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公开(公告)号：US09074609B2
公开(公告)日：2015-07-07
申请号：US13027366
申请日：2011-02-15
申请人： Jiping Zhang , Kevin M. Light
发明人： Jiping Zhang , Kevin M. Light
CPC分类号： F04D29/542 , F01D5/081 , F01D9/041 , F01D9/065 , F01D11/24 , F04D29/584 , F05D2240/12 , F05D2260/20
摘要： A power turbine receiving cooling fluid from compressor apparatus is provided. The turbine comprises: fixed housing structure; a support shaft rotatably supported in the housing structure; at least one disk overhung on the support shaft and coupled to the support shaft so as to rotate with the support shaft; and cooling fluid structure. The at least one disk is formed from a low-alloy-content steel. The cooling fluid supply structure extends through the support shaft and the at least one disk so as to supply cooling fluid to the at least one disk.
摘要翻译： 提供从压缩机装置接收冷却流体的动力涡轮机。 涡轮机包括：固定的外壳结构; 可旋转地支撑在所述壳体结构中的支撑轴; 至少一个盘悬挂在所述支撑轴上并且联接到所述支撑轴以与所述支撑轴一起旋转; 和冷却流体结构。 所述至少一个盘由低合金含量的钢形成。 冷却流体供应结构延伸穿过支撑轴和至少一个盘，以将冷却流体供应到至少一个盘。
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公开(公告)号：US20120204574A1
公开(公告)日：2012-08-16
申请号：US13027366
申请日：2011-02-15
申请人： Jiping Zhang , Kevin M. Light
发明人： Jiping Zhang , Kevin M. Light
CPC分类号： F04D29/542 , F01D5/081 , F01D9/041 , F01D9/065 , F01D11/24 , F04D29/584 , F05D2240/12 , F05D2260/20
摘要： A power turbine receiving cooling fluid from compressor apparatus is provided. The turbine comprises: fixed housing structure; a support shaft rotatably supported in the housing structure; at least one disk overhung on the support shaft and coupled to the support shaft so as to rotate with the support shaft; and cooling fluid structure. The at least one disk is formed from a low-alloy-content steel. The cooling fluid supply structure extends through the support shaft and the at least one disk so as to supply cooling fluid to the at least one disk.
摘要翻译： 提供从压缩机装置接收冷却流体的动力涡轮机。 涡轮机包括：固定的外壳结构; 可旋转地支撑在所述壳体结构中的支撑轴; 至少一个盘悬挂在所述支撑轴上并且联接到所述支撑轴以与所述支撑轴一起旋转; 和冷却流体结构。 该至少一个盘由低合金含量的钢形成。 冷却流体供应结构延伸穿过支撑轴和至少一个盘，以将冷却流体供应到至少一个盘。
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公开(公告)号：US20110268579A1
公开(公告)日：2011-11-03
申请号：US12769928
申请日：2010-04-29
IPC分类号： F04D29/00
CPC分类号： F04D29/644 , F01D5/066 , F04D29/054 , F05D2260/311
摘要： A spindle bolt structure is provided in a gas turbine engine. The gas turbine engine includes a rotor including a plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk. The spindle bolt structure includes a plurality of spindle bolts extending through the turbine disks and disposed offset from a rotational axis of the turbine disks. The spindle bolts include a first terminal end located adjacent to the compressor side of the turbine disks, and a sleeve member is provided extending over a portion of the first terminal end of each spindle bolt and embedded within a compressor side of the seal disk for effecting a reduction in fretting movement of the spindle bolt relative to the seal disk.
摘要翻译： 在燃气涡轮发动机中设置有主轴螺栓结构。 燃气涡轮发动机包括：转子，其包括用于支撑叶片行的多个涡轮盘，位于涡轮盘的压缩机侧的扭矩管，以及位于扭矩管和第一级涡轮盘之间的密封盘。 主轴螺栓结构包括多个主轴螺栓，其延伸穿过涡轮盘并且设置成偏离涡轮盘的旋转轴线。 主轴螺栓包括位于涡轮盘的压缩机侧附近的第一终端，并且套筒构件设置成在每个主轴螺栓的第一终端的一部分上延伸并且嵌入在密封盘的压缩机侧中，以实现 减少主轴螺栓相对于密封盘的微动运动。
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公开(公告)号：US08465259B2
公开(公告)日：2013-06-18
申请号：US12769928
申请日：2010-04-29
IPC分类号： F04D29/18
CPC分类号： F04D29/644 , F01D5/066 , F04D29/054 , F05D2260/311
摘要： A spindle bolt structure is provided in a gas turbine engine. The gas turbine engine includes a rotor including a plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk. The spindle bolt structure includes a plurality of spindle bolts extending through the turbine disks and disposed offset from a rotational axis of the turbine disks. The spindle bolts include a first terminal end located adjacent to the compressor side of the turbine disks, and a sleeve member is provided extending over a portion of the first terminal end of each spindle bolt and embedded within a compressor side of the seal disk for effecting a reduction in fretting movement of the spindle bolt relative to the seal disk.
摘要翻译： 在燃气涡轮发动机中设置有主轴螺栓结构。 燃气涡轮发动机包括：转子，其包括用于支撑叶片行的多个涡轮盘，位于涡轮盘的压缩机侧的扭矩管，以及位于扭矩管和第一级涡轮盘之间的密封盘。 主轴螺栓结构包括多个主轴螺栓，其延伸穿过涡轮盘并且设置成偏离涡轮盘的旋转轴线。 主轴螺栓包括位于涡轮盘的压缩机侧附近的第一终端，并且套筒构件设置成在每个主轴螺栓的第一终端的一部分上延伸并且嵌入在密封盘的压缩机侧中，以实现 减少主轴螺栓相对于密封盘的微动运动。
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5.发明授权Combustion turbine including a diffuser section with cooling fluid passageways and associated methods 有权燃烧涡轮机包括具有冷却液通道的扩散段和相关方法公开(公告)号：US08257025B2
公开(公告)日：2012-09-04
申请号：US12106375
申请日：2008-04-21
IPC分类号： F01D9/06
CPC分类号： F01D25/14
摘要： A combustion turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. A diffuser section is downstream from the turbine section and has an outer wall, an inner wall, and at least one strut member extending therebetween. The outer wall has at least one first gas passageway therein, the inner wall has at least one second gas passageway therein, and the at least one strut member has at least one third gas passageway therein. The at least one first, second and third gas passageways deliver gas therethrough to assist attachment of a boundary layer to adjacent surfaces of the outer wall, the inner wall, and the at least one strut, respectively.
摘要翻译： 燃气轮机包括压缩机部分，压缩机部分下游的燃烧部分和燃烧部分下游的涡轮部分。 扩散器部分在涡轮机部分的下游，并且具有外壁，内壁和在它们之间延伸的至少一个支柱构件。 外壁在其中具有至少一个第一气体通道，内壁在其中具有至少一个第二气体通道，并且至少一个支柱构件在其中具有至少一个第三气体通道。 所述至少一个第一，第二和第三气体通道输送气体通过其中以帮助边界层分别附接到外壁，内壁和至少一个支柱的相邻表面。
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6.发明申请INNER RING WITH INDEPENDENT THERMAL EXPANSION FOR MOUNTING GAS TURBINE FLOW PATH COMPONENTS 有权具有独立热膨胀的内环，用于安装气体涡轮机流路组件公开(公告)号：US20100031671A1
公开(公告)日：2010-02-11
申请号：US11506096
申请日：2006-08-17
CPC分类号： F01D25/246 , F01D11/18 , F05D2230/60 , F05D2230/642 , F05D2300/50212 , Y10T29/4932 , Y10T29/49323
摘要： An inner mounting ring (20) for gas turbine flow path components such as shroud ring segments (24). The inner ring (20) may be mounted to an outer ring (22) on radially slidable mounts (26, 28) that maintain the two rings (20, 22) in coaxial relationship, but allows them to thermally expand at different rates. This allows matching of the radial expansion rate of the inner ring (20) to that of the turbine blade tips (32), thus providing reduced clearance (33) between the turbine blade tips (32) and the inner surface of the shroud ring segments (24) under all engine operating conditions. The inner ring (20) may be made of a material with a lower coefficient of thermal expansion than that of the outer ring (22).
摘要翻译： 用于燃气轮机流动路径部件（例如护罩环段）的内部安装环（20）。 内环（20）可以安装在径向可滑动的安装件（26,28）上的外环（22）上，其保持两个环（20,22）处于同轴的关系，但允许它们以不同的速率热膨胀。 这允许内环（20）的径向膨胀速率与涡轮叶片尖端（32）的径向膨胀速率匹配，从而在涡轮叶片尖端（32）和护罩环段的内表面之间提供减小的间隙（33） （24）在所有发动机运行条件下。 内圈（20）可以由比外圈（22）的热膨胀系数低的材料制成。
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公开(公告)号：US07165889B2
公开(公告)日：2007-01-23
申请号：US11044792
申请日：2005-01-27
IPC分类号： F16C17/02
CPC分类号： F16C32/0659 , F16C17/02 , F16C32/0685 , F16C39/04 , F16C2300/14 , F16C2360/00
摘要： An oil lift pocket for a bearing surface having a plurality of channels in communication with a supply port. The plurality of channels may be formed in a substantially bow shaped configuration. Each channel may extend from a supply port and terminate at an end and away from the supply port. The oil lift pocket greatly reduces friction in slow turning operations and reduces babbitt delamination, dead zones, and nonuniform support and lift as well.
摘要翻译： 一种用于支承表面的提油口，其具有与供给口连通的多个通道。 多个通道可以形成为大致弓形的构型。 每个通道可以从供应端口延伸并终止并且远离供应端口。 提油口袋大大降低了慢转动作业中的摩擦力，并减少了巴氏合金分层，死区和不均匀的支撑和提升。
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8.发明申请GAS TURBINE INCLUDING BELLY BAND SEAL ANTI-ROTATION DEVICE 有权气体涡轮机包括BELLY BAND SEAL ANTI-ROTTING DEVICE公开(公告)号：US20140119900A1
公开(公告)日：2014-05-01
申请号：US13665992
申请日：2012-11-01
IPC分类号： F01D11/08
CPC分类号： F01D5/06 , B23K20/129 , F01D5/066 , F01D5/084 , F01D11/005 , F02C7/28 , F05D2220/32 , F05D2230/60 , F05D2240/55
摘要： A sealing band located in opposing seal band receiving slots of adjacent turbine disks to seal an annular gap therebetween. An anti-rotation body including a base portion is located between edges of the sealing band within the annular gap, and a pin portion extends axially from the base portion for engagement with a cut-out portion of at least one of the disks. A pair of spaced projections extend from the base portion and into through openings in the sealing band at a location within the annular gap. The projections define an attachment structure attaching the anti-rotation body to the sealing band.
摘要翻译： 位于相邻密封带的密封带，其接收相邻涡轮盘的槽，以密封其间的环形间隙。 包括基部的防旋转体位于环形间隙内的密封带的边缘之间，并且销部从基部轴向延伸以与至少一个盘的切口部分接合。 一对间隔开的突出部从环形间隙内的位置从基部延伸到密封带中的通孔中。 突起限定了将防旋转体附接到密封带的附接结构。
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9.发明授权Inner ring with independent thermal expansion for mounting gas turbine flow path components 有权具有独立热膨胀的内环，用于安装燃气轮机流路部件公开(公告)号：US07686575B2
公开(公告)日：2010-03-30
申请号：US11506096
申请日：2006-08-17
IPC分类号： F01D25/26
CPC分类号： F01D25/246 , F01D11/18 , F05D2230/60 , F05D2230/642 , F05D2300/50212 , Y10T29/4932 , Y10T29/49323
摘要： An inner mounting ring (20) for gas turbine flow path components such as shroud ring segments (24). The inner ring (20) may be mounted to an outer ring (22) on radially slidable mounts (26, 28) that maintain the two rings (20, 22) in coaxial relationship, but allows them to thermally expand at different rates. This allows matching of the radial expansion rate of the inner ring (20) to that of the turbine blade tips (32), thus providing reduced clearance (33) between the turbine blade tips (32) and the inner surface of the shroud ring segments (24) under all engine operating conditions. The inner ring (20) may be made of a material with a lower coefficient of thermal expansion than that of the outer ring (22).
摘要翻译： 用于燃气轮机流动路径部件（例如护罩环段）的内部安装环（20）。 内环（20）可以安装在径向可滑动的安装件（26,28）上的外环（22）上，其保持两个环（20,22）处于同轴的关系，但允许它们以不同的速率热膨胀。 这允许内环（20）的径向膨胀速率与涡轮叶片尖端（32）的径向膨胀速率匹配，从而在涡轮叶片尖端（32）和护罩环段的内表面之间提供减小的间隙（33） （24）在所有发动机运行条件下。 内圈（20）可以由比外圈（22）的热膨胀系数低的材料制成。
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10.发明申请Combustion Turbine Including a Diffuser Section with Cooling Fluid Passageways and Associated Methods 有权燃烧涡轮包括具有冷却液通道的扩散器部分和相关方法公开(公告)号：US20090263243A1
公开(公告)日：2009-10-22
申请号：US12106375
申请日：2008-04-21
IPC分类号： F01D25/14
CPC分类号： F01D25/14
摘要： A combustion turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. A diffuser section is downstream from the turbine section and has an outer wall, an inner wall, and at least one strut member extending therebetween. The outer wall has at least one first gas passageway therein, the inner wall has at least one second gas passageway therein, and the at least one strut member has at least one third gas passageway therein. The at least one first, second and third gas passageways deliver gas therethrough to assist attachment of a boundary layer to adjacent surfaces of the outer wall, the inner wall, and the at least one strut, respectively.
摘要翻译： 燃气轮机包括压缩机部分，压缩机部分下游的燃烧部分和燃烧部分下游的涡轮部分。 扩散器部分在涡轮机部分的下游，并且具有外壁，内壁和在它们之间延伸的至少一个支柱构件。 外壁在其中具有至少一个第一气体通道，内壁在其中具有至少一个第二气体通道，并且至少一个支柱构件在其中具有至少一个第三气体通道。 所述至少一个第一，第二和第三气体通道输送气体通过其中以帮助边界层分别附接到外壁，内壁和至少一个支柱的相邻表面。
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