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1.发明授权Method of manufacturing a cooled turbine blade with dense cooling fin array 有权制造具有致密散热片阵列的冷却涡轮叶片的方法公开(公告)号：US09314838B2
公开(公告)日：2016-04-19
申请号：US13631043
申请日：2012-09-28
Applicant: Solar Turbines Incorporated
Inventor： Stephen Edward Pointon , Andrew Meier , Nnawuihe Asonye Okpara , Daniel Martinez
CPC classification number: B22C9/10 , B22C7/02 , B22C9/04 , B22C9/043 , B22C9/108 , F01D5/187 , F05D2230/21 , F05D2240/126 , F05D2240/127 , F05D2250/185 , F05D2260/22141 , Y10T29/49339 , Y10T29/49341
Abstract: A method of manufacturing a cooled turbine blade for use in a gas turbine engine. The method includes forming an inner blade pattern, the inner blade pattern including an inner spar and a plurality of inner spar cooling fins. The method also includes forming an inner blade core, removing the inner blade pattern from the inner blade core, forming an outer blade pattern, forming a casting shell, removing the outer blade pattern from the casting shell, and casting the cooled turbine blade in the casting shell. The method also includes removing the casting shell from the cast cooled turbine blade, and removing the inner blade core from the cast cooled turbine blade.
Abstract translation: 一种制造用于燃气涡轮发动机的冷却涡轮叶片的方法。 该方法包括形成内刀片图案，内刀片图案包括内翼片和多个内翼片冷却翅片。 该方法还包括形成内刀片芯，从内刀片芯中去除内刀片图案，形成外刀片图案，形成铸造壳体，从铸造壳体移除外刀片图案，以及将冷却的涡轮叶片铸造在 铸壳。 该方法还包括从铸冷却的涡轮机叶片移除铸造壳体，以及从铸造冷却的涡轮机叶片移除内部叶片芯部。
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公开(公告)号：US09206695B2
公开(公告)日：2015-12-08
申请号：US13631219
申请日：2012-09-28
Applicant: Solar Turbines Incorporated
Inventor： Stephen Edward Pointon , Andrew Meier , Nnawuihe Asonye Okpara , Jiang Luo
IPC: F01D5/18
CPC classification number: F01D5/186 , F05D2240/304 , F05D2260/202
Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a plurality of trailing edge cooling fins, and a perforated first and second trailing edge rib configured to meter cooling air passing there thorough.
Abstract translation: 具有底座和翼型件的冷却涡轮机叶片，该底座包括冷却空气入口和内部冷却空气通道，并且该翼型件包括内部热交换路径，该内部热交换路径从基座开始并在其后缘处的冷却空气出口处终止 翼型。 翼型件还包括一个“皮肤”，其包括尖端壁，内部翼梁，多个后缘冷却翅片，以及被配置成计量通过那里的冷却空气的穿孔的第一和第二后缘肋条。
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公开(公告)号：US20140093388A1
公开(公告)日：2014-04-03
申请号：US13631085
申请日：2012-09-28
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Stephen Edward Pointon , Andrew Meier , Nnawuihe Asonye Okpara , Jiang Luo
CPC classification number: F01D5/186 , F05D2240/303
Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a leading edge rib, and a leading edge air deflector. The leading edge rib is configured to form a leading edge chamber in conjunction with the leading edge of the skin. The leading edge air deflector is at least partially intersected by the inner spar.
Abstract translation: 具有底座和翼型件的冷却涡轮机叶片，该底座包括冷却空气入口和内部冷却空气通道，并且该翼型件包括内部热交换路径，该内部热交换路径从基座开始并在其后缘处的冷却空气出口处终止 翼型。 机翼还包括一个“皮肤”，其包括尖端壁，内部翼梁，前缘肋和前缘空气导流板。 前缘肋构造成与皮肤的前缘结合形成前缘室。 前缘空气导流板至少部分地与内部翼梁相交。
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Patent Agency Ranking
公开(公告)号：US09228439B2
公开(公告)日：2016-01-05
申请号：US13631133
申请日：2012-09-28
Applicant: Solar Turbines Incorporated
Inventor： Stephen Edward Pointon , Andrew Meier , Nnawuihe Asonye Okpara , Jiang Luo
IPC: F01D5/18
Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a leading edge rib, and a leading edge air deflector. The leading edge rib is configured to form a leading edge chamber in conjunction with the leading edge of the skin. The leading edge air deflector is shaped and positioned such that cooling air leaving the leading edge chamber is both turned and diffused.
Abstract translation: 具有底座和翼型件的冷却涡轮机叶片，该底座包括冷却空气入口和内部冷却空气通道，并且该翼型件包括内部热交换路径，该内部热交换路径从基座开始并在其后缘处的冷却空气出口处终止 翼型。 机翼还包括一个“皮肤”，其包括尖端壁，内部翼梁，前缘肋和前缘空气导流板。 前缘肋构造成与皮肤的前缘结合形成前缘室。 前缘导风板的形状和定位使得离开前缘室的冷却空气都被转动和扩散。
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公开(公告)号：US20140093391A1
公开(公告)日：2014-04-03
申请号：US13631219
申请日：2012-09-28
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Stephen Edward Pointon , Andrew Meier , Nnawuihe Asonye Okpara , Jiang Luo
IPC: F01D5/18
CPC classification number: F01D5/186 , F05D2240/304 , F05D2260/202
Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a plurality of trailing edge cooling fins, and a perforated first and second trailing edge rib configured to meter cooling air passing there thorough.
Abstract translation: 具有底座和翼型件的冷却涡轮机叶片，该底座包括冷却空气入口和内部冷却空气通道，并且该翼型件包括内部热交换路径，该内部热交换路径从基座开始并在其后缘处的冷却空气出口处终止 翼型。 翼型件还包括一个“皮肤”，其包括尖端壁，内部翼梁，多个后缘冷却翅片，以及被配置成计量通过那里的冷却空气的穿孔的第一和第二后缘肋条。
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6.发明申请公开(公告)号：US20140093390A1
公开(公告)日：2014-04-03
申请号：US13631133
申请日：2012-09-28
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Stephen Edward Pointon , Andrew Meier , Nnawuihe Asonye Okpara , Jiang Luo
Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a leading edge rib, and a leading edge air deflector. The leading edge rib is configured to form a leading edge chamber in conjunction with the leading edge of the skin. The leading edge air deflector is shaped and positioned such that cooling air leaving the leading edge chamber is both turned and diffused.
Abstract translation: 具有底座和翼型件的冷却涡轮机叶片，该底座包括冷却空气入口和内部冷却空气通道，并且该翼型件包括内部热交换路径，该内部热交换路径从基座开始并在其后缘处的冷却空气出口处终止 翼型。 机翼还包括一个“皮肤”，其包括尖端壁，内部翼梁，前缘肋和前缘空气导流板。 前缘肋构造成与皮肤的前缘结合形成前缘室。 前缘导风板的形状和定位使得离开前缘室的冷却空气都被转动和扩散。
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公开(公告)号：US20140093387A1
公开(公告)日：2014-04-03
申请号：US13631043
申请日：2012-09-28
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Stephen Edward Pointon , Andrew Meier , Nnawuihe Asonye Okpara , Daniel Martinez
CPC classification number: B22C9/10 , B22C7/02 , B22C9/04 , B22C9/043 , B22C9/108 , F01D5/187 , F05D2230/21 , F05D2240/126 , F05D2240/127 , F05D2250/185 , F05D2260/22141 , Y10T29/49339 , Y10T29/49341
Abstract: A method of manufacturing a cooled turbine blade for use in a gas turbine engine. The method includes forming an inner blade pattern, the inner blade pattern including an inner spar and a plurality of inner spar cooling fins. The method also includes forming an inner blade core, removing the inner blade pattern from the inner blade core, forming an outer blade pattern, forming a casting shell, removing the outer blade pattern from the casting shell, and casting the cooled turbine blade in the casting shell. The method also includes removing the casting shell from the cast cooled turbine blade, and removing the inner blade core from the cast cooled turbine blade.
Abstract translation: 一种制造用于燃气涡轮发动机的冷却涡轮叶片的方法。 该方法包括形成内刀片图案，内刀片图案包括内翼片和多个内翼片冷却翅片。 该方法还包括形成内刀片芯，从内刀片芯中去除内刀片图案，形成外刀片图案，形成铸造壳体，从铸造壳体移除外刀片图案，以及将冷却的涡轮叶片铸造在 铸壳。 该方法还包括从铸冷却的涡轮机叶片移除铸造壳体，以及从铸造冷却的涡轮机叶片移除内部叶片芯部。
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公开(公告)号：US20140093386A1
公开(公告)日：2014-04-03
申请号：US13631258
申请日：2012-09-28
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Stephen Edward Pointon , Andrew Meier , Nnawuihe Asonye Okpara , Daniel Martinez , Jiang Luo
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/20 , F05D2260/2214
Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a plurality of inner spar cooling fins extending from the inner spar to the skin, and a plurality of trailing edge cooling fins extending from the pressure side of the skin to the lift side of the skin aft of the inner spar.
Abstract translation: 具有底座和翼型件的冷却涡轮机叶片，该底座包括冷却空气入口和内部冷却空气通道，并且该翼型件包括内部热交换路径，该内部热交换路径从基座开始并在其后缘处的冷却空气出口处终止 翼型。 机翼还包括一个“皮肤”，其包括尖端壁，内部翼梁，从内部翼梁延伸到皮肤的多个内部翼梁冷却翅片，以及从皮肤的压力侧延伸的多个后缘冷却翅片 到内部翼梁的皮肤后部的提升面。
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