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1.发明授权Axial flow compressor, gas turbine system having the axial flow compressor and method of modifying the axial flow compressor 有权轴流压缩机，具有轴流压缩机的燃气轮机系统和轴流式压缩机的改进方法公开(公告)号：US09109461B2
公开(公告)日：2015-08-18
申请号：US13197947
申请日：2011-08-04
申请人： Yasuo Takahashi , Chihiro Myoren , Ryou Akiyama , Ichiro Miyoshi
发明人： Yasuo Takahashi , Chihiro Myoren , Ryou Akiyama , Ichiro Miyoshi
CPC分类号： F01D25/00 , F01D5/142 , F04D29/544 , F05D2230/50 , F05D2240/10
摘要： There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.
摘要翻译： 提供了一种轴流式压缩机，其由于燃气轮机的部分负载操作而提高了轴流式压缩机的最后一级定子叶片上的叶片负载的增加的可靠性。 环形流路由安装有多个转子叶片的转子和安装有多个定子叶片的壳体形成，其中两个或更多个定子叶片设置在最后一个转子叶片的下游，转子叶片是设置在转子叶片 在环形流路的流动方向上的最下游侧，设置在最上游侧的第一定子叶片上的叶片负荷设定为小于设置在第一定子叶片下游的第二定子叶片的叶片负载量 行。
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2.发明申请Axial Flow Compressor, Gas Turbine System Having the Axial Flow Compressor and Method of Modifying the Axial Flow Compressor 有权轴流式压缩机，具有轴流式压缩机的燃气轮机系统及轴流压缩机修改方法公开(公告)号：US20120070267A1
公开(公告)日：2012-03-22
申请号：US13197947
申请日：2011-08-04
申请人： Yasuo TAKAHASHI , Chihiro Myoren , Ryou Akiyama , Ichiro Miyoshi
发明人： Yasuo TAKAHASHI , Chihiro Myoren , Ryou Akiyama , Ichiro Miyoshi
CPC分类号： F01D25/00 , F01D5/142 , F04D29/544 , F05D2230/50 , F05D2240/10
摘要： There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed. at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.
摘要翻译： 提供了一种轴流式压缩机，其由于燃气轮机的部分负载操作而提高了轴流式压缩机的最后一级定子叶片上的叶片负载的增加的可靠性。 由安装有多个转子叶片的转子和安装有多个定子叶片的壳体形成环形流动通道，其中两个或更多个定子叶片设置在设置转子叶片的最后一个转子叶片的下游。 在环形流路的流动方向的最下游侧，设置在最上游侧的第一定子叶片上的叶片的载荷被设定为小于设置在第一定子叶片下游的第二定子叶片的叶片负荷 一行
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3.发明申请Inner Bleed Structure of 2-Shaft Gas Turbine and a Method to Determine the Stagger Angle of Last Stage Stator of Compressor for 2-Shaft Gas Turbine 审中-公开2轴燃气轮机内部排气结构及确定2轴燃气轮机压缩机末级定子交错角的方法公开(公告)号：US20120060509A1
公开(公告)日：2012-03-15
申请号：US13198751
申请日：2011-08-05
CPC分类号： F04D29/321 , F01D5/085
摘要： An inner bleed structure of the 2-shaft gas turbine includes a slit for leading part of compressed air to a cavity is formed between a wall surface of a rotor wheel of the compressor equipped with a last stage rotor of the compressor which is connected to a first rotating shaft and end of an inner casing, and a bleed hole for leading part of compressed air after flowing down the last stage of the compressor to a cavity formed in the inner side of the inner casing at the downstream side of the last stage of the compressor.
摘要翻译： 2轴燃气轮机的内排气结构包括用于将压缩空气的一部分引导到空腔的狭缝形成在配备有压缩机的最后级转子的压缩机的转子轮的壁表面之间，压缩机的最后级转子连接到 第一旋转轴和内壳的端部，以及用于在压缩机的最后阶段向下流动的压缩空气的前端部分之后的下游侧的形成在内壳的内侧的空腔的排气孔 压缩机。
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公开(公告)号：US20120163965A1
公开(公告)日：2012-06-28
申请号：US13336644
申请日：2011-12-23
申请人： Yasuo TAKAHASHI , Chihiro Myoren , Ryou Akiyama
发明人： Yasuo TAKAHASHI , Chihiro Myoren , Ryou Akiyama
CPC分类号： F04D29/544 , Y10T29/49238 , Y10T29/49245
摘要： When a gas turbine is operated with inlet guide vanes (IGVs) closed during part load operation or the like, the degradation of aerodynamic performance and of reliability may potentially occur since the load on rear stage side vanes of a compressor increases. An object of the present invention is to suppress the degradation of the aerodynamic performance and of reliability of an axial compressor.The axial compressor includes a rotor; a plurality of rotor blade rows installed on the rotor; a casing located outside of the rotor blade rows; a plurality of stator vane rows installed on the casing; and exit guide vanes installed on the downstream side of a final stage stator vane row among the stator vane rows. An incidence angle of a flow toward the final stage stator vane row is equal to or below a limit line of an incidence operating range.
摘要翻译： 当在部分加载操作等期间在入口导向叶片（IGV）关闭的情况下操作燃气轮机时，由于压缩机的后级侧叶片上的负载增加，潜在的空气动力性能和可靠性的降低可能会发生。 本发明的目的是抑制轴向压缩机的空气动力性能的劣化和可靠性的降低。 轴向压缩机包括转子; 安装在转子上的多个转子叶片排; 壳体，位于转子叶片排的外侧; 安装在所述壳体上的多个定子叶片排; 以及安装在定子叶片排中的末级定子叶片排的下游侧的出口导向叶片。 朝向末级定子叶片排的流的入射角等于或低于入射操作范围的极限线。
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公开(公告)号：US20100293963A1
公开(公告)日：2010-11-25
申请号：US12780002
申请日：2010-05-14
申请人： Chihiro Myoren , Ryou Akiyama
发明人： Chihiro Myoren , Ryou Akiyama
CPC分类号： F02C3/10 , F01D5/142 , F05D2220/321
摘要： On a two-shaft gas turbine, on at least one of an inner peripheral side or an outer peripheral side of a main flow passage, an outlet of a high-pressure turbine is lower than an inlet of a low-pressure turbine, an outer periphery of a flow channel that connects the outlet of the high-pressure turbine and the inlet of the low-pressure turbine includes a first casing shroud that is supported by a casing and located on an outer peripheral side of a final-stage rotor vane of the high-pressure turbine, and an initial-stage stator vane of the low-pressure turbine, and a connection position of the first casing shroud and the initial-stage stator vane of the low-pressure turbine is closer to the inlet of the initial-stage stator vane of the low-pressure turbine than the outlet of the final-stage rotor vane of the high-pressure turbine.
摘要翻译： 在双轴燃气轮机上，在主流路的内周侧或外周侧的至少一方，高压涡轮机的出口低于低压涡轮机的入口，外侧 连接高压涡轮机的出口和低压涡轮机的入口的流路的周边包括第一壳体护罩，其由壳体支撑并位于最终级转子叶片的外周侧 高压涡轮机和低压涡轮机的初级定子叶片，并且低压涡轮机的第一壳体护罩和初级定子叶片的连接位置更接近初始状态的入口 低压涡轮机的台阶定子叶片比高压涡轮机的末级转子叶片的出口。
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公开(公告)号：US09127569B2
公开(公告)日：2015-09-08
申请号：US13197818
申请日：2011-08-04
CPC分类号： F01D25/246 , F01D11/24 , F01D25/14 , F05D2240/11
摘要： There is provided a shroud structure for gas turbines capable of suppressing a drop in the amount of cooling air for cooling the inner shroud by reducing the amount of cooling air leakage that occurs along the cooling air path when feeding cooling air from the one-piece outer shroud to the inner shroud of the gas turbine and ensure more reliable cooling of the inner shroud. The gas turbine shroud structure contains a one-piece outer shroud, and an inner shroud retained on the inner circumferential side of the outer shroud in a structure divided into multiple inner shrouds along the periphery. An inner seal plate groove is formed on the outer circumference of the hook formed on the inner shroud, a seal plate is inserted in the inner seal plate groove, and the seal plate is mounted so that a section of the seal plate protrudes in the gap between the hook mechanism of the outer shroud and the inner shroud.
摘要翻译： 提供了一种用于燃气轮机的护罩结构，其能够通过减少沿着冷却空气路径发生的冷却空气泄漏量来抑制冷却空气的量的下降，当从一体式外部 护罩到燃气轮机的内护罩，并确保内护罩更可靠的冷却。 燃气轮机罩结构包括一体式外护罩，以及保持在外护罩的内周侧上的内罩，其沿着周边分成多个内护罩的结构。 在形成在内护罩上的钩的外周上形成内密封板槽，在内密封板槽中插入密封板，并且密封板安装成使得密封板的一部分在间隙中突出 在外护罩的钩机构和内护罩之间。
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7.发明授权Gas turbine, gas turbine apparatus, and refrigerant collection method for gas turbine moving blades 有权燃气轮机，燃气轮机装置和燃气轮机动叶片的制冷剂收集方法公开(公告)号：US06568192B2
公开(公告)日：2003-05-27
申请号：US10138429
申请日：2002-05-06
IPC分类号： F02C716
CPC分类号： F02C7/12 , F01D5/081 , F01D5/187 , F05D2260/205
摘要： A turbine rotor includes a plurality of moving blades having cooling paths through which a refrigerant flows inside, a plurality of wheels having the moving blades mounted in the outer periphery thereof and at least one spacer member installed between the wheels. The spacer member has a plurality of flow paths through which a refrigerant flows after cooling the moving blades. The plurality of flow paths have flow paths interconnecting to the cooling paths in the moving blades on a first wheel adjacent the spacer member and interconnecting to a space formed on a side wall surface with which a second wheel adjacent the spacer member and the spacer member are in contact.
摘要翻译： 涡轮转子包括具有制冷剂流过其中的冷却通道的多个活动叶片，具有安装在其外周中的移动叶片的多个车轮和安装在车轮之间的至少一个间隔件。 间隔件具有多个流动路径，制冷剂在冷却动叶片之后流过该流路。 所述多个流路具有与所述间隔件相邻的第一轮上的所述活动叶片中的冷却路径相互连接的流路，并且与形成在侧壁表面上的空间相互连接，与所述间隔件相邻的第二轮 接触。
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8.发明授权Gas turbine, gas turbine apparatus, and refrigerant collection method for gas turbine moving blades 有权燃气轮机，燃气轮机装置和燃气轮机动叶片的制冷剂收集方法公开(公告)号：US06405538B1
公开(公告)日：2002-06-18
申请号：US09644770
申请日：2000-08-24
IPC分类号： F02C716
CPC分类号： F02C7/12 , F01D5/081 , F01D5/187 , F05D2260/205
摘要： A gas turbine having a structure for collecting a refrigerant after cooling the moving blades, has a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members alternately arranged on the rotating axis. A plurality of flow paths through which a refrigerant flows after cooling the moving blades are provided in the spacer members. First flow paths interconnect the moving blades arranged on the wheels on the upstream side of gas flow to the downstream side of gas flow of the spacer members, and second flow paths interconnect the moving blades arranged on the wheels on the downstream side of gas flow to the upstream side of gas flow of the spacer members. The flow paths may be provided with bent parts in the neighborhood of the center of the space members in the axial direction or may be in a linear shape.
摘要翻译： 具有用于在冷却动叶片之后收集制冷剂的结构的燃气轮机具有多个车轮，所述多个车轮具有包括外周部的冷却路径的多个动叶片和交替配置在旋转轴上的多个间隔件。 在间隔件中设置有多个冷却流动叶片后制冷剂流过的流路。 第一流动路径将布置在气流上游侧的轮上的动叶片与间隔件的气流的下游侧相互连接，第二流路将布置在气流下游侧的轮上的动叶相互连接 间隔件的气流的上游侧。 流动路径可以在轴向方向上在空间构件的中心附近设置弯曲部分，或者可以是直线形状。
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公开(公告)号：US07320175B2
公开(公告)日：2008-01-22
申请号：US10765866
申请日：2004-01-29
申请人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
发明人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
CPC分类号： F02C3/13 , F02C3/04 , F05D2230/61 , F05D2240/40 , Y02E20/14 , Y02E20/16 , Y02T50/67 , Y10T29/49316 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49716
摘要： The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.
摘要翻译： 本发明提供一种可应用于各种循环的燃气轮机的生产方法。 燃气轮机的主要部分是基于大致设定的条件而预先设定的，并且可以基于该组设定压缩机的级数和可以提供适合于期望循环的条件的涡轮机的级数 主体。 每个具有设定级数并且包括在主要部分中的压缩机和涡轮机彼此组合以构造燃气轮机。 当压缩机或涡轮机的设定级数在多个期望循环中不同时，具有形成压缩机或涡轮机的大致环形流动通道的内周壁的外周的大致圆盘形构件， 被组装到具有较少数量级的循环中，使得在多个期望循环中操作的燃气轮机中的轴承 - 承载距离保持恒定。
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公开(公告)号：US20050076502A1
公开(公告)日：2005-04-14
申请号：US10765866
申请日：2004-01-29
申请人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
发明人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
CPC分类号： F02C3/13 , F02C3/04 , F05D2230/61 , F05D2240/40 , Y02E20/14 , Y02E20/16 , Y02T50/67 , Y10T29/49316 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49716
摘要： The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.
摘要翻译： 本发明提供一种可应用于各种循环的燃气轮机的生产方法。 燃气轮机的主要部分是基于大致设定的条件而预先设定的，并且可以基于该组设定压缩机的级数和可以提供适合于期望循环的条件的涡轮机的级数 主体。 每个具有设定级数并且包括在主要部分中的压缩机和涡轮机彼此组合以构造燃气轮机。 当压缩机或涡轮机的设定级数在多个期望循环中不同时，具有形成压缩机或涡轮机的大致环形的流路的内周壁的外周的大致圆盘状构件， 被组装到具有较少数量级的循环中，使得在多个期望循环中操作的燃气轮机中的轴承 - 承载距离保持恒定。
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