专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US09605548B2 Nozzle endwall film cooling with airfoil cooling holes 有权
公开(公告)号：US09605548B2
公开(公告)日：2017-03-28
申请号：US14146469
申请日：2014-01-02
申请人： SOLAR TURBINES INCORPORATED
发明人： Luzeng Zhang , Juan Yin , Hee Koo Moon
IPC分类号： F01D9/04 , F01D9/06 , F01D5/18
CPC分类号： F01D9/065 , F01D5/186 , F01D5/187 , F01D9/041 , F05D2240/121 , F05D2240/122 , F05D2240/123 , F05D2250/323 , F05D2260/202
摘要： 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.

2. 发明申请

US20150184516A1 NOZZLE ENDWALL FILM COOLING WITH AIRFOIL COOLING HOLES 有权
标题翻译：喷嘴端盖冷却带有空气冷却孔
公开(公告)号：US20150184516A1
公开(公告)日：2015-07-02
申请号：US14146469
申请日：2014-01-02
申请人： SOLAR TURBINES INCORPORATED
发明人： Luzeng Zhang , Juan Yin , Hee Koo Moon
IPC分类号： F01D5/18
CPC分类号： F01D9/065 , F01D5/186 , F01D5/187 , F01D9/041 , F05D2240/121 , F05D2240/122 , F05D2240/123 , F05D2250/323 , F05D2260/202
摘要： 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.
摘要翻译：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。

3. 发明授权

US10208606B2 Airfoil for turbomachine and airfoil cooling method 有权
公开(公告)号：US10208606B2
公开(公告)日：2019-02-19
申请号：US15055895
申请日：2016-02-29
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee-Koo Moon
IPC分类号： F01D5/18 , F04D29/58 , F04D29/32 , F01D25/12 , F01D9/04 , F04D29/54
摘要： 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.

4. 发明授权

US10196905B2 Airfoil for turbomachine and method of cooling same 有权
公开(公告)号：US10196905B2
公开(公告)日：2019-02-05
申请号：US15047179
申请日：2016-02-18
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee-Koo Moon
IPC分类号： F01D5/18 , F04D29/32 , F01D9/04 , F04D29/54
摘要： 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.

5. 发明申请

US20170248022A1 AIRFOIL FOR TURBOMACHINE AND AIRFOIL COOLING METHOD 审中-公开
公开(公告)号：US20170248022A1
公开(公告)日：2017-08-31
申请号：US15055895
申请日：2016-02-29
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee-Koo Moon
IPC分类号： F01D5/18 , F04D29/58 , F04D29/32 , F04D29/54 , F01D9/04 , F01D25/12
CPC分类号： F01D5/187 , F05D2240/304 , F05D2240/305 , F05D2250/231 , F05D2260/202 , F05D2260/2214 , Y02T50/676
摘要： 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.

6. 发明申请

US20170241270A1 AIRFOIL FOR TURBOMACHINE AND METHOD OF COOLING SAME 审中-公开
公开(公告)号：US20170241270A1
公开(公告)日：2017-08-24
申请号：US15047179
申请日：2016-02-18
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee-Koo Moon
IPC分类号： F01D5/18 , F01D9/04 , F04D29/58 , F04D29/32 , F04D29/52 , F04D29/54 , F01D5/14 , F01D25/12
CPC分类号： F01D5/187 , F01D9/041 , F04D29/324 , F04D29/542 , F05D2220/30 , F05D2240/12 , F05D2240/30 , F05D2260/201 , F05D2260/22141 , Y02T50/676
摘要： 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.

7. 发明授权

US10190422B2 Rotation enhanced turbine blade cooling 有权
公开(公告)号：US10190422B2
公开(公告)日：2019-01-29
申请号：US15096854
申请日：2016-04-12
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee Koo Moon
IPC分类号： F01D5/18 , F01D5/14 , F02C7/12 , F02C3/04
摘要： 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.

8. 发明授权

US10174622B2 Wrapped serpentine passages for turbine blade cooling 有权
公开(公告)号：US10174622B2
公开(公告)日：2019-01-08
申请号：US15096866
申请日：2016-04-12
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee Koo Moon
IPC分类号： F01D5/18 , F01D5/20
摘要： 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.

9. 发明授权

US09464528B2 Cooled turbine blade with double compound angled holes and slots 有权
标题翻译：具有双组合倾斜孔和槽的冷却涡轮叶片
公开(公告)号：US09464528B2
公开(公告)日：2016-10-11
申请号：US13918052
申请日：2013-06-14
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee Koo Moon
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/304 , F05D2250/314 , F05D2250/324 , F05D2260/202
摘要： A turbine blade for a gas turbine engine. The turbine blade includes a base having a blade root, a platform, a cooling air inlet, and a base air passageway. The turbine blade also includes an airfoil section adjoined to the base and having an outer wall, an airfoil air passageway, a plurality of trailing edge slots in fluid communication with the airfoil air passageway and a plurality of directional film holes through the outer wall in fluid communication with the airfoil air passageway. The plurality of directional film holes includes a first portion configured to discharge the cooling air toward a tip end, and a second portion configured to discharge the cooling air toward the platform.
摘要翻译：一种用于燃气涡轮发动机的涡轮叶片。涡轮叶片包括具有叶片根部，平台，冷却空气入口和基部空气通道的底座。涡轮机叶片还包括邻接于基座的翼型部分，并且具有外壁，翼型空气通道，与翼型空气通道流体连通的多个后缘槽和通过流体的外壁的多个定向膜孔与翼型通风通道。多个定向膜孔包括构造成朝向顶端排出冷却空气的第一部分和被构造成朝向平台排出冷却空气的第二部分。

10. 发明申请

US20140377054A1 NOZZLE FILM COOLING WITH ALTERNATING COMPOUND ANGLES 审中-公开
标题翻译：喷嘴膜冷却与替代化合物角度
公开(公告)号：US20140377054A1
公开(公告)日：2014-12-25
申请号：US13924178
申请日：2013-06-21
申请人： Solar Turbines Incorporated
发明人： Luzeng Zhang , Juan Yin , Hee Koo Moon
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D9/065
摘要： A nozzle segment for a nozzle ring of a gas turbine engine is disclosed. The nozzle segment includes a first endwall, a second endwall, and an airfoil extending between the first endwall and the second endwall. The airfoil includes a multiple groups of cooling apertures spaced apart and alternating in directionality such that a first grouping of cooling apertures is angled toward the first endwall, a second grouping of cooling apertures is angled toward the second endwall and spaced apart from the first grouping of cooling apertures, and a third grouping of cooling apertures are angled toward the first endwall and spaced apart from the second grouping of cooling apertures.
摘要翻译：公开了一种用于燃气涡轮发动机的喷嘴环的喷嘴段。喷嘴段包括第一端壁，第二端壁和在第一端壁和第二端壁之间延伸的翼型件。翼型件包括多组冷却孔，其间隔开并在方向性上交替，使得第一组冷却孔朝向第一端壁成角度，第二组冷却孔朝向第二端壁成角度并与第一组冷却孔和第三组冷却孔相对于第一端壁成角度并且与第二组冷却孔隔开。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式