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61. 发明申请

US20070009359A1 Industrial gas turbine blade assembly 有权
标题翻译：工业燃气轮机叶片组件
公开(公告)号：US20070009359A1
公开(公告)日：2007-01-11
申请号：US11167445
申请日：2005-06-27
申请人： Anthony Cherolis , Jesse Christophel , William Abdel-Messeh
发明人： Anthony Cherolis , Jesse Christophel , William Abdel-Messeh
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/90 , F05D2240/81 , F05D2250/314 , F05D2260/201 , F05D2260/202
摘要： A gas turbine blade assembly includes a neck defining a neck cavity, and has a first end and a second end at an opposite side relative to the first end. A platform has first and second sides. The first side is disposed on and faces the second end of the neck. An airfoil is supported on the second side of the platform. The neck, platform and airfoil define an inner cooling passage extending through the neck, platform and into the airfoil. The neck defines at least one core channel extending between the cooling passage and the neck cavity. The platform defines at least one film cooling channel extending from the first side facing the neck cavity to the second side disposed exterior to the airfoil to permit cooling air to flow through the inner cooling passage into the neck cavity and through the platform exterior to the airfoil.
摘要翻译：燃气轮机叶片组件包括限定颈腔的颈部，并且在相对于第一端的相对侧具有第一端和第二端。一个平台有第一面和第二面。第一侧设置在颈部的第二端并面向颈部的第二端。翼片支撑在平台的第二侧上。颈部，平台和翼型件限定了延伸穿过颈部，平台并进入翼型的内部冷却通道。颈部限定在冷却通道和颈腔之间延伸的至少一个芯通道。平台限定了至少一个薄膜冷却通道，其从面向颈部空腔的第一侧延伸到设置在翼型件外部的第二侧，以允许冷却空气流过内部冷却通道进入颈部腔并且通过翼面外部平台。

62. 发明授权

US07114916B2 Tailored turbulation for turbine blades 有权
标题翻译：涡轮叶片的定制紊流
公开(公告)号：US07114916B2
公开(公告)日：2006-10-03
申请号：US10774822
申请日：2004-02-09
申请人： Bryan P. Dube , William Abdel-Messeh , Daniel Herrera , Richard Page
发明人： Bryan P. Dube , William Abdel-Messeh , Daniel Herrera , Richard Page
IPC分类号： F03D11/00
CPC分类号： F01D5/187 , F05D2250/30 , F05D2260/2212 , F05D2260/22141
摘要： A turbine blade having improved cooling characteristics is provided. The turbine blade has an airfoil portion having a span, and at least one cooling passageway in the airfoil portion extending from a root portion of the airfoil portion to a tip portion of the airfoil portion. A plurality of turbulation promotion devices are placed in the at least one cooling passageway. The turbulation promotion devices have a P/e ratio which varies along the span of the airfoil portion, where P is the pitch between adjacent turbulation promotion devices and e is the height of the turbulation promotion devices.
摘要翻译：提供了具有改进的冷却特性的涡轮叶片。涡轮机叶片具有翼部，翼型部分具有跨度，翼型部分中的至少一个冷却通道从翼型部分的根部延伸到翼型部分的顶端部分。多个紊流促进装置被放置在至少一个冷却通道中。紊流促进装置具有沿翼型部分的跨度变化的P / e比，其中P是相邻的紊流促进装置之间的间距，e是紊流促进装置的高度。

63. 发明授权

US06997675B2 Turbulated hole configurations for turbine blades 有权
标题翻译：涡轮叶片的涡轮孔配置
公开(公告)号：US06997675B2
公开(公告)日：2006-02-14
申请号：US10774989
申请日：2004-02-09
申请人： Bryan P. Dube , William Abdel-Messeh , Daniel Herrera , Richard Page
发明人： Bryan P. Dube , William Abdel-Messeh , Daniel Herrera , Richard Page
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F05D2250/141 , F05D2250/25 , F05D2250/30 , F05D2250/314 , F05D2260/2212 , F05D2260/22141
摘要： A turbine blade having improved cooling has an airfoil with a root end and a tip end and at least one cooling passageway in the airfoil. Each cooling passageway extends from the root end to the tip end and has a circular cross-section. A plurality of turbulation promotion devices are arranged in each cooling passageway. Each of the turbulation promotion devices is arcuate in shape and circumscribes an arc less than 180 degrees.
摘要翻译：具有改进的冷却的涡轮机叶片具有具有根端和顶端的翼型和在翼型中的至少一个冷却通道。每个冷却通道从根端延伸到尖端并具有圆形横截面。在每个冷却通道中布置有多个紊流促进装置。每个紊流促进装置的形状都是弧形的，并且外接一个小于180度的弧。

64. 发明申请

US20050175454A1 Turbulated hole configurations for turbine blades 有权
标题翻译：涡轮叶片的涡轮孔配置
公开(公告)号：US20050175454A1
公开(公告)日：2005-08-11
申请号：US10774989
申请日：2004-02-09
申请人： Bryan Dube , William Abdel-Messeh , Daniel Herrera , Richard Page
发明人： Bryan Dube , William Abdel-Messeh , Daniel Herrera , Richard Page
IPC分类号： F01D5/18 , B63H1/14
CPC分类号： F01D5/187 , F05D2250/141 , F05D2250/25 , F05D2250/30 , F05D2250/314 , F05D2260/2212 , F05D2260/22141
摘要： A turbine blade having improved cooling has an airfoil with a root end and a tip end and at least one cooling passageway in the airfoil. Each cooling passageway extends from the root end to the tip end and has a circular cross-section. A plurality of turbulation promotion devices are arranged in each cooling passageway. Each of the turbulation promotion devices is arcuate in shape and circumscribes an arc less than 180 degrees.
摘要翻译：具有改进的冷却的涡轮机叶片具有具有根端和顶端的翼型和在翼型中的至少一个冷却通道。每个冷却通道从根端延伸到尖端并具有圆形横截面。在每个冷却通道中布置有多个紊流促进装置。每个紊流促进装置的形状都是弧形的，并且外接一个小于180度的弧。

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