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公开(公告)号：US20110142597A1
公开(公告)日：2011-06-16
申请号：US12596224
申请日：2009-04-23
申请人： Keizo Tsukagoshi , Tomoko Hashimoto , Satoshi Hada
发明人： Keizo Tsukagoshi , Tomoko Hashimoto , Satoshi Hada
IPC分类号： F01D9/02
CPC分类号： F01D5/16 , F01D5/188 , F05D2260/94 , F05D2260/941
摘要： Provided is a turbine blade structure that is capable of suppressing quality variations of cast products during the manufacturing of turbine blades. A turbine blade structure wherein the space inside an air foil is divided into a plurality of cavities, partitioned by rib members provided substantially perpendicular to the center line connecting a leading edge and a trailing edge, is provided with partition members that partition the inside of the cavities located in the central portion of the blade, excluding the blade leading-edge side and the blade trailing-edge side, into blade pressure side cavities and blade suction side cavities substantially along the center line, wherein blade leading-edge end portions and blade trailing-edge end portions of the partition members are inserted from one shroud surface side to the other shroud surface side along engagement grooves formed on the rib members.
摘要翻译： 提供一种涡轮叶片结构，其能够抑制在涡轮叶片的制造期间铸造产品的质量变化。 一种涡轮叶片结构，其中，空气箔内的空间被分成多个空腔，所述多个空腔由基本上垂直于连接前缘和后缘的中心线设置的肋构件分隔开，分隔构件分隔 位于叶片的中心部分的除了叶片前缘侧和叶片后缘侧之外的空腔基本上沿着中心线分成叶片压力侧空腔和叶片吸入侧空腔，其中叶片前缘端部和叶片 分隔构件的后缘端部沿着形成在肋构件上的接合槽从一个护罩表面侧插入另一个护罩表面侧。
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公开(公告)号：US20100150734A1
公开(公告)日：2010-06-17
申请号：US12633842
申请日：2009-12-09
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/189 , F05D2240/126 , F05D2240/306 , F05D2260/201 , F05D2260/202
摘要： In a turbine blade in which a tabular rib partitioning the blade into a pressure side and a suction side is provided in substantially the midsection of the blade along a center line connecting a leading edge and a trailing edge, and at least two cavities of which a cavity at the suction side and a cavity at the pressure side do not communicate with each other are provided, a pressure adjustment member for cooling air flowing into and out of the cavity at the suction side reduces the amount of cooling air flowing into the suction side, relative to the pressure side.
摘要翻译： 在涡轮机叶片中，其中沿着连接前缘和后缘的中心线将叶片分隔成压力侧和吸力侧的片状肋在叶片的大致中央部分中设置，并且其中至少两个空腔 设置吸入侧的空腔和压力侧的空腔不相通，用于冷却在吸入侧流入和流出空气的空气的压力调节构件减少流入吸入侧的冷却空气量 ，相对于压力侧。
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公开(公告)号：US08366391B2
公开(公告)日：2013-02-05
申请号：US12596224
申请日：2009-04-23
申请人： Keizo Tsukagoshi , Tomoko Hashimoto , Satoshi Hada
发明人： Keizo Tsukagoshi , Tomoko Hashimoto , Satoshi Hada
IPC分类号： F01D5/12
CPC分类号： F01D5/16 , F01D5/188 , F05D2260/94 , F05D2260/941
摘要： Provided is a turbine blade structure that is capable of suppressing quality variations of cast products during the manufacturing of turbine blades. A turbine blade structure wherein the space inside an air foil is divided into a plurality of cavities, partitioned by rib members provided substantially perpendicular to the center line connecting a leading edge and a trailing edge, is provided with partition members that partition the inside of the cavities located in the central portion of the blade, excluding the blade leading-edge side and the blade trailing-edge side, into blade pressure side cavities and blade suction side cavities substantially along the center line, wherein blade leading-edge end portions and blade trailing-edge end portions of the partition members are inserted from one shroud surface side to the other shroud surface side along engagement grooves formed on the rib members.
摘要翻译： 提供一种涡轮叶片结构，其能够抑制在涡轮叶片的制造期间铸造产品的质量变化。 一种涡轮叶片结构，其中，空气箔内的空间被分成多个空腔，所述多个空腔由基本上垂直于连接前缘和后缘的中心线设置的肋构件分隔开，分隔构件分隔 位于叶片的中心部分的除了叶片前缘侧和叶片后缘侧之外的空腔基本上沿着中心线分成叶片压力侧空腔和叶片吸入侧空腔，其中叶片前缘端部和叶片 分隔构件的后缘端部沿着形成在肋构件上的接合槽从一个护罩表面侧插入另一个护罩表面侧。
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公开(公告)号：US08079815B2
公开(公告)日：2011-12-20
申请号：US12633842
申请日：2009-12-09
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/189 , F05D2240/126 , F05D2240/306 , F05D2260/201 , F05D2260/202
摘要： In a turbine blade in which a tabular rib partitioning the blade into a pressure side and a suction side is provided in substantially the midsection of the blade along a center line connecting a leading edge and a trailing edge, and at least two cavities of which a cavity at the suction side and a cavity at the pressure side do not communicate with each other are provided, a pressure adjustment member for cooling air flowing into and out of the cavity at the suction side reduces the amount of cooling air flowing into the suction side, relative to the pressure side.
摘要翻译： 在涡轮机叶片中，其中沿着连接前缘和后缘的中心线将叶片分隔成压力侧和吸力侧的片状肋在叶片的大致中央部分中设置，并且其中至少两个空腔 设置吸入侧的空腔和压力侧的空腔不相通，用于冷却在吸入侧流入和流出空气的空气的压力调节构件减少流入吸入侧的冷却空气量 ，相对于压力侧。
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公开(公告)号：US20110103971A1
公开(公告)日：2011-05-05
申请号：US12999371
申请日：2008-11-07
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2260/201 , F05D2260/202
摘要： The amount of cooling air (cooling medium) can be reduced, and low-temperature cooling air is prevented from being blown out through film cooling holes. Part of a cooling medium impingement-cooling an inner circumferential surface of a blade main body located on a ventral side further impingement-cools the inner circumferential surface of the blade main body located on a dorsal side and is blown out through film cooling holes in the blade main body that are located on the dorsal side.
摘要翻译： 可以减少冷却空气（冷却介质）的量，并且防止低温冷却空气通过膜冷却孔吹出。 冷却介质的一部分冲击 - 冷却位于腹侧的刀片主体的内周面，进一步冲击 - 冷却位于背侧的刀片主体的内周面，并通过膜侧冷却孔 刀片主体位于背侧。
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公开(公告)号：US08596976B2
公开(公告)日：2013-12-03
申请号：US12999371
申请日：2008-11-07
IPC分类号： F01D5/08
CPC分类号： F01D5/189 , F05D2260/201 , F05D2260/202
摘要： The amount of cooling air (cooling medium) can be reduced, and low-temperature cooling air is prevented from being blown out through film cooling holes. Part of a cooling medium impingement-cooling an inner circumferential surface of a blade main body located on a ventral side further impingement-cools the inner circumferential surface of the blade main body located on a dorsal side and is blown out through film cooling holes in the blade main body that are located on the dorsal side.
摘要翻译： 可以减少冷却空气（冷却介质）的量，并且防止低温冷却空气通过膜冷却孔吹出。 冷却介质的一部分冲击 - 冷却位于腹侧的刀片主体的内周面，进一步冲击 - 冷却位于背侧的刀片主体的内周面，并通过膜侧冷却孔 刀片主体位于背侧。
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