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

US06945750B2 Turbine blade 有权
标题翻译：涡轮叶片
公开(公告)号：US06945750B2
公开(公告)日：2005-09-20
申请号：US10724091
申请日：2003-12-01
申请人： Bruno Benedetti , Said Jaamei , David Johns , Joerg Krueckels
发明人： Bruno Benedetti , Said Jaamei , David Johns , Joerg Krueckels
IPC分类号： B23H9/10 , F01D5/18 , F01D9/02 , F01D25/12 , F01D9/06
CPC分类号： F01D5/186 , B23H9/10 , F01D5/187 , F01D9/02 , F05D2230/12 , F05D2240/81 , F05D2260/2212
摘要： A turbine blade for a gas turbine has a hollow airfoil extending from a platform. There is a fillet between the airfoil and the platform, both on the pressure side and on the suction side of the airfoil. The fillet contains a cooling bore extending along part of the length of the fillet, having a first end communicating with the interior of the turbine blade for receiving a gaseous coolant and a second end communicating with the exterior of the turbine blade. The cooling may be formed by electro-discharge machining.
摘要翻译：用于燃气轮机的涡轮叶片具有从平台延伸的中空翼型件。在翼型和平台之间都有在翼型的压力侧和吸力侧上的圆角。所述圆角包含沿所述圆角长度的一部分延伸的冷却孔，所述冷却孔具有与所述涡轮机叶片的内部连通的第一端，用于接收气态冷却剂和与所述涡轮叶片的外部连通的第二端。冷却可以通过放电加工形成。

2. 发明授权

US08182225B2 Blade for a gas turbine 有权
标题翻译：燃气轮机叶片
公开(公告)号：US08182225B2
公开(公告)日：2012-05-22
申请号：US12876602
申请日：2010-09-07
申请人： Joerg Krueckels , Roland Dueckershoff , Martin Schnieder
发明人： Joerg Krueckels , Roland Dueckershoff , Martin Schnieder
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2250/23 , F05D2250/231 , F05D2260/2212 , Y02T50/676
摘要： A blade for a gas turbine includes a leading edge running in a longitudinal direction substantially radially to an axis of the turbine; a trailing edge running in the longitudinal direction; a blade body disposed between the leading edge and the trailing edge so as to define a pressure side and a suction side; an exit slot disposed in the blade body in an area of the trailing edge and running in the longitudinal direction and configured to discharge a cooling medium from an interior of the blade body; and a row of first and second control elements disposed in the exit slot in a distributed manner in the longitudinal direction and configured to control a mass flow of the cooling medium exiting through the exit slot, the first control elements having a first configuration and the second control elements having a second configuration different from the first configuration.
摘要翻译：一种用于燃气轮机的叶片包括沿着基本上径向相对于涡轮轴线的纵向方向延伸的前缘; 沿纵向延伸的后缘; 刀片体，其设置在所述前缘和所述后缘之间，以限定压力侧和吸力侧; 出口狭槽，其设置在所述后缘的区域中并沿所述纵向方向延伸并且构造成从所述叶片本体的内部排出冷却介质; 以及一排第一和第二控制元件，其沿长度方向以分布的方式设置在出口槽中，并被配置为控制从出口槽排出的冷却介质的质量流量，第一控制元件具有第一配置，第二控制元件具有第二配置控制元件具有不同于第一配置的第二配置。

3. 发明授权

US08444376B2 Cooled constructional element for a gas turbine 有权
标题翻译：用于燃气轮机的冷却结构元件
公开(公告)号：US08444376B2
公开(公告)日：2013-05-21
申请号：US13192656
申请日：2011-07-28
申请人： Joerg Krueckels , Milan Pathak
发明人： Joerg Krueckels , Milan Pathak
IPC分类号： F04D31/00
CPC分类号： F01D5/187 , F01D25/12 , F05D2240/81 , F05D2260/201
摘要： A cooled constructional element for a gas turbine includes a wall having a front and a rear side. The front side is configured to be thermally loaded during operation of the turbine, and the rear side has a plurality of pins projecting therefrom in a two-dimensional distribution, the two-dimensional distribution including a higher density distribution of pins in a critical zone of the cooled constructional element than in the remaining regions of the cooled constructional element. A device is configured to create jets of a cooling medium that are directed onto the rear side of the wall in a region of the plurality of pins so as to cool the rear side of the wall by impingement.
摘要翻译：用于燃气涡轮机的冷却结构元件包括具有前侧和后侧的壁。前侧被构造成在涡轮机的运行期间被热负载，并且后侧具有以二维分布从其突出的多个销，所述二维分布包括在关键区域中的销的较高密度分布冷却结构元件比冷却结构元件的其余区域要冷。一种装置构造成在多个销的区域中产生指向壁的后侧的冷却介质的喷嘴，以便通过冲击来冷却壁的后侧。

4. 发明申请

US20120020768A1 COOLED CONSTRUCTIONAL ELEMENT FOR A GAS TURBINE 有权
标题翻译：用于气体涡轮的冷却结构元件
公开(公告)号：US20120020768A1
公开(公告)日：2012-01-26
申请号：US13192656
申请日：2011-07-28
申请人： Joerg Krueckels , Milan Pathak
发明人： Joerg Krueckels , Milan Pathak
IPC分类号： F01D25/12 , F01D9/00
CPC分类号： F01D5/187 , F01D25/12 , F05D2240/81 , F05D2260/201
摘要： A cooled constructional element for a gas turbine includes a wall having a front and a rear side. The front side is configured to be thermally loaded during operation of the turbine, and the rear side has a plurality of pins projecting therefrom in a two-dimensional distribution, the two-dimensional distribution including a higher density distribution of pins in a critical zone of the cooled constructional element than in the remaining regions of the cooled constructional element. A device is configured to create jets of a cooling medium that are directed onto the rear side of the wall in a region of the plurality of pins so as to cool the rear side of the wall by impingement.
摘要翻译：用于燃气涡轮机的冷却结构元件包括具有前侧和后侧的壁。前侧被构造成在涡轮机的运行期间被热负载，并且后侧具有以二维分布从其突出的多个销，所述二维分布包括在关键区域中的销的较高密度分布冷却结构元件比冷却结构元件的其余区域要冷。一种装置构造成在多个销的区域中产生指向壁的后侧的冷却介质的喷嘴，以便通过冲击来冷却壁的后侧。

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