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公开(公告)号：US20220145800A1
公开(公告)日：2022-05-12
申请号：US17094034
申请日：2020-11-10
Applicant: Solar Turbines Incorporated
Inventor： James B. Peffley , Ashley M. Vega , Jiang Luo , Richard A. Rogers
Abstract: A compact heat exchanger is disclosed for re-circulating bleed air from a combustor into an inlet and/or exhaust of a gas turbine engine. In an embodiment, the heat exchanger may comprise a plurality of airfoils with internal passages that receive bleed air. The bleed air may be forced through outlets in one or a plurality of concentric passages from the internal passage of each airfoil to an internal cavity of each airfoil, and out of micro-holes within a trailing surface of the airfoil. This enables bleed air to be mixed with gas flowing through the airfoils, in close proximity to the compressor or turbine of the gas turbine engine, while providing acoustic noise suppression and low thermal mixing stratification.
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公开(公告)号：US11859544B1
公开(公告)日：2024-01-02
申请号：US17842245
申请日：2022-06-16
Applicant: Solar Turbines Incorporated
Inventor： John Lockyer , Jiang Luo , Stephen Theron , Stephen Burke
Abstract: In a closed system that recirculates exhaust gas from a gas turbine engine, recirculated exhaust gas should be mixed into inlet gas in a manner that produces a uniform distribution within the mixed gas, while preventing an excessive pressure drop at the point of mixing, and without needing excessive duct length. Otherwise, the performance of the gas turbine engine may be detrimentally affected. Accordingly, a mixer box is disclosed that injects recirculated exhaust gas into a flow path of inlet gas in a uniform manner. The mixer box may comprise mixer(s) that extend the flow path of the recirculated exhaust gas into the flow path of the inlet gas along two axes. Each mixer may comprise surface apertures and/or interior channels designed to promote uniform ejection of the recirculated exhaust gas from the mixers into the flow path of inlet gas.
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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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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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Patent Agency Ranking
公开(公告)号：US20230407787A1
公开(公告)日：2023-12-21
申请号：US17842245
申请日：2022-06-16
Applicant: Solar Turbines Incorporated
Inventor： John Lockyer , Jiang Luo , Stephen Theron , Stephen Burke
Abstract: In a closed system that recirculates exhaust gas from a gas turbine engine, recirculated exhaust gas should be mixed into inlet gas in a manner that produces a uniform distribution within the mixed gas, while preventing an excessive pressure drop at the point of mixing, and without needing excessive duct length. Otherwise, the performance of the gas turbine engine may be detrimentally affected. Accordingly, a mixer box is disclosed that injects recirculated exhaust gas into a flow path of inlet gas in a uniform manner. The mixer box may comprise mixer(s) that extend the flow path of the recirculated exhaust gas into the flow path of the inlet gas along two axes. Each mixer may comprise surface apertures and/or interior channels designed to promote uniform ejection of the recirculated exhaust gas from the mixers into the flow path of inlet gas.
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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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8.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：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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