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公开(公告)号：US08142137B2
公开(公告)日：2012-03-27
申请号：US12323736
申请日：2008-11-26
申请人： Chris Johnston , Gary Bash , Tim teRiele , David Parker , James Page Strohl
发明人： Chris Johnston , Gary Bash , Tim teRiele , David Parker , James Page Strohl
CPC分类号： F01D5/188 , F01D9/041 , F02C7/12 , F05D2240/81 , F05D2260/202 , Y10S416/50
摘要： A gas turbine vane to improve vane performance by addressing known failure mechanisms. A cooling circuit to the trailing edge of a vane airfoil is fed from the outer diameter platform, which prevents failure due to an oxidized and eroded airfoil trailing edge. The gas turbine includes an outer diameter platform, a hollow airfoil and an inner diameter platform with a plurality of cooling tubes extending radially through the airfoil. The cooling tubes are open at the outer diameter end and closed with covers at the inner diameter end. The inner diameter platform is also cooled and includes a meterplate for a portion of the cooling passageway and includes an undercut to improve thermal deflections of the inner diameter platform.
摘要翻译： 一种燃气轮机叶片，通过解决已知的故障机制来改善叶片性能。 从外径平台供给到叶片翼型的后缘的冷却回路，这防止由于氧化和侵蚀的翼型后缘造成的故障。 燃气轮机包括外径平台，中空翼型件和具有径向延伸穿过翼型件的多个冷却管的内径平台。 冷却管在外径端开口，在内径端用盖封闭。 内径平台也被冷却，并且包括用于冷却通道的一部分的仪表板，并且包括底切以改善内径平台的热偏转。
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公开(公告)号：US20100129196A1
公开(公告)日：2010-05-27
申请号：US12323736
申请日：2008-11-26
申请人： Chris Johnston , Gary Bash , Tim teRiele , David Parker , James Page Strohl
发明人： Chris Johnston , Gary Bash , Tim teRiele , David Parker , James Page Strohl
IPC分类号： F02C7/12
CPC分类号： F01D5/188 , F01D9/041 , F02C7/12 , F05D2240/81 , F05D2260/202 , Y10S416/50
摘要： A gas turbine vane to improve vane performance by addressing known failure mechanisms. A cooling circuit to the trailing edge of a vane airfoil is fed from the outer diameter platform, which prevents failure due to an oxidized and eroded airfoil trailing edge. The gas turbine includes an outer diameter platform, a hollow airfoil and an inner diameter platform with a plurality of cooling tubes extending radially through the airfoil. The cooling tubes are open at the outer diameter end and closed with covers at the inner diameter end. The inner diameter platform is also cooled and includes a meterplate for a portion of the cooling passageway and includes an undercut to improve thermal deflections of the inner diameter platform.
摘要翻译： 一种燃气轮机叶片，通过解决已知的故障机制来改善叶片性能。 从外径平台供给到叶片翼型的后缘的冷却回路，这防止由于氧化和侵蚀的翼型后缘造成的故障。 燃气轮机包括外径平台，中空翼型件和具有径向延伸穿过翼型件的多个冷却管的内径平台。 冷却管在外径端开口，在内径端用盖封闭。 内径平台也被冷却，并且包括用于冷却通道的一部分的仪表板，并且包括底切以改善内径平台的热偏转。
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公开(公告)号：US20100284815A1
公开(公告)日：2010-11-11
申请号：US12273695
申请日：2008-11-19
申请人： David Parker , James Page Strohl
发明人： David Parker , James Page Strohl
CPC分类号： F01D5/14 , F01D5/147 , Y10T29/49336
摘要： A gas turbine engine blade or vane having a first platform, an airfoil, and a compound fillet extending about a region where the airfoil joins the first platform is disclosed. The compound fillet has a first conic surface and a second conic surface, with the first conic surface tangent to the airfoil and to an offset platform surface and the second conic surface tangent to the first conic surface and the first platform. The two conic surfaces are of different sizes, with different radii, and the conic surfaces can vary in size about the periphery of the joint between the airfoil and the first platform.
摘要翻译： 公开了一种燃气涡轮发动机叶片或叶片，其具有第一平台，翼型和围绕翼型件连接第一平台的区域延伸的复合圆角。 复合圆角具有第一圆锥面和第二圆锥面，第一圆锥面与翼型相切，并且与偏移平台表面相切，第二圆锥面与第一圆锥面和第一平面相切。 两个锥形表面具有不同的尺寸，具有不同的半径，锥形表面可以围绕翼型件和第一平台之间的接头的周边尺寸变化。
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公开(公告)号：US08287241B2
公开(公告)日：2012-10-16
申请号：US12275911
申请日：2008-11-21
申请人： James Page Strohl , David Parker
发明人： James Page Strohl , David Parker
IPC分类号： B64C11/16
CPC分类号： F01D5/141 , F05D2240/122 , F05D2240/304
摘要： A gas turbine blade having reduced stresses around a regions where the airfoil training edge joins the platform is disclosed. The lower stresses are achieved due to an undercut region proximate the blade trailing edge being placed in the platform. The undercut region has a compound fillet radius formed from two single and tangent radii where the first radius closer to the airfoil is larger than the second radius such that a ratio of R1/R2 is approximately 2.0 to 2.5.
摘要翻译： 公开了一种在机翼训练边缘连接平台的区域周围具有减小的应力的燃气轮机叶片。 由于靠近叶片后缘的底切区域被放置在平台中，实现了较低的应力。 底切区域具有由两个单个和切线半径形成的复合圆角半径，其中靠近翼型的第一半径大于第二半径，使得R1 / R2的比率为约2.0至2.5。
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公开(公告)号：US20100129228A1
公开(公告)日：2010-05-27
申请号：US12275911
申请日：2008-11-21
申请人： James Page Strohl , David Parker
发明人： James Page Strohl , David Parker
IPC分类号： B64C11/16
CPC分类号： F01D5/141 , F05D2240/122 , F05D2240/304
摘要： A gas turbine blade having reduced stresses around a regions where the airfoil training edge joins the platform is disclosed. The lower stresses are achieved due to an undercut region proximate the blade trailing edge being placed in the platform. The undercut region has a compound fillet radius formed from two single and tangent radii where the first radius closer to the airfoil is larger than the second radius such that a ratio of R1/R2 is approximately 2.0 to 2.5.
摘要翻译： 公开了一种在机翼训练边缘连接平台的区域周围具有减小的应力的燃气轮机叶片。 由于靠近叶片后缘的底切区域被放置在平台中，实现了较低的应力。 底切区域具有由两个单个和切线半径形成的复合圆角半径，其中靠近翼型的第一半径大于第二半径，使得R1 / R2的比率为约2.0至2.5。
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公开(公告)号：US08206095B2
公开(公告)日：2012-06-26
申请号：US12273695
申请日：2008-11-19
申请人： David Parker , James Page Strohl
发明人： David Parker , James Page Strohl
IPC分类号： F03D11/00
CPC分类号： F01D5/14 , F01D5/147 , Y10T29/49336
摘要： A gas turbine engine blade or vane having a first platform, an airfoil, and a compound fillet extending about a region where the airfoil joins the first platform is disclosed. The compound fillet has a first conic surface and a second conic surface, with the first conic surface tangent to the airfoil and to an offset platform surface and the second conic surface tangent to the first conic surface and the first platform. The two conic surfaces are of different sizes, with different radii, and the conic surfaces can vary in size about the periphery of the joint between the airfoil and the first platform.
摘要翻译： 公开了一种燃气涡轮发动机叶片或叶片，其具有第一平台，翼型和围绕翼型件连接第一平台的区域延伸的复合圆角。 复合圆角具有第一圆锥面和第二圆锥面，第一圆锥面与翼型相切，并且与偏移平台表面相切，第二圆锥面与第一圆锥面和第一平面相切。 两个锥形表面具有不同的尺寸，具有不同的半径，锥形表面可以围绕翼型件和第一平台之间的接头的周边尺寸变化。
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公开(公告)号：US08573942B2
公开(公告)日：2013-11-05
申请号：US12277471
申请日：2008-11-25
CPC分类号： F01D11/006 , F01D5/3007 , F05D2240/80 , F16J15/061 , F16J15/0887
摘要： A gas turbine engine component having an axial pin stop assembly that reduces stress around a seal pin damper slot between a platform and a buttress is disclosed. The seal pin damper slot is extended to the leading edge of the buttress and an axial pin stop seal extends into the pin damper slot to limit movement of the seal pin damper while relieving stress concentration at the interface between the buttress and platform.
摘要翻译： 公开了一种具有轴向销止动组件的燃气涡轮发动机部件，其减小了在平台和支柱之间的密封销阻尼器槽周围的应力。 密封销阻尼器狭槽延伸到支撑件的前缘，并且轴向销止动密封件延伸到销阻尼器狭槽中，以限制密封销阻尼器的移动，同时减轻支撑件和平台之间的界面处的应力集中。
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公开(公告)号：US08066482B2
公开(公告)日：2011-11-29
申请号：US12277704
申请日：2008-11-25
CPC分类号： F01D5/186 , F01D9/065 , F05D2240/81 , F05D2250/14 , F05D2260/202
摘要： A gas turbine engine component having shaped cooling holes that further enhances the cooling of a desired region while reducing stress levels in and around the cooling holes is disclosed. The cooling holes are generally elliptically-shaped and diffuse from a cooling fluid supply side to a discharge side and are oriented on the turbine component to reduce stress concentrations while directing the cooling fluid to a desired surface or location. The elliptical cooling holes have openings in the surface that have high points that are concentric and planar.
摘要翻译： 公开了一种具有成形冷却孔的燃气涡轮发动机部件，其进一步增强了所需区域的冷却，同时降低了冷却孔内和周围的应力水平。 冷却孔通常是椭圆形的并且从冷却流体供应侧扩散到排放侧，并且在涡轮机部件上定向以减少应力集中，同时将冷却流体引导到期望的表面或位置。 椭圆形冷却孔在表面具有开口，其具有同心和平面的高点。
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公开(公告)号：US08511982B2
公开(公告)日：2013-08-20
申请号：US12623940
申请日：2009-11-23
申请人： Adam L. Hart , Charles A. Ellis , Elliot I. Goodman , W. David Day , Gerald Raresheid , James Page Strohl
发明人： Adam L. Hart , Charles A. Ellis , Elliot I. Goodman , W. David Day , Gerald Raresheid , James Page Strohl
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F01D11/006 , F01D25/246 , F05D2240/80 , Y10T29/49323
摘要： A compressor diaphragm for a gas turbine engine having improved wear capability, manufacturability, and assembly techniques is disclosed. The diaphragm includes a shiplap-type joint at an outer vane platform for connecting to adjacent vane assemblies and a clamshell-like assembly of a seal box secures and seals regions around the inner vane platform of the compressor diaphragm so as to reduce wear between the seal box and the vane assemblies. The inner platform of the diaphragm segments are fastened to each other through circumferentially-oriented fasteners at the inner diameter platform.
摘要翻译： 公开了一种具有改进的耐磨性，可制造性和装配技术的用于燃气轮机的压缩机隔膜。 隔膜包括用于连接到相邻叶片组件的外叶片平台处的遮光板接头，并且密封箱的蛤壳状组件固定并密封围绕压缩机隔膜的内叶片平台的区域，以便减少密封件 箱和叶片组件。 隔膜段的内平台通过在内径平台处的周向定向的紧固件彼此紧固。
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公开(公告)号：US20110116917A1
公开(公告)日：2011-05-19
申请号：US12617983
申请日：2009-11-13
申请人： Yong Wang , James Page Strohl
发明人： Yong Wang , James Page Strohl
CPC分类号： F01D5/141 , F04D29/544 , F04D29/668
摘要： A compressor component having a non-linear thickness distribution along the span length is disclosed. By altering the thickness distribution to a non-linear arrangement so as to locally increase airfoil thickness proximate a mid-span location, the natural frequency of the airfoil is increased so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1. The present invention also includes a carrier segment or disk fabricated from a material so as to eliminate corrosion with the compressor component.
摘要翻译： 公开了沿跨度长度具有非线性厚度分布的压缩机部件。 通过将厚度分布改变为非线性布置以便在中跨位置附近局部地增加翼型件的厚度，翼型件的固有频率增加，从而与压缩机的关键发动机顺序不一致。 此外，本发明提供了根据表1的坐标的新型翼型轮廓。本发明还包括由材料制成的载体段或盘，以消除压缩机部件的腐蚀。
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