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公开(公告)号：US10208606B2
公开(公告)日：2019-02-19
申请号：US15055895
申请日：2016-02-29
Applicant: Solar Turbines Incorporated
Inventor： Luzeng Zhang , Juan Yin , Hee-Koo Moon
Abstract: An airfoil for a turbomachine such as a gas turbine engine includes a pressure side and a suction side, a flow-distributing forward wall and an inner cooling wall. A switchbacked passage extends through the airfoil, and the flow-distributing forward wall has a plurality of jetting orifices formed therein and connecting the switchbacked passage to a forward cavity. The jetting orifices are oriented to produce wall jets of cooling fluid directed in an upstream direction toward a back side of the leading edge. A second passage extends between the forward cavity and outlets of the airfoil, so as to convey cooling fluid in a downstream direction toward the outlets.
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公开(公告)号：US09605548B2
公开(公告)日：2017-03-28
申请号：US14146469
申请日：2014-01-02
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Luzeng Zhang , Juan Yin , Hee Koo Moon
CPC classification number: F01D9/065 , F01D5/186 , F01D5/187 , F01D9/041 , F05D2240/121 , F05D2240/122 , F05D2240/123 , F05D2250/323 , F05D2260/202
Abstract: A nozzle segment for a nozzle ring of a gas turbine engine is disclosed. The nozzle segment includes an upper endwall, a lower endwall, and an airfoil extending between the upper endwall and the lower endwall. The airfoil includes a pressure side wall, a plurality of inner cooling apertures, and a plurality of outer cooling apertures. The plurality of inner cooling apertures extends through a pressure side wall and is arranged in a first row adjacent the lower endwall. The plurality of outer cooling apertures extends through the pressure side wall and is arranged in a second row adjacent the upper endwall.
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公开(公告)号：US20150184516A1
公开(公告)日：2015-07-02
申请号：US14146469
申请日：2014-01-02
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Luzeng Zhang , Juan Yin , Hee Koo Moon
IPC: F01D5/18
CPC classification number: F01D9/065 , F01D5/186 , F01D5/187 , F01D9/041 , F05D2240/121 , F05D2240/122 , F05D2240/123 , F05D2250/323 , F05D2260/202
Abstract: A nozzle segment for a nozzle ring of a gas turbine engine is disclosed. The nozzle segment includes an upper endwall, a lower endwall, and an airfoil extending between the upper endwall and the lower endwall. The airfoil includes a pressure side wall, a plurality of inner cooling apertures, and a plurality of outer cooling apertures. The plurality of inner cooling apertures extends through a pressure side wall and is arranged in a first row adjacent the lower endwall. The plurality of outer cooling apertures extends through the pressure side wall and is arranged in a second row adjacent the upper endwall.
Abstract translation: 公开了一种用于燃气涡轮发动机的喷嘴环的喷嘴段。 喷嘴段包括上端壁，下端壁和在上端壁与下端壁之间延伸的翼型件。 翼型件包括压力侧壁，多个内部冷却孔和多个外部冷却孔。 多个内部冷却孔延伸穿过压力侧壁并且被布置在邻近下端壁的第一排中。 多个外部冷却孔延伸穿过压力侧壁并且被布置在邻近上端壁的第二排中。
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公开(公告)号：US10190422B2
公开(公告)日：2019-01-29
申请号：US15096854
申请日：2016-04-12
Applicant: Solar Turbines Incorporated
Inventor： Luzeng Zhang , Juan Yin , Hee Koo Moon
Abstract: A turbine blade for a gas turbine engine may include an outer, peripheral wall extending along a suction side and a pressure side of the blade from a leading edge to a trailing edge of the blade and from a root end to a tip end of the blade, a substantially vertical bifurcating internal wall extending between the leading edge and the trailing edge of the blade in between the suction side and the pressure side of the blade, a plurality of pressure side cooling fluid passages defined between the peripheral wall on the pressure side of the blade and the bifurcating internal wall and extending at least part way from the root end to the tip end of the blade, and a plurality of suction side cooling fluid passages defined between the peripheral wall on the suction side of the blade and the bifurcating internal wall and extending at least part way from the tip end to the root end of the blade. At least one of the pressure side cooling fluid passages may receive fresh cooling fluid from a cooling fluid inlet opening at the root end of the blade and direct the cooling fluid radially upwardly toward the tip end of the blade, across a top side of the bifurcating internal wall, and down through at least one of the plurality of suction side cooling fluid passages.
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公开(公告)号：US11428166B2
公开(公告)日：2022-08-30
申请号：US17096046
申请日：2020-11-12
Applicant: Solar Turbines Incorporated
Inventor： Scott L. Stafford , Juan Yin , Steven D. Gray
Abstract: Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.
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Patent Agency Ranking
公开(公告)号：US10196905B2
公开(公告)日：2019-02-05
申请号：US15047179
申请日：2016-02-18
Applicant: Solar Turbines Incorporated
Inventor： Luzeng Zhang , Juan Yin , Hee-Koo Moon
Abstract: An airfoil for a turbomachine such as a gas turbine engine includes a switchbacked passage for conveying cooling fluid, and flow-distribution passages in a forward wall so as to direct cooling fluid from the internal passage for back side impingement upon a leading edge of the airfoil. An inner cooling wall forms a passage for discharging the spent cooling air from a trailing edge of the airfoil after impingement, and cools one of a pressure side and a suction side of the airfoil by way of conduction. The switchbacked passage may have a serpentine form.
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公开(公告)号：US20170248022A1
公开(公告)日：2017-08-31
申请号：US15055895
申请日：2016-02-29
Applicant: Solar Turbines Incorporated
Inventor： Luzeng Zhang , Juan Yin , Hee-Koo Moon
CPC classification number: F01D5/187 , F05D2240/304 , F05D2240/305 , F05D2250/231 , F05D2260/202 , F05D2260/2214 , Y02T50/676
Abstract: An airfoil for a turbomachine such as a gas turbine engine includes a pressure side and a suction side, a flow-distributing forward wall and an inner cooling wall. A switchbacked passage extends through the airfoil, and the flow-distributing forward wall has a plurality of jetting orifices formed therein and connecting the switchbacked passage to a forward cavity. The jetting orifices are oriented to produce wall jets of cooling fluid directed in an upstream direction toward a back side of the leading edge. A second passage extends between the forward cavity and outlets of the airfoil, so as to convey cooling fluid in a downstream direction toward the outlets.
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公开(公告)号：US20170241270A1
公开(公告)日：2017-08-24
申请号：US15047179
申请日：2016-02-18
Applicant: Solar Turbines Incorporated
Inventor： Luzeng Zhang , Juan Yin , Hee-Koo Moon
CPC classification number: F01D5/187 , F01D9/041 , F04D29/324 , F04D29/542 , F05D2220/30 , F05D2240/12 , F05D2240/30 , F05D2260/201 , F05D2260/22141 , Y02T50/676
Abstract: An airfoil for a turbomachine such as a gas turbine engine includes a switchbacked passage for conveying cooling fluid, and flow-distribution passages in a forward wall so as to direct cooling fluid from the internal passage for back side impingement upon a leading edge of the airfoil. An inner cooling wall forms a passage for discharging the spent cooling air from a trailing edge of the airfoil after impingement, and cools one of a pressure side and a suction side of the airfoil by way of conduction. The switchbacked passage may have a serpentine form.
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公开(公告)号：US20220145799A1
公开(公告)日：2022-05-12
申请号：US17096046
申请日：2020-11-12
Applicant: Solar Turbines Incorporated
Inventor： Scott L. Stafford , Juan Yin , Steven D. Gray
Abstract: Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.
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公开(公告)号：US10174622B2
公开(公告)日：2019-01-08
申请号：US15096866
申请日：2016-04-12
Applicant: Solar Turbines Incorporated
Inventor： Luzeng Zhang , Juan Yin , Hee Koo Moon
Abstract: A turbine blade for a gas turbine engine may include at least two wrapped, serpentine-shaped internal cooling paths. A first one of the serpentine-shaped internal cooling paths may include a first passage that extends radially along a leading edge of the turbine blade from adjacent a root end of the turbine blade to adjacent a tip end of the turbine blade. The first passage may be configured to provide fresh cooling fluid to the leading edge. A second passage downstream of the first passage may be configured to discharge spent cooling fluid from the first passage of the first one of the serpentine-shaped internal cooling paths across a plurality of flow disrupters positioned along an upper span of a trailing edge of the turbine blade before exiting from the trailing edge of the turbine blade. A second one of the serpentine-shaped internal cooling paths may be configured to supply fresh cooling fluid to a lower span of the trailing edge of the turbine blade.
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