an airfoil having a tip plate that extends across an outer radial end. A rim extends radially outward from the tip plate and surrounds at least a portion of the airfoil and includes a concave portion opposed to a convex portion. A plurality of dividers extend between the concave and convex portions to define a plurality of pockets between the concave and convex portions at the outer radial end. A plurality of cooling passages through the tip plate provide fluid communication through the tip plate to the plurality of pockets. A first fluid passage in at least one divider provides fluid communication between adjacent pockets across the at least one divider.
Abstract translation: 转子叶片包括具有延伸穿过外径向端的顶板的翼型件。 边缘从顶板径向向外延伸并且包围翼型的至少一部分并且包括与凸部相对的凹部。 多个分隔件在凹部和凸部之间延伸以在外径向端部处在凹部和凸部之间限定多个凹穴。 通过顶板的多个冷却通道提供通过顶板到多个凹穴的流体连通。 至少一个分隔器中的第一流体通道提供穿过至少一个分隔器的相邻袋之间的流体连通。
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