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1.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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2.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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公开(公告)号：US09109608B2
公开(公告)日：2015-08-18
申请号：US13326399
申请日：2011-12-15
申请人： David A. Little , Zhengxiang Pu
发明人： David A. Little , Zhengxiang Pu
IPC分类号： F04D29/16 , F04D29/052 , F01D11/22
CPC分类号： F04D29/164 , F01D11/22 , F04D19/028 , F04D29/052 , F04D29/522
摘要： A compressor airfoil tip clearance optimization system for reducing a gap between a tip of a compressor airfoil and a radially adjacent component of a turbine engine is disclosed. The turbine engine may include ID and OD flowpath boundaries configured to minimize compressor airfoil tip clearances during turbine engine operation in cooperation with one or more clearance reduction systems that are configured to move the rotor assembly axially to reduce tip clearance. The configurations of the ID and OD flowpath boundaries enhance the effectiveness of the axial movement of the rotor assembly, which includes movement of the ID flowpath boundary. During operation of the turbine engine, the rotor assembly may be moved axially to increase the efficiency of the turbine engine.
摘要翻译： 公开了一种用于减小压缩机叶片的尖端与涡轮发动机的径向相邻部件之间的间隙的压缩机翼型顶端间隙优化系统。 涡轮发动机可以包括ID和OD流动路径边界，其被配置为在涡轮发动机运行期间最小化压缩机翼型顶端间隙，与一个或多个间隙减小系统配合，其被配置成轴向地移动转子组件以减小顶端间隙。 ID和OD流路边界的结构增强了转子组件的轴向运动的有效性，其包括ID流路边界的移动。 在涡轮发动机的操作期间，转子组件可以轴向移动以提高涡轮发动机的效率。
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公开(公告)号：US20130156578A1
公开(公告)日：2013-06-20
申请号：US13326399
申请日：2011-12-15
申请人： David A. Little , Zhengxiang Pu
发明人： David A. Little , Zhengxiang Pu
IPC分类号： F04D29/18
CPC分类号： F04D29/164 , F01D11/22 , F04D19/028 , F04D29/052 , F04D29/522
摘要： A compressor airfoil tip clearance optimization system for reducing a gap between a tip of a compressor airfoil and a radially adjacent component of a turbine engine is disclosed. The turbine engine may include ID and OD flowpath boundaries configured to minimize compressor airfoil tip clearances during turbine engine operation in cooperation with one or more clearance reduction systems that are configured to move the rotor assembly axially to reduce tip clearance. The configurations of the ID and OD flowpath boundaries enhance the effectiveness of the axial movement of the rotor assembly, which includes movement of the ID flowpath boundary. During operation of the turbine engine, the rotor assembly may be moved axially to increase the efficiency of the turbine engine.
摘要翻译： 公开了一种用于减小压缩机叶片的尖端与涡轮发动机的径向相邻部件之间的间隙的压缩机翼型顶端间隙优化系统。 涡轮发动机可以包括ID和OD流动路径边界，其被配置为在涡轮发动机运行期间最小化压缩机翼型顶端间隙，与一个或多个间隙减小系统配合，其被配置成轴向地移动转子组件以减小顶端间隙。 ID和OD流路边界的结构增强了转子组件的轴向运动的有效性，其包括ID流路边界的移动。 在涡轮发动机的操作期间，转子组件可以轴向移动以提高涡轮发动机的效率。
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5.发明申请Angled honeycomb seal between turbine rotors and turbine stators in a turbine engine 审中-公开涡轮发动机涡轮转子和涡轮定子之间的角度的蜂窝密封公开(公告)号：US20090014964A1
公开(公告)日：2009-01-15
申请号：US11825692
申请日：2007-07-09
申请人： Zhengxiang Pu , Yan Yin
发明人： Zhengxiang Pu , Yan Yin
IPC分类号： F01D11/08 , F04D29/08 , F16J15/447
CPC分类号： F16J15/444 , F01D11/001 , F01D11/04 , F01D11/08 , F01D11/122 , F01D11/127 , F01D11/22
摘要： A seal system for an intersection between a turbine stator and a turbine rotor to seal cooling fluids. The seal system may be formed from a seal base extending from the turbine stator, an arm extending radially outward from the turbine rotor and toward the seal base but terminating short of the seal base thereby creating a gap between the seal base and the arm. The seal system may include a honeycomb shaped seal attached to the seal base and extending radially inward from the seal base toward the arm. An outer sealing surface of the seal may be nonparallel with a longitudinal axis about which the turbine rotor rotates thereby enabling the distance of the gap to be reduced with axial movement of the turbine rotor.
摘要翻译： 一种用于涡轮机定子和涡轮转子之间的相交的密封系统，以密封冷却流体。 密封系统可以由从涡轮机定子延伸的密封基座，从涡轮机转子径向向外延伸并且朝向密封基座延伸的臂形成，但是密封基座的端部不足以在密封基部和臂之间形成间隙。 密封系统可以包括附接到密封基部并从密封基部朝向臂径向向内延伸的蜂窝状密封件。 密封件的外密封表面可以与纵向轴线不平行，涡轮机转子围绕该轴线旋转，从而能够通过涡轮机转子的轴向运动来减小间隙的距离。
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