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1.发明授权Method of inspecting turbine internal cooling features using non-contact scanners 有权使用非接触式扫描仪检查涡轮机内部冷却功能的方法公开(公告)号：US07578178B2
公开(公告)日：2009-08-25
申请号：US11906030
申请日：2007-09-28
IPC分类号： G01M15/14
CPC分类号： G01M15/14 , F01D25/285 , F05D2260/80
摘要： A method of inspecting an internal feature of a gas turbine component includes removing a portion of the turbine component to expose the internal feature, treating the surfaces of the internal feature to provide the surfaces with a substantially uniform coloration, generating an electronic model of the internal feature, analyzing the electronic model generated with reference to a nominal electronic model, and providing an output based on the analysis of the electronic model generated.
摘要翻译： 检查燃气涡轮机部件的内部特征的方法包括移除涡轮机部件的一部分以暴露内部特征，处理内部特征的表面以使表面具有基本均匀的着色，产生内部的电子模型 特征，分析参考标称电子模型生成的电子模型，并且基于生成的电子模型的分析来提供输出。
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公开(公告)号：US20090089020A1
公开(公告)日：2009-04-02
申请号：US11906030
申请日：2007-09-28
CPC分类号： G01M15/14 , F01D25/285 , F05D2260/80
摘要： A method of inspecting an internal feature of a gas turbine component includes removing a portion of the turbine component to expose the internal feature, treating the surfaces of the internal feature to provide the surfaces with a substantially uniform coloration, generating an electronic model of the internal feature, analyzing the electronic model generated with reference to a nominal electronic model, and providing an output based on the analysis of the electronic model generated.
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公开(公告)号：US08011892B2
公开(公告)日：2011-09-06
申请号：US11769756
申请日：2007-06-28
CPC分类号： F01D5/3007 , F01D5/22 , F01D11/006 , F05D2260/96
摘要： A turbine blade damper-seal assembly includes a seal nested within a damper such that both the seal and damper are disposed to provide sealing between adjacent blade platforms. The seal traverses the seal slot in the damper and seals the gap between adjacent blade platforms for the full axial length of the neck cavity between adjacent blades. The damper is located in an aft most position and includes features to facilitate vibration-dampening performance. The damper also includes features that cause entrapment between blades and therefore avoids the conventionally required protrusions on the blade to retain it in the assembled position.
摘要翻译： 涡轮叶片阻尼器密封组件包括嵌在阻尼器内的密封件，使得密封件和阻尼器都设置成在相邻的刀片平台之间提供密封。 密封件穿过阻尼器中的密封槽并密封相邻刀片平台之间的间隙，用于相邻刀片之间的颈腔的整个轴向长度。 阻尼器位于最靠前的位置，并且包括有助于减振性能的特征。 阻尼器还包括引起叶片之间夹带的特征，因此避免了刀片上常规需要的突出物以将其保持在组装位置。
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公开(公告)号：US20130206733A1
公开(公告)日：2013-08-15
申请号：US13544031
申请日：2012-07-09
申请人： Glenn Levasseur , Edward F. Pietraszkiewicz , Mark F. Zelesky , Dominic J. Mongillo, JR. , Kevin J. Klinefelter , Stephen D. Doll , Markus W. Fritch
发明人： Glenn Levasseur , Edward F. Pietraszkiewicz , Mark F. Zelesky , Dominic J. Mongillo, JR. , Kevin J. Klinefelter , Stephen D. Doll , Markus W. Fritch
IPC分类号： B23H9/00
CPC分类号： B23H9/10 , B23H1/00 , B23H7/26 , B23H9/14 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676
摘要： A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges.
摘要翻译： 用于形成从壁的第一表面上的入口延伸到壁的第二表面上的出口的冷却孔的方法包括：通过放电加工形成冷却孔的扩散部分和出口上的后缘， 并在扩散段中形成纵向凸起。 计量部分从壁的第一表面上的入口延伸到壁的第二表面。 扩散部分从出口延伸到位于入口和出口之间的计量部分的一端。 出口在后缘处基本上是线性的或凸起的，并且叶片由纵向脊部分开。
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公开(公告)号：US09024226B2
公开(公告)日：2015-05-05
申请号：US13544031
申请日：2012-07-09
申请人： Glenn Levasseur , Edward F. Pietraszkiewicz , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Kevin J. Klinefelter , Stephen D. Doll , Markus W. Fritch
发明人： Glenn Levasseur , Edward F. Pietraszkiewicz , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Kevin J. Klinefelter , Stephen D. Doll , Markus W. Fritch
CPC分类号： B23H9/10 , B23H1/00 , B23H7/26 , B23H9/14 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676
摘要： A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges.
摘要翻译： 用于形成从壁的第一表面上的入口延伸到壁的第二表面上的出口的冷却孔的方法包括：通过放电加工形成冷却孔的扩散部分和出口上的后缘， 并在扩散段中形成纵向凸起。 计量部分从壁的第一表面上的入口延伸到壁的第二表面。 扩散部分从出口延伸到位于入口和出口之间的计量部分的一端。 出口在后缘处基本上是线性的或凸起的，并且叶片由纵向脊部分开。
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公开(公告)号：US20090004013A1
公开(公告)日：2009-01-01
申请号：US11769756
申请日：2007-06-28
IPC分类号： F01D5/10
CPC分类号： F01D5/3007 , F01D5/22 , F01D11/006 , F05D2260/96
摘要： A turbine blade damper-seal assembly includes a seal nested within a damper such that both the seal and damper are disposed to provide sealing between adjacent blade platforms. The seal traverses the seal slot in the damper and seals the gap between adjacent blade platforms for the full axial length of the neck cavity between adjacent blades. The damper is located in an aft most position and includes features to facilitate vibration-dampening performance. The damper also includes features that cause entrapment between blades and therefore avoids the conventionally required protrusions on the blade to retain it in the assembled position.
摘要翻译： 涡轮叶片阻尼器密封组件包括嵌在阻尼器内的密封件，使得密封件和阻尼器都设置成在相邻的刀片平台之间提供密封。 密封件穿过阻尼器中的密封槽并密封相邻刀片平台之间的间隙，用于相邻刀片之间的颈腔的整个轴向长度。 阻尼器位于最靠前的位置，并且包括有助于减振性能的特征。 阻尼器还包括引起叶片之间夹带的特征，因此避免了刀片上常规需要的突出物以将其保持在组装位置。
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公开(公告)号：US20080003096A1
公开(公告)日：2008-01-03
申请号：US11477293
申请日：2006-06-29
申请人： Atul Kohli , Joseph B. Staubach , Stephen D. Doll
发明人： Atul Kohli , Joseph B. Staubach , Stephen D. Doll
IPC分类号： F03B11/00
CPC分类号： F01D5/186 , F05D2250/70 , F05D2260/202 , F05D2260/221 , Y02T50/676
摘要： A cooling hole for a gas turbine engine component has a bi-lobed shape to improve cooling effectiveness. The gas turbine engine component has a first outer surface and a second outer surface separated from each other by a thickness. The cooling hole extends through the thickness from a first opening at the first outer surface to a second opening at the second outer surface. The first and second openings are defined by shapes that are different from each other. One of the first and second openings has the bi-lobed shape.
摘要翻译： 用于燃气涡轮发动机部件的冷却孔具有双叶形状以改善冷却效果。 燃气涡轮发动机部件具有彼此隔开一定厚度的第一外表面和第二外表面。 冷却孔从第一外表面的第一开口延伸穿过厚度，在第二外表面延伸到第二开口。 第一和第二开口由彼此不同的形状限定。 第一和第二开口中的一个具有双叶形状。
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