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公开(公告)号：US06951447B2
公开(公告)日：2005-10-04
申请号：US10738288
申请日：2003-12-17
申请人： Anthony Cherolis , Wieslaw A. Chlus
发明人： Anthony Cherolis , Wieslaw A. Chlus
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/141 , F05D2230/80 , F05D2240/80 , F05D2250/71 , Y02T50/673
摘要： A turbine blade has an undercut beneath its platform at a trailing edge. The undercut has a complex shape to move thermal stress concentration away from the platform. A preferred undercut shape has a pair of curved fillets at upper and lower extents of the undercut with an intermediate straight section. The intermediate straight section is preferably parallel to a principle stress field of the platform.
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公开(公告)号：US07175386B2
公开(公告)日：2007-02-13
申请号：US10738842
申请日：2003-12-17
申请人： Anthony Cherolis , Wieslaw A. Chlus
发明人： Anthony Cherolis , Wieslaw A. Chlus
IPC分类号： F01D5/14
CPC分类号： F01D5/187 , F05D2260/2212 , Y02T50/676
摘要： A blade for a gas turbine engine includes a trailing edge cooling chamber, wherein the pressure and suction sides are connected by an array of spaced pedestals. The pedestals in a region most subject to thermal stresses are formed to be elliptical, such that the thermal stresses are spread over a larger area. Thus, stress concentrations are reduced. Also, various sized cylindrical pedestals may be used at other locations.
摘要翻译： 用于燃气涡轮发动机的叶片包括后缘冷却室，其中压力和吸力侧通过间隔开的基座的阵列连接。 最受热应力的区域中的基座形成为椭圆形，使得热应力分布在更大的面积上。 因此，应力集中减少。 此外，可以在其他位置使用各种尺寸的圆柱形基座。
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公开(公告)号：US20070009359A1
公开(公告)日：2007-01-11
申请号：US11167445
申请日：2005-06-27
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 。
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公开(公告)号：US20060029500A1
公开(公告)日：2006-02-09
申请号：US10911298
申请日：2004-08-04
申请人： Anthony Cherolis , Wieslaw Chlus
发明人： Anthony Cherolis , Wieslaw Chlus
IPC分类号： F01D11/00
CPC分类号： F01D5/147 , Y02T50/672 , Y02T50/673
摘要： A turbine blade construction having a flared buttress is disclosed. The turbine blade is of the type adapted for use within a gas turbine engine and includes a buttress so as to fortify the area of the blade between the airfoil and the serrated root fillet. The bottom of the buttress is flared to reduce the stress concentration due to the abrupt termination of the buttress in close proximity of the mounting root. By employing a flared buttress, the blade is able to withstand the operating conditions of the turbine within the gas turbine engine over an extended period of time. The turbine blade may also include a mounting root with a compound radiused fillet to further enable the blade to withstand operating stress.
摘要翻译： 公开了一种具有扩口支撑的涡轮叶片结构。 涡轮叶片是适于在燃气涡轮发动机内使用的类型，并且包括支撑件，以便加强翼型件与锯齿形根圆角之间的叶片区域。 支撑的底部被张开，以减小紧靠安装根部的支撑件突然终止引起的应力集中。 通过使用扩口支撑，叶片能够在延长的时间段内承受燃气涡轮发动机内的涡轮机的操作条件。 涡轮机叶片还可以包括具有复合圆角圆角的安装根部，以进一步使叶片承受操作应力。
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公开(公告)号：US20050135936A1
公开(公告)日：2005-06-23
申请号：US10738288
申请日：2003-12-17
申请人： Anthony Cherolis , Wieslaw Chlus
发明人： Anthony Cherolis , Wieslaw Chlus
CPC分类号： F01D5/147 , F01D5/141 , F05D2230/80 , F05D2240/80 , F05D2250/71 , Y02T50/673
摘要： A turbine blade has an undercut beneath its platform at a trailing edge. The undercut has a complex shape to move thermal stress concentration away from the platform. A preferred undercut shape has a pair of curved fillets at upper and lower extents of the undercut with an intermediate straight section. The intermediate straight section is preferably parallel to a principle stress field of the platform.
摘要翻译： 涡轮叶片在其后缘处具有在其平台下方的底切。 底切具有复杂的形状，以使热应力集中远离平台。 优选的底切形状在底切的上部和下部具有一对具有中间直线部分的弧形圆角。 中间直线段最好平行于平台的原理应力场。
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公开(公告)号：US07708525B2
公开(公告)日：2010-05-04
申请号：US11167445
申请日：2005-06-27
IPC分类号： F01D5/08
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 。
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公开(公告)号：US20050135922A1
公开(公告)日：2005-06-23
申请号：US10738842
申请日：2003-12-17
申请人： Anthony Cherolis , Wieslaw Chlus
发明人： Anthony Cherolis , Wieslaw Chlus
CPC分类号： F01D5/187 , F05D2260/2212 , Y02T50/676
摘要： A blade for a gas turbine engine includes a trailing edge cooling chamber, wherein the pressure and suction sides are connected by an array of spaced pedestals. The pedestals in a region most subject to thermal stresses are formed to be elliptical, such that the thermal stresses are spread over a larger area. Thus, stress concentrations are reduced. Also, various sized cylindrical pedestals may be used at other locations.
摘要翻译： 用于燃气涡轮发动机的叶片包括后缘冷却室，其中压力和吸力侧通过间隔开的基座的阵列连接。 最受热应力的区域中的基座形成为椭圆形，使得热应力分布在更大的面积上。 因此，应力集中减少。 此外，可以在其他位置使用各种尺寸的圆柱形基座。
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