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

US09297262B2 Cooling structures in the tips of turbine rotor blades 有权
标题翻译：涡轮转子叶片尖端的冷却结构
公开(公告)号：US09297262B2
公开(公告)日：2016-03-29
申请号：US13479683
申请日：2012-05-24
申请人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
发明人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/20 , F01D5/186
摘要： A turbine rotor blade for a gas turbine engine is described. The turbine rotor blade includes an airfoil that includes a tip at an outer radial end. The tip includes a rail that defines a tip cavity; and the rail includes a circumscribing rail microchannel. The circumscribing rail microchannel is a microchannel that extends around at least a majority of the length of the inner rail surface.
摘要翻译：描述了一种用于燃气涡轮发动机的涡轮转子叶片。涡轮转子叶片包括在外径向端部包括尖端的翼型件。尖端包括限定尖端腔的轨道; 并且轨道包括外接轨道微通道。外接导轨微通道是围绕内轨表面的至少大部分长度延伸的微通道。

2. 发明申请

US20130315749A1 COOLING STRUCTURES IN THE TIPS OF TURBINE ROTOR BLADES 有权
标题翻译：涡轮转子叶片的冷却结构
公开(公告)号：US20130315749A1
公开(公告)日：2013-11-28
申请号：US13479683
申请日：2012-05-24
申请人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
发明人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/186
摘要： A turbine rotor blade for a gas turbine engine is described. The turbine rotor blade includes an airfoil that includes a tip at an outer radial end. The tip includes a rail that defines a tip cavity; and the rail includes a circumscribing rail microchannel. The circumscribing rail microchannel is a microchannel that extends around at least a majority of the length of the inner rail surface.
摘要翻译：描述了一种用于燃气涡轮发动机的涡轮转子叶片。涡轮转子叶片包括在外径向端部包括尖端的翼型件。尖端包括限定尖端腔的轨道; 并且轨道包括外接轨道微通道。外接导轨微通道是围绕内轨表面的至少大部分长度延伸的微通道。

3. 发明申请

US20130039758A1 TURBINE AIRFOIL AND METHOD OF CONTROLLING A TEMPERATURE OF A TURBINE AIRFOIL 审中-公开
标题翻译：涡轮机空气和控制涡轮机空气温度的方法
公开(公告)号：US20130039758A1
公开(公告)日：2013-02-14
申请号：US13205763
申请日：2011-08-09
申请人： Aaron Ezekiel Smith , Bradley Taylor Boyer , Anthony Louis Giglio , Ross James Gustafson , Christopher Michael Penny
发明人： Aaron Ezekiel Smith , Bradley Taylor Boyer , Anthony Louis Giglio , Ross James Gustafson , Christopher Michael Penny
IPC分类号： F01D5/18
CPC分类号： F01D11/04 , F01D11/006 , F05D2240/81 , F05D2260/205 , F05D2260/2212 , F05D2260/22141
摘要： According to one aspect of the invention, a turbine airfoil includes a platform and a blade extending from the platform. The airfoil also includes a slot formed in a slashface of the platform, the slot being configured to receive a pressurized fluid via passages and configured to direct the pressurized fluid to a selected region of the turbine airfoil to improve airfoil life.
摘要翻译：根据本发明的一个方面，涡轮机翼片包括平台和从平台延伸的叶片。翼型件还包括形成在平台的斜面中的槽，该槽被配置为经由通道接收加压流体并且构造成将加压流体引导到涡轮机翼型的选定区域以改善翼型件的寿命。

4. 发明授权

US09447691B2 Bucket assembly treating apparatus and method for treating bucket assembly 有权
标题翻译：铲斗总成处理装置及方法
公开(公告)号：US09447691B2
公开(公告)日：2016-09-20
申请号：US13214583
申请日：2011-08-22
申请人： Aaron Ezekiel Smith , Gary Michael Itzel , Scott Edmond Ellis
发明人： Aaron Ezekiel Smith , Gary Michael Itzel , Scott Edmond Ellis
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/81
摘要： A bucket assembly and a method for treating a bucket assembly are disclosed. The bucket assembly includes a platform, the platform defining a platform cooling circuit, and an airfoil extending generally radially outward from the platform, the airfoil defining an airfoil cooling circuit. The bucket assembly additionally includes a lower body portion extending generally radially inward from the platform, the lower body portion defining a root and a cooling passage extending from the root, the cooling passage in fluid communication with the airfoil cooling circuit. The bucket assembly further includes a transfer passage defined between and in fluid communication with the airfoil cooling circuit and the platform cooling circuit such that a cooling medium may flow from the airfoil cooling circuit through the transfer passage to the platform cooling circuit.
摘要翻译：公开了一种用于处理铲斗组件的铲斗组件和方法。铲斗组件包括平台，限定平台冷却回路的平台和从平台大致径向向外延伸的翼型件，翼型件限定翼型冷却回路。铲斗组件还包括从平台大致径向向内延伸的下主体部分，下主体部分限定根部和从根部延伸的冷却通道，冷却通道与翼型件冷却回路流体连通。铲斗组件还包括一个传导通道，其限定在翼型件冷却回路和平台冷却回路之间并与其流体连通，使得冷却介质可以从翼型冷却回路通过传送通道流到平台冷却回路。

5. 发明授权

US09109454B2 Turbine bucket with pressure side cooling 有权
标题翻译：涡轮桶与压力侧冷却
公开(公告)号：US09109454B2
公开(公告)日：2015-08-18
申请号：US13409341
申请日：2012-03-01
申请人： Scott Edmond Ellis , Randall Richard Good , Bradley Taylor Boyer , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Randall Richard Good , Bradley Taylor Boyer , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2250/185
摘要： A turbine bucket for use with a gas turbine engine, as described herein, may include a platform, an airfoil extending from the platform, and a number of cooling circuits extending through the platform and the airfoil. One of the cooling circuits may be a serpentine cooling channel positioned within the platform.
摘要翻译：如本文所述，用于燃气涡轮发动机的涡轮机桶可以包括平台，从平台延伸的翼型件以及延伸穿过平台和翼型件的多个冷却回路。冷却回路中的一个可以是位于平台内的蛇形冷却通道。

6. 发明授权

US09051842B2 System and method for cooling turbine blades 有权
标题翻译：冷却涡轮叶片的系统和方法
公开(公告)号：US09051842B2
公开(公告)日：2015-06-09
申请号：US13344530
申请日：2012-01-05
申请人： Aaron Ezekiel Smith , Christopher Michael Penny
发明人： Aaron Ezekiel Smith , Christopher Michael Penny
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D5/187 , F01D5/186 , F01D25/12 , F05D2230/21 , F05D2240/304 , F05D2250/131 , F05D2250/323 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A system includes a turbine blade, which includes at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade. The cooling slot includes an entrance coupled to the interior and a converging section downstream from the entrance. The converging section includes a first cross-sectional area that decreases in the flow direction. The cooling slot also includes an exit disposed along a trailing edge of the turbine blade.
摘要翻译：一种系统包括涡轮机叶片，其包括至少一个冷却槽，该冷却槽构造成沿涡轮叶片的内部到外部在流动方向上输送冷却剂。冷却槽包括连接到内部的入口和入口下游的会聚部分。会聚部分包括在流动方向上减小的第一横截面面积。冷却槽还包括沿涡轮叶片的后缘设置的出口。

7. 发明申请

US20130177446A1 SYSTEM AND METHOD FOR COOLING TURBINE BLADES 有权
标题翻译：用于冷却涡轮叶片的系统和方法
公开(公告)号：US20130177446A1
公开(公告)日：2013-07-11
申请号：US13344530
申请日：2012-01-05
申请人： Aaron Ezekiel Smith , Christopher Michael Penny
发明人： Aaron Ezekiel Smith , Christopher Michael Penny
IPC分类号： F01D5/18 , B22C9/10 , B22D25/02
CPC分类号： F01D5/187 , F01D5/186 , F01D25/12 , F05D2230/21 , F05D2240/304 , F05D2250/131 , F05D2250/323 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A system includes a turbine blade, which includes at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade. The cooling slot includes an entrance coupled to the interior and a converging section downstream from the entrance. The converging section includes a first cross-sectional area that decreases in the flow direction. The cooling slot also includes an exit disposed along a trailing edge of the turbine blade.
摘要翻译：一种系统包括涡轮机叶片，其包括至少一个冷却槽，该冷却槽构造成沿涡轮叶片的内部到外部在流动方向上输送冷却剂。冷却槽包括连接到内部的入口和入口下游的会聚部分。会聚部分包括在流动方向上减小的第一横截面面积。冷却槽还包括沿涡轮叶片的后缘设置的出口。

8. 发明申请

US20130052036A1 PIN-FIN ARRAY 审中-公开
标题翻译： PIN-FIN阵列
公开(公告)号：US20130052036A1
公开(公告)日：2013-02-28
申请号：US13221009
申请日：2011-08-30
申请人： Aaron Ezekiel Smith
发明人： Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2240/304 , F05D2260/2212 , F05D2260/2214
摘要： The present application provides an airfoil with a cooling flow therein. The airfoil may include an internal cooling passage, a number of cooling holes in communication with the internal cooling passage, and a number of pin-fins positioned within the internal cooling passage. The pin-fins are arranged with one or more turning openings and one or more guiding openings so as to direct the cooling flow towards the cooling holes.
摘要翻译：本申请提供其中具有冷却流的翼型件。翼型件可以包括内部冷却通道，与内部冷却通道连通的多个冷却孔以及位于内部冷却通道内的多个销翅片。销翅片布置有一个或多个转动开口和一个或多个引导开口，以便将冷却流引向冷却孔。

9. 发明授权

US09249674B2 Turbine rotor blade platform cooling 有权
标题翻译：涡轮转子叶片平台冷却
公开(公告)号：US09249674B2
公开(公告)日：2016-02-02
申请号：US13341024
申请日：2011-12-30
申请人： Scott Edmond Ellis , Aaron Ezekiel Smith
发明人： Scott Edmond Ellis , Aaron Ezekiel Smith
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A platform cooling arrangement in a turbine rotor blade having a platform positioned between an airfoil and a root. The rotor blade, along a side that coincides with a pressure side of the airfoil, includes a pressure side of the platform includes a topside extending from an airfoil base to a pressure side slashface. The platform cooling arrangement includes: a main plenum residing just inboard of the topside in the pressure side of the platform, the main plenum extending through the platform from an upstream end having an aft position to a downstream end having a forward position; and cooling apertures. Near the upstream end, the main plenum includes an aft switchback, and, between the aft switchback and the downstream end, a forward arc. Each of the cooling apertures extends from the main plenum to a port formed on the pressure side slashface.
摘要翻译：涡轮转子叶片中的平台冷却装置，其具有位于翼型件和根部之间的平台。转子叶片沿着与翼型件的压力侧重合的一侧，包括平台的压力侧，其包括从翼型基部延伸到压力侧斜面的顶侧。平台冷却装置包括：位于平台的压力侧的顶侧刚好内侧的主增压室，主增压室从具有后位的上游端延伸穿过平台到具有向前位置的下游端; 和冷却孔。在上游端附近，主增压室包括尾部折返，并且在后退和下游端之间具有前弧。每个冷却孔从主增压室延伸到形成在压力侧斜面上的端口。

10. 发明申请

US20140064983A1 AIRFOIL AND METHOD FOR MANUFACTURING AN AIRFOIL 审中-公开
标题翻译：飞行器和制造航空器的方法
公开(公告)号：US20140064983A1
公开(公告)日：2014-03-06
申请号：US13600717
申请日：2012-08-31
申请人： Mark Andrew Jones , Aaron Ezekiel Smith , Harika Senem Kahveci
发明人： Mark Andrew Jones , Aaron Ezekiel Smith , Harika Senem Kahveci
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/304 , F05D2260/202
摘要： An airfoil includes a pressure side, a suction side opposed to the pressure side, a cavity inside the airfoil between the pressure and suction sides, and a trailing edge downstream from the cavity between the pressure and suction sides. A first set of cooling passages through the trailing edge provide fluid communication from the cavity through the trailing edge. A first divider across each cooling passage in the first set of cooling passages extends from the pressure side to the suction side at the trailing edge.
摘要翻译：翼型件包括压力侧，与压力侧相对的吸入侧，在压力侧和吸力侧之间的翼型内的空腔，以及在压力侧和吸力侧之间的空腔下游的后缘。通过后缘的第一组冷却通道提供从空腔到后缘的流体连通。第一组冷却通道中的每个冷却通道的第一分隔件从后侧的压力侧延伸到吸入侧。

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