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公开(公告)号：US07229245B2
公开(公告)日：2007-06-12
申请号：US10891400
申请日：2004-07-14
申请人： Charles A. Ellis , David Parker , J. Page Strohl , David Medrano
发明人： Charles A. Ellis , David Parker , J. Page Strohl , David Medrano
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F05D2260/941
摘要： A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their resistance to thermal deflection. This is accomplished by placing an opening along the vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.
摘要翻译： 公开了一种用于燃气涡轮发动机的叶片组件，其具有较低的热致应力，导致改进的部件耐久性。 叶片组件翼型中的应力通过增加叶片平台的柔性并降低其对热偏转的抵抗力而降低。 这是通过沿着叶片组装轨道放置开口来实现的，其减小了平台的有效刚度，从而降低了叶片组件的翼型件中的操作应力。 然后将可拆卸密封件放置在开口中，以防止不期望的泄漏，同时保持增加的平台灵活性的益处。
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公开(公告)号：US07293957B2
公开(公告)日：2007-11-13
申请号：US11692505
申请日：2007-03-28
申请人： Charlie Ellis , David Parker , J. Page Strohl , David Medrano
发明人： Charlie Ellis , David Parker , J. Page Strohl , David Medrano
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D11/005 , F05D2260/941
摘要： A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing its resistance to thermal deflection. This is accomplished by placing an opening along the innermost vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.
摘要翻译： 公开了一种用于燃气涡轮发动机的叶片组件，其具有较低的热致应力，导致改进的部件耐久性。 叶片组件翼型中的应力通过增加叶片平台的柔性并降低其对热偏转的抵抗力而降低。 这是通过沿着最内侧叶片组装轨道放置开口来实现的，该开口减小了平台的有效刚度，从而降低了叶片组件的翼型件中的操作应力。 然后将可拆卸密封件放置在开口中，以防止不期望的泄漏，同时保持增加的平台灵活性的益处。
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公开(公告)号：US20060013685A1
公开(公告)日：2006-01-19
申请号：US10891400
申请日：2004-07-14
申请人： Charles Ellis , David Parker , J. Page Strohl , David Medrano
发明人： Charles Ellis , David Parker , J. Page Strohl , David Medrano
IPC分类号： F01D1/02
CPC分类号： F01D9/041 , F05D2260/941
摘要： A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their resistance to thermal deflection. This is accomplished by placing an opening along the vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.
摘要翻译： 公开了一种用于燃气涡轮发动机的叶片组件，其具有较低的热致应力，导致改进的部件耐久性。 叶片组件翼型中的应力通过增加叶片平台的柔性并降低其对热偏转的抵抗力而降低。 这是通过沿着叶片组装轨道放置开口来实现的，其减小了平台的有效刚度，从而降低了叶片组件的翼型件中的操作应力。 然后将可拆卸密封件放置在开口中，以防止不期望的泄漏，同时保持增加的平台灵活性的益处。
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公开(公告)号：US08057188B2
公开(公告)日：2011-11-15
申请号：US12175822
申请日：2008-07-18
申请人： David Parker , J. Page Strohl , Richard Ramirez , Robert Moore
发明人： David Parker , J. Page Strohl , Richard Ramirez , Robert Moore
IPC分类号： B63H1/26 , B63H7/02 , B64C11/16 , B64C27/46 , F01D5/14 , F03B3/12 , F03B7/00 , F03D11/02 , F04D29/38
CPC分类号： F01D5/141 , F05D2220/3216
摘要： A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.
摘要翻译： 公开了具有根据表1的轮廓的翼型的压缩机部件。 诸如压缩机叶片的压缩机部件在翼型跨度的一部分上具有增加的厚度，以增加刚度。 此外，已经重新安装翼型件以在叶片根部/附接区域中引起压缩应力。 增加的刚度和复位翼型结合起来以改善压缩机部件的高循环疲劳能力。
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公开(公告)号：US09322089B2
公开(公告)日：2016-04-26
申请号：US11492423
申请日：2006-07-25
申请人： Charles Biondo , J. Page Strohl , Jeffery W. Samuelson , Gerhard E. Fuchs , Stanley T. Wlodek , Ramona T. Wlodek
CPC分类号： C22F1/10 , C22C19/03 , C22C19/05 , C22C19/056
摘要： A nickel-based alloy suitable for casting gas turbine components having a lower density and basic heat treating process while achieving improved strength is disclosed. Multiple embodiments of the alloy are disclosed capable of providing both directionally-solidified and equiaxed castings. Also disclosed is a method of making a cast and heat treated article utilizing the improved nickel-base alloy.
摘要翻译： 公开了一种适用于铸造具有较低密度和基础热处理工艺的燃气轮机部件同时实现改进的强度的镍基合金。 公开了能够提供定向凝固和等轴铸件的合金的多个实施例。 还公开了利用改进的镍基合金制造铸造和热处理制品的方法。
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公开(公告)号：US20080193290A1
公开(公告)日：2008-08-14
申请号：US11674731
申请日：2007-02-14
CPC分类号： F01D9/04 , F01D9/042 , F01D25/246 , F01D25/28 , Y10T29/49323
摘要： Embodiments for a compressor stator vane assembly in a gas turbine engine are disclosed. In an embodiment of the present invention a stator vane assembly is provided having a plurality of vanes each with an attachment and channels machined into the forward and aft walls of the attachment. A forward hook ring segment is pressfit into the channel in the forward wall of the attachment and an aft hook ring is pressfit into the channel in the aft wall of the attachment. The hook ring segments join a plurality of vanes together so as to provide a uniform engagement of mounting slots in the compressor case. Such an arrangement increases the contact area between the hook rings and the compressor case such that damping of individual vane vibrations are improved and operating stresses are reduced.
摘要翻译： 公开了一种用于燃气涡轮发动机中的压缩机定子叶片组件的实施例。 在本发明的一个实施例中，定子叶片组件设置有多个叶片，每个叶片具有附接件和通道，其被加工成附件的前壁和后壁。 向前钩环段被压入附件的前壁中的通道中，并且后钩环被压入附件的后壁中的通道中。 钩环段将多个叶片连接在一起，以便提供压缩机壳体中的安装槽的均匀接合。 这种布置增加了钩环和压缩机壳体之间的接触面积，使得各个叶片振动的阻尼得到改善，并且降低了操作应力。
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公开(公告)号：US07101150B2
公开(公告)日：2006-09-05
申请号：US10842976
申请日：2004-05-11
申请人： Gary Bash , J. Page Strohl
发明人： Gary Bash , J. Page Strohl
CPC分类号： F01D9/042 , F05D2230/642 , F05D2240/80 , F05D2260/30
摘要： A vane assembly for a gas turbine is described wherein the vane assembly comprises a first vane and a second vane connected together by a plurality of flanges, at least one fastener, and at least one spring plate. The fastener and hole diameters in the respective flanges are sized such that the first vane and second vane are essentially pinned together along their inner flanges and allowed to adjust due to thermal growth along their outer flanges, while maintaining a constant seal along both inner and outer platform edges. The thermal growth along the outer flanges is made possible by oversized flange holes relative to the diameter of the fastener.
摘要翻译： 描述了一种用于燃气轮机的叶片组件，其中叶片组件包括通过多个凸缘，至少一个紧固件和至少一个弹簧板连接在一起的第一叶片和第二叶片。 相应凸缘中的紧固件和孔直径的尺寸使得第一叶片和第二叶片沿着其内凸缘基本上被固定在一起，并且由于沿着它们的外凸缘的热生长而允许调节，同时沿着内外两者保持恒定的密封 平台边缘。 通过相对于紧固件的直径的超大的凸缘孔，沿着外凸缘的热生长成为可能。
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公开(公告)号：US06769878B1
公开(公告)日：2004-08-03
申请号：US10434691
申请日：2003-05-09
IPC分类号： F01D514
CPC分类号： F01D5/141 , F01D5/187 , F05D2250/70 , F05D2260/221 , Y10S416/02
摘要： A turbine blade including an airfoil having a profile in accordance with Table 1 is disclosed. The turbine blade has a plurality of cooling passages extending radially outward through the airfoil. The aerodynamic profile of the airfoil has been reconfigured to further reduce overall heat load to the airfoil while paying particular attention to the leading edge region. Specifically, the airfoil leading edge, which is the life-limiting location of the turbine blade has been reconfigured to lower heat load and allow for increased cooling, thereby increasing turbine blade life.
摘要翻译： 公开了一种包括具有根据表1的轮廓的翼型的涡轮叶片。 涡轮机叶片具有径向向外延伸穿过翼型的多个冷却通道。 翼型的空气动力学特性已经被重新配置，以进一步降低翼型的总热负荷，同时特别注意前缘区域。 具体地说，作为涡轮叶片的寿命限制位置的翼型件前缘已被重构，以降低热负荷并允许增加冷却，从而增加涡轮机叶片寿命。
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公开(公告)号：US20100080729A1
公开(公告)日：2010-04-01
申请号：US11492423
申请日：2006-07-25
申请人： Charles Biondo , J. Page Strohl , Jeffery W. Samuelson , Gerhard E. Fuchs , Stanley T. Wlodek , Ramona T. Wlodek
发明人： Charles Biondo , J. Page Strohl , Jeffery W. Samuelson , Gerhard E. Fuchs , Stanley T. Wlodek , Ramona T. Wlodek
CPC分类号： C22F1/10 , C22C19/03 , C22C19/05 , C22C19/056
摘要： A nickel-based alloy suitable for casting gas turbine components having a lower density and basic heat treating process while achieving improved strength is disclosed. Multiple embodiments of the alloy are disclosed capable of providing both directionally-solidified and equiaxed castings. Also disclosed is a method of making a cast and heat treated article utilizing the improved nickel-base alloy.
摘要翻译： 公开了一种适用于铸造具有较低密度和基础热处理工艺的燃气轮机部件同时实现改进的强度的镍基合金。 公开了能够提供定向凝固和等轴铸件的合金的多个实施例。 还公开了利用改进的镍基合金制造铸造和热处理制品的方法。
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公开(公告)号：US07618234B2
公开(公告)日：2009-11-17
申请号：US11674731
申请日：2007-02-14
IPC分类号： F01D9/04
CPC分类号： F01D9/04 , F01D9/042 , F01D25/246 , F01D25/28 , Y10T29/49323
摘要： Embodiments for a compressor stator vane assembly in a gas turbine engine are disclosed. In an embodiment of the present invention a stator vane assembly is provided having a plurality of vanes each with an attachment and channels machined into the forward and aft walls of the attachment. A forward hook ring segment is pressfit into the channel in the forward wall of the attachment and an aft hook ring is pressfit into the channel in the aft wall of the attachment. The hook ring segments join a plurality of vanes together so as to provide a uniform engagement of mounting slots in the compressor case. Such an arrangement increases the contact area between the hook rings and the compressor case such that damping of individual vane vibrations are improved and operating stresses are reduced.
摘要翻译： 公开了一种用于燃气涡轮发动机中的压缩机定子叶片组件的实施例。 在本发明的一个实施例中，定子叶片组件设置有多个叶片，每个叶片具有附接件和通道，其被加工成附件的前壁和后壁。 向前钩环段被压入附件的前壁中的通道中，并且后钩环被压入附件的后壁中的通道中。 钩环段将多个叶片连接在一起，以便提供压缩机壳体中的安装槽的均匀接合。 这种布置增加了钩环和压缩机壳体之间的接触面积，使得各个叶片振动的阻尼得到改善，并且降低了操作应力。
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