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1. 发明授权

US07028486B2 Coolant recovery type gas turbine 失效
公开(公告)号：US07028486B2
公开(公告)日：2006-04-18
申请号：US10782961
申请日：2004-02-23
申请人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
发明人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
IPC分类号： F02G7/12
CPC分类号： F02C7/18 , F01D25/12 , F05D2260/205 , F05D2260/2322
摘要： An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

2. 发明授权

US06393829B2 Coolant recovery type gas turbine 有权
标题翻译：冷却液回收式燃气轮机
公开(公告)号：US06393829B2
公开(公告)日：2002-05-28
申请号：US09308981
申请日：1999-05-28
申请人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
发明人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
IPC分类号： F02C300
CPC分类号： F02C7/18 , F01D25/12 , F05D2260/205 , F05D2260/2322
摘要： A gas turbine has a rotor shaft which includes a plurality of discs, each having a plurality of moving blades driven by combustion gas and arranged annularly on the peripheral portion and having spaces arranged between the discs. The respective discs and spacers are arranged in the axial direction. Gap portions are formed between the rotor axis side regions of the discs facing the spacers and adjacent spacers. Contact surfaces contacting each other on both rotor peripheral side regions of the discs facing the spaces and adjacent spacers are formed. A first flow path for supplying a coolant into the moving blades and a second flow path for recovering the coolant heated by the moving blades from the moving blade are provided. A third flow path for introducing fluid into the gap portions is formed in the discs with the third flow path being independent from the first and second flow paths.
摘要翻译：燃气轮机具有转子轴，该转子轴包括多个盘，每个盘具有由燃烧气体驱动的多个活动叶片，环形地布置在周边部分上，并且在盘之间具有间隔。相应的盘和间隔件沿轴向布置。间隙部分形成在面向间隔物和相邻间隔物的盘的转子轴线侧区域之间。形成面对空间和相邻间隔物的圆盘的两个转子周边区域彼此接触的接触表面。提供了用于将冷却剂供应到动叶片中的第一流动路径和用于从动叶片回收由移动叶片加热的冷却剂的第二流路。用于将流体引入间隙部分的第三流动路径形成在盘中，其中第三流动路径独立于第一和第二流动路径。

3. 发明授权

US06735957B2 Coolant recovery type gas turbine 失效
标题翻译：冷却液回收式燃气轮机
公开(公告)号：US06735957B2
公开(公告)日：2004-05-18
申请号：US10403124
申请日：2003-04-01
申请人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
发明人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
IPC分类号： F02G712
CPC分类号： F02C7/18 , F01D25/12 , F05D2260/205 , F05D2260/2322
摘要： An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
摘要翻译：目的是通过抑制作用在燃气轮机的转子上的热应力和热变形来提高燃气轮机的操作可靠性。燃气轮机具有转子轴，转子轴沿轴向方向依次布置有多个盘，每个盘具有环形地设置在周边部分上的多个燃烧气体驱动的移动叶片和布置在盘之间的间隔件，其特征在于在转子轴中心部分侧的面对间隔件的盘和相邻的间隔件之间形成间隙部分，形成两个接触表面，这两个接触表面在转子周边侧的两个区域上接触，上述圆盘面对间隔件和相邻的间隔件，并且提供了将流体引导到上述间隙部分的第三流动路径。

4. 发明授权

US06370866B1 Coolant recovery type gas turbine 有权
公开(公告)号：US06370866B1
公开(公告)日：2002-04-16
申请号：US09754383
申请日：2001-01-05
申请人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
发明人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
IPC分类号： F02C300
摘要： Operational reliability of a gas turbine is improved by suppressing the thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs. Gap portions are formed between a region on the rotor shaft center portion side of the discs facing the spacers and spacers adjacent thereof. Contact surfaces are formed which contact on both a region on the rotor peripheral side of the discs facing the spacers and adjacent spacers thereto. Furthermore, a third flow path leading fluid to the above-mentioned gap portions is provided.

5. 发明授权

US07028487B2 Coolant recovery type gas turbine 失效
公开(公告)号：US07028487B2
公开(公告)日：2006-04-18
申请号：US10782966
申请日：2004-02-23
申请人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
发明人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
IPC分类号： F02G7/12
CPC分类号： F02C7/18 , F01D25/12 , F05D2260/205 , F05D2260/2322
摘要： An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

6. 发明授权

US06568191B2 Coolant recovery type gas turbine 失效
公开(公告)号：US06568191B2
公开(公告)日：2003-05-27
申请号：US10082062
申请日：2002-02-26
申请人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
发明人： Shinya Marushima , Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Takashi Machida , Masaru Sekihara
IPC分类号： F02C712
CPC分类号： F02C7/18 , F01D25/12 , F05D2260/205 , F05D2260/2322
摘要： An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

7. 发明授权

US5695319A Gas turbine 失效
标题翻译：燃气轮机
公开(公告)号：US5695319A
公开(公告)日：1997-12-09
申请号：US627397
申请日：1996-04-04
申请人： Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Shunichi Anzai , Masami Noda , Nobuaki Kizuka , Shin'ichi Higuchi , Shinya Marushima , Masaru Sekihara
发明人： Manabu Matsumoto , Kazuhiko Kawaike , Takashi Ikeguchi , Shunichi Anzai , Masami Noda , Nobuaki Kizuka , Shin'ichi Higuchi , Shinya Marushima , Masaru Sekihara
IPC分类号： F01D5/08 , F04D29/58
CPC分类号： F01D5/085 , F05D2260/2322
摘要： A vapor cooled gas turbine has a cooling system including a vapor supply port and a vapor recovery port, and the cooling system is formed so that vapor from the supply port is supplied to blades through a central supply passage in a rotor and the vapor having cooled the blades is recovered from the recovery port through a recovery passage spaced outwardly from the supply passage.
摘要翻译：蒸汽冷却燃气轮机具有包括蒸气供给口和蒸汽回收口的冷却系统，并且形成冷却系统，使得来自供应口的蒸气通过转子中的中央供应通道供应到叶片，并且蒸汽已冷却叶片通过从供应通道向外间隔开的回收通道从回收口回收。

8. 发明授权

US5860789A Gas turbine rotor 失效
标题翻译：燃气轮机转子
公开(公告)号：US5860789A
公开(公告)日：1999-01-19
申请号：US791510
申请日：1997-01-30
申请人： Masaru Sekihara , Takashi Machida
发明人： Masaru Sekihara , Takashi Machida
IPC分类号： F01D5/06
CPC分类号： F01D5/066
摘要： A gas turbine has a gas turbine rotor including a plurality of rotary disks each having an opening of a circular shape formed through its central portion, the rotary disk including a pair of hub portions formed respectively on opposite sides thereof, and a pair of in-low portions formed respectively at the opposite sides thereof. The gas turbine rotor also includes a plurality of spacers each having an opening of a circular shape formed through its central portion, the spacer having a pair of in-low portions formed respectively at opposite sides thereof. The rotary disks and the spacers are alternately stacked together in such a manner that the opposite sides of each of the spacers contact opposed side surfaces of the adjacent hub portions, respectively, and that the in-low portions of each of the spacers are engaged respectively with the in-low portions of the adjacent rotary disks. The stack of rotary disks and spacers are fastened together in an axial direction by stacking bolts. A thickness of that portion of the rotary disk extending radially from an inner periphery of the hub portions to an inner peripheral surface of the rotary disk is so determined that stresses, developing at the inner peripheral surface of the rotary disk, can be made generally equal to one another over an entire area thereof.
摘要翻译：燃气轮机具有燃气轮机转子，该燃气轮机转子包括多个旋转盘，每个旋转盘具有通过其中心部分形成的圆形开口，该旋转盘包括分别形成在其相对侧上的一对毂部，分别形成在其相对侧的低部分。燃气轮机转子还包括多个间隔件，每个间隔件具有通过其中心部分形成的圆形开口，间隔件分别形成在其相对侧的一对低低部分。旋转盘和间隔件以这样的方式交替地堆叠在一起，使得每个间隔件的相对侧分别接触相邻轮毂部分的相对侧表面，并且每个间隔件的低低部分分别接合与相邻旋转盘的低部分。通过堆叠螺栓将旋转盘和间隔物的堆叠沿轴向紧固在一起。旋转盘的从轮毂部的内周向旋转盘的内周面径向延伸的部分的厚度被确定为能够使在旋转盘的内周面显影的应力大致相等在其整个区域上彼此相交。

9. 发明授权

US06546627B1 Repair method for a gas turbine 有权
标题翻译：燃气轮机的修理方法
公开(公告)号：US06546627B1
公开(公告)日：2003-04-15
申请号：US09824641
申请日：2001-04-04
申请人： Masaru Sekihara , Shigeo Sakurai
发明人： Masaru Sekihara , Shigeo Sakurai
IPC分类号： B23P600
CPC分类号： B23P6/005 , F01D9/023 , F05D2250/231 , F23R3/00 , F23R3/06 , Y10T29/49318 , Y10T29/49323 , Y10T29/4973
摘要： A gas turbine has a compressor for compressing air as a working fluid, a combustor for producing combustion gas by mixing fuel with the compressed air, and a turbine for generating a rotating force at the time of expansion of combustion gas. The gas turbine further includes a cylindrical liner; a transition piece for transferring the working fluid from the liner to the turbine; an outlet portion of the transition piece, which has a region parallel with a direction of a rotating shaft of the turbine; cooling holes formed in the region so that longitudinal intervals thereof are lengthened; and a picture frame portion provided to secure stiffness at an outlet of the outlet portion.
摘要翻译：燃气轮机具有用于压缩空气作为工作流体的压缩机，用于通过将燃料与压缩空气混合来产生燃烧气体的燃烧器，以及用于在燃烧气体膨胀时产生旋转力的涡轮机。燃气轮机还包括圆柱形衬套; 用于将工作流体从衬套转移到涡轮机的过渡件; 所述过渡件的出口部分具有与所述涡轮机的旋转轴的方向平行的区域; 在该区域中形成的冷却孔使得其纵向间隔被延长; 以及设置用于确保出口部分的出口处的刚度的相框部分。

10. 发明授权

US07762083B2 Gas turbine plant and gas turbine power generator plant 失效
标题翻译：燃气轮机厂和燃气轮机发电厂
公开(公告)号：US07762083B2
公开(公告)日：2010-07-27
申请号：US10989544
申请日：2004-11-17
申请人： Yasushi Hayasaka , Masaru Sekihara
发明人： Yasushi Hayasaka , Masaru Sekihara
IPC分类号： F02C6/04
CPC分类号： F04D29/5853 , F02C3/05 , F02C3/085 , F02C7/12 , F02C7/28
摘要： In a gas turbine plant and a gas turbine power generator plant, as a device of reducing the heat transfer from the gas turbine to the compressor, for instance, an air flow path for circulating part of compressed air from the compressor toward the gas turbine is formed between the gas turbine and the compressor. With the air flow path, which is a heat transfer reducing device, the heat conducted from the gas turbine to the compressor can be reduced by cooling or interception, and accordingly the temperature on the compressor side does not rise high, making it possible to prevent the performance of the compressor from deteriorating.
摘要翻译：在燃气轮机厂和燃气轮机发电厂中，作为减少从燃气轮机到压缩机的传热的装置，例如将压缩空气的压缩空气从压缩机向燃气轮机循环的空气流路是形成在燃气轮机和压缩机之间。利用作为传热降低装置的空气流动路径，可以通过冷却或拦截来减少从燃气轮机传递到压缩机的热量，因此压缩机侧的温度不会上升，从而可以防止压缩机的性能恶化。

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