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1. 发明授权

US06430916B1 Combined cycle power plant 有权
公开(公告)号：US06430916B1
公开(公告)日：2002-08-13
申请号：US09866710
申请日：2001-05-30
申请人： Hideaki Sugishita , Hidetaka Mori , Ichiro Fukue , Kazuo Uematsu
发明人： Hideaki Sugishita , Hidetaka Mori , Ichiro Fukue , Kazuo Uematsu
IPC分类号： F02C618
摘要： Provided is turbine plant using methanol as fuel in which working fluid is compressed by compressor 1 and led into combustor 2. A mixture of H2 and CO2 as fuel added with O2 is burned to generate high temperature gas, which works in high temperature turbine 3, flows through heat exchangers 4, 5 and returns partly to the compressor 1 and enters partly low pressure turbine 7 of a bottoming system to work. Condensed water from condenser 9 of the bottoming system is pressurized by pressure pump 10 and flows through the heat exchangers 4, 5 to become high temperature steam and to work in high pressure turbine 6. Exhaust gas thereof is mixed into the combustor 2. A mixture of methanol and water is supplied into reformer 13 to absorb heat from the heat exchanger 4 to be reformed into H2 and CO2, which is supplied into the combustor 2. A high temperature portion of the high temperature turbine 3 is cooled by cooling medium extracted from the compressor 1 outlet and high pressure turbine 6 outlet thereby reliability of the high temperature turbine 3 is enhanced.

2. 发明授权

US06536205B2 Combined cycle power plant 失效
公开(公告)号：US06536205B2
公开(公告)日：2003-03-25
申请号：US10096939
申请日：2002-03-14
申请人： Hideaki Sugishita , Hidetaka Mori , Ichiro Fukue , Kazuo Uematsu
发明人： Hideaki Sugishita , Hidetaka Mori , Ichiro Fukue , Kazuo Uematsu
IPC分类号： F02C618
CPC分类号： F01K23/10 , Y02E20/16 , Y02E20/344
摘要： Provided is turbine plant using methanol as fuel in which working fluid is compressed by compressor 1 and led into combustor 2. A mixture of H2 and CO2 as fuel added with O2 is burned to generate high temperature gas, which works at high temperature turbine 3, flows through heat exchangers 4, 5 and returns partly to the compressor 1 and enters partly low pressure turbine 7 of bottoming system to work. Condensed water from condenser 9 of the bottoming system is pressurized by pressure pump 10 and flows through the heat exchangers 4, 5 to become high temperature steam and to work at high pressure turbine 6. Exhaust gas thereof is mixed into the combustor 2. A mixture of methanol and water is supplied into reformer 13 to absorb heat from the heat exchanger 4 to be reformed into H2 and CO2, which is supplied into the combustor 2. A high temperature portion of the high temperature turbine 3 is cooled by cooling medium extracted from compressor 1 outlet and high pressure turbine 6 outlet thereby reliability of the high temperature turbine 3 is enhanced.

3. 发明授权

US06260348B1 Combined cycle power plant with fuel reformer 失效
标题翻译：燃料重整器联合循环发电厂
公开(公告)号：US06260348B1
公开(公告)日：2001-07-17
申请号：US09285066
申请日：1999-04-02
申请人： Hideaki Sugishita , Hidetaka Mori , Ichiro Fukue , Kazuo Uematsu
发明人： Hideaki Sugishita , Hidetaka Mori , Ichiro Fukue , Kazuo Uematsu
IPC分类号： F02C618
CPC分类号： F01K23/10 , Y02E20/16 , Y02E20/344
摘要： Provided is turbine plant using methanol as fuel in which working fluid is compressed by compressor 1 and led into combustor 2. A mixture of H2 and CO2 as fuel added with O2 is burned to generate high temperature gas, which works at high temperature turbine 3, flows through heat exchangers 4, 5 and returns partly to the compressor 1 and enters partly low pressure turbine 7 of bottoming system to work. Condensed water from condenser 9 of the bottoming system is pressurized by pressure pump 10 and flows through the heat exchangers 4, 5 to become high temperature steam and to work at high pressure turbine 6. Exhaust gas thereof is mixed into the combustor 2. A mixture of methanol and water is supplied into reformer 13 to absorb heat from the heat exchanger 4 to be reformed into H2 and CO2, which is supplied into the combustor 2. A high temperature portion of the high temperature turbine 3 is cooled by cooling medium extracted from compressor 1 outlet and high pressure turbine 6 outlet thereby reliability of the high temperature turbine 3 is enhanced.
摘要翻译：提供了使用甲醇作为燃料的涡轮机组，其中工作流体被压缩机1压缩并被引导到燃烧器2中。作为添加有O2的燃料的H 2和CO 2的混合物被燃烧以产生在高温涡轮机3工作的高温气体，流过热交换器4,5，并部分返回到压缩机1并进入底部系统的部分低压涡轮机7工作。底部系统的冷凝器9的冷凝水由压力泵10加压，流过热交换器4,5，成为高温蒸汽，并在高压汽轮机6工作。其废气混入燃烧器2中。混合物的甲醇和水被供给到重整器13中以从热交换器4吸收热量，以将其重新形成为供应到燃烧器2中的H 2和CO 2。高温涡轮3的高温部分由从压缩机1出口和高压涡轮机6出口，从而提高高温涡轮机3的可靠性。

4. 发明授权

US06190130B1 Gas turbine moving blade platform 有权
标题翻译：燃气轮机动叶片平台
公开(公告)号：US06190130B1
公开(公告)日：2001-02-20
申请号：US09255793
申请日：1999-02-23
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2240/81
摘要： A gas turbine moving blade platform having a simplified platform cooling structure. A cooling effect of the platform side end portions is increased resulting in uniform cooling of the entire platform. Cooling passages (2, 3) are bored in the platform (1) front portion so as to communicate with a cooling air passage (52) of the moving blade (51) and open at both platform side end surfaces. The openings are closed by inserting covers (2a, 2b) therein. Cooling passages (6, 4) are bored in platform (1) side end portions so as to communicate with the front end cooling passages (2, 3), respectively, and open in the platform rear end surface. A plurality of cooling holes (5) are bored so as to communicate with the cooling passage (4) and open at the platform side end surface. Thus, the entire platform is cooled uniformly and the platform side portions are cooled by the cooling holes (5) so that an effective cooling performance is ensured and also the workability of the cooling lines is enhanced.
摘要翻译：具有简化的平台冷却结构的燃气轮机动叶片平台。平台侧端部的冷却效果增加，导致整个平台的均匀冷却。在平台（1）的前部分中钻出冷却通道（2,3），以便与活动叶片（51）的冷却空气通道（52）连通并在两个平台侧端面处打开。通过将盖（2a，2b）插入其中来封闭开口。平台（1）的侧端部分分别将冷却通道（6,4）与前端冷却通道（2,3）连通，并在平台后端面开口。多个冷却孔（5）钻孔，以与冷却通道（4）连通并在平台侧端面打开。因此，整个平台被均匀地冷却，并且平台侧部分被冷却孔（5）冷却，从而确保了有效的冷却性能，并且还提高了冷却管线的可加工性。

5. 发明授权

US6152695A Gas turbine moving blade 有权
标题翻译：燃气轮机动叶片
公开(公告)号：US6152695A
公开(公告)日：2000-11-28
申请号：US243821
申请日：1999-02-03
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
IPC分类号： F01D5/18 , F01D5/20 , F01D5/22
CPC分类号： F01D5/187 , F01D5/225 , F05D2240/81 , F05D2260/22141
摘要： In a gas turbine moving blade 1, the convection of cooling air is promoted to enhance the heat transfer rate, the cooling effect of a shroud 2 is enhanced and the entire cooling effect of the blade is enhanced. An inner cavity 10 is formed in the blade over the entire length thereof. A multiplicity of pin fins 5 are provided in the inner cavity, being fixed to wall thereof. An enlarged cavity 6 is formed in the shroud 2 of a terminal end of the blade 1. Cooling air entering the inner cavity 10 of the blade 1 flows into the enlarged cavity 6 and flows out of the shroud 2 downwardly through holes 7 of a peripheral portion of the enlarged cavity 6. The entire portion of the shroud 2 is cooled uniformly, and the cooling effect of the entire blade is enhanced by an enhanced heat transfer rate in the blade and by uniform cooling of the entire shroud.
摘要翻译：在燃气轮机动叶片1中，促进冷却空气的对流，提高传热速度，提高护罩2的冷却效果，提高叶片的整体冷却效果。在叶片的整个长度上形成内腔10。多个销翅片5设置在内腔中，固定在其壁上。在叶片1的末端的护罩2中形成有扩大的空腔6.进入叶片1的内腔10的冷却空气流入扩大空腔6，并通过周边的孔7向下流出护罩2 扩大的腔体6的部分。护罩2的整个部分被均匀地冷却，并且整个刀片的冷却效果通过增加叶片中的传热速率和整个护罩的均匀冷却来增强。

6. 发明授权

US06196799B1 Gas turbine moving blade platform 失效
标题翻译：燃气轮机动叶片平台
公开(公告)号：US06196799B1
公开(公告)日：2001-03-06
申请号：US09252064
申请日：1999-02-18
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita , Koji Watanabe
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita , Koji Watanabe
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/81
摘要： A gas turbine moving blade platform having a simplified cooling structure for effecting uniform cooling of the platform. The platform (1) includes cavities (2, 3, 4) and an impingement plate (11) provided below the cavities (2, 3, 4). A cooling hole (5) communicates with cavity (2), cooling hole (6) communicated with cavity (3) and cooling holes (7, 8) communicate with cavity (4) and all of the cooling holes pass through the platform (1) at an inclined angle. Cooling air (70) flows into the cavities (2, 3, 4) through holes (12) in the impingement plate (11) for effecting impingement cooling of platform (1) plane portion. The cooling air (70) further flows through the cooling holes (5, 6, 7) to blow outside angularly upward for cooling peripheral portions of the platform. Thus, the platform is cooled uniformly, no lengthy and complicated cooling passage is provided, and workability is enhanced.
摘要翻译：一种具有简化冷却结构的燃气轮机动叶片平台，用于实现平台的均匀冷却。平台（1）包括空腔（2,3,4）和设置在空腔（2,3,4）下方的冲击板）。冷却孔（5）与空腔（2）连通，与空腔（3）连通的冷却孔（6）和冷却孔（7,8）与空腔（4）连通，所有的冷却孔都通过平台）。冷却空气（70）通过冲击板（11）中的孔（12）流入空腔（2,3,4），以实现平台（1）平面部分的冲击冷却。冷却空气（70）进一步流过冷却孔（5,6,7）以向外侧向外侧吹出以冷却平台的周边部分。因此，平台被均匀地冷却，没有设置冗长且复杂的冷却通道，并且可加工性得到提高。

7. 发明授权

US5947687A Gas turbine moving blade 失效
标题翻译：燃气轮机动叶片
公开(公告)号：US5947687A
公开(公告)日：1999-09-07
申请号：US862135
申请日：1997-05-22
申请人： Masahiko Mori , Yukihiro Hashimoto , Hiroji Tada , Ichiro Fukue , Keizo Tsukagoshi , Jyunichiro Masada
发明人： Masahiko Mori , Yukihiro Hashimoto , Hiroji Tada , Ichiro Fukue , Keizo Tsukagoshi , Jyunichiro Masada
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/147 , F05D2260/94 , F05D2260/941 , Y02T50/671
摘要： A movable gas turbine blade includes a platform (10) which is provided with a groove (15). The groove is located on a blade trailing side of the platform. Also, the groove is rounded and has a depth which does not enter a stress line of the platform caused by a load on the blade. The groove functions to suppress a high thermal stress arising at a connection portion of a blade trailing edge and the platform of the gas turbine air cooled moving blade during unsteady (start and stop) operation of the turbine.
摘要翻译：可移动燃气轮机叶片包括具有凹槽（15）的平台（10）。凹槽位于平台的叶片后侧。此外，凹槽是圆形的并且具有不会由叶片上的载荷引起的平台的压力线的深度。该凹槽用于在涡轮的不稳定（启动和停止）操作期间抑制在叶片后缘的连接部分和燃气轮机空气冷却的动叶片的平台处产生的高热应力。

8. 发明授权

US5410884A Combustor for gas turbines with diverging pilot nozzle cone 失效
标题翻译：燃气轮机燃油机具有发散的先导喷嘴锥体
公开(公告)号：US5410884A
公开(公告)日：1995-05-02
申请号：US137343
申请日：1993-10-18
申请人： Ichiro Fukue , Shigemi Mandai , Katsunori Tanaka , Hitoshi Kawabata , Nobuo Sato , Hiroyuki Nishida , Tetsuo Gora
发明人： Ichiro Fukue , Shigemi Mandai , Katsunori Tanaka , Hitoshi Kawabata , Nobuo Sato , Hiroyuki Nishida , Tetsuo Gora
IPC分类号： F23D17/00 , F23R3/28 , F23R3/34 , F23R3/36 , F02C1/00
CPC分类号： F23R3/286 , F23D17/002 , F23R3/34 , F23R3/36 , F23D2205/00
摘要： A gas turbine combustor suppresses the generation of NOx by mixing a fuel and air homogeneously. A pilot nozzle is provided at the center of the gas turbine combustor. A plurality of main nozzles surround the pilot nozzle. A diverging cone projects from the vicinity of the injection port of the pilot nozzle such that the flame from the main nozzles is sustained by the pilot nozzle and NOx is suppressed. The main nozzles can be provided upstream of the injection port of the pilot nozzle in which case an annular premixing nozzle having a throttled exit end is disposed downstream of the main nozzles. The main nozzle may also be in the form of a fuel nozzle having a plurality of tubes, a gaseous fuel being injected through one of the tubes, and liquid fuel being injected into the annular premixing nozzle through the other of the tubes so that the liquid fuel is atomized to mix the fuel and air homogeneously.
摘要翻译：燃气轮机燃烧器通过均匀混合燃料和空气来抑制NOx的产生。在燃气轮机燃烧器的中心设置有先导喷嘴。多个主喷嘴包围引燃喷嘴。发散锥从引燃喷嘴的喷射口附近突出，使得来自主喷嘴的火焰被导向喷嘴维持，并且抑制了NOx。主喷嘴可以设置在先导喷嘴的喷射口的上游，在这种情况下，具有节流出口端的环形预混喷嘴设置在主喷嘴的下游。主喷嘴也可以是具有多个管的燃料喷嘴的形式，气体燃料通过管中的一个喷射，液体燃料通过另一个管注入到环形预混合喷嘴中，使得液体燃料被雾化以均匀地混合燃料和空气。

9. 发明授权

US06250065B1 Gas turbine combustion system and combustor ignition method therefor 有权
标题翻译：燃气轮机燃烧系统及燃烧器点火方法
公开(公告)号：US06250065B1
公开(公告)日：2001-06-26
申请号：US09292385
申请日：1999-04-15
申请人： Shigemi Mandai , Tetsuo Gora , Koichi Nishida , Masataka Ota , Ichiro Fukue , Shinji Akamatsu , Satoshi Tanimura , Hideki Haruta , Tomohisa Takasaki , Teruya Tachibana
发明人： Shigemi Mandai , Tetsuo Gora , Koichi Nishida , Masataka Ota , Ichiro Fukue , Shinji Akamatsu , Satoshi Tanimura , Hideki Haruta , Tomohisa Takasaki , Teruya Tachibana
IPC分类号： F02B300
CPC分类号： F02C7/232
摘要： Liquid fuel purge device uses water, not compressed air as in the prior art, thereby prevented are rapid load change of gas turbine due to sudden discharge of liquid fuel and coking of remaining liquid fuel. Upon supply of liquid fuel to fuel nozzle (05) being stopped, water purge system (15) having stop valve (16) supplies water into fuel system including liquid fuel system (08) and fuel nozzle (05) and liquid fuel remaining therein is purged by water into combustion chamber (013) from the fuel nozzle (05).
摘要翻译：液体燃料净化装置如现有技术那样使用水而不是压缩空气，由此防止了由于液体燃料的突然排放和剩余的液体燃料的焦化引起的燃气轮机的快速负荷变化。在向燃料喷嘴（05）停止供应液体燃料时，具有截止阀（16）的净水系统（15）将水供应到包括液体燃料系统（08）和燃料喷嘴（05）的燃料系统中，其中残留的液体燃料是从燃料喷嘴（05）通过水从燃烧室（013）中清除。

10. 发明授权

US6099253A Gas turbine rotor blade 有权
标题翻译：燃气轮机转子叶片
公开(公告)号：US6099253A
公开(公告)日：2000-08-08
申请号：US203680
申请日：1998-12-01
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
IPC分类号： F01D5/18 , F01D5/20 , F02C7/18
CPC分类号： F01D5/225 , F01D5/187 , Y02T50/676
摘要： A gas turbine rotor blade has a plurality of first cooling holes for the flow of a cooling gas bored in a blade portion along its lengthwise direction and a plurality of second cooling holes for flow of the cooling gas bored in a shroud along its plane direction so as to communicate with the first cooling holes, and is constructed such that the cooling gas can flow in a uniform distribution. The plurality of the first cooling holes 3 for flow of the cooling gas are bored in the blade portion 2 and the plurality of the second cooling holes 5 for flow of the cooling gas are bored in the shroud 1 along its plane direction. The second cooling holes 5 communicate with the first cooling holes 3, hole to hole, via two-step holes 4, and the second cooling holes 5 are bored alternately on the dorsal side and the ventral side of the rotor blade.
摘要翻译：燃气轮机转子叶片具有多个第一冷却孔，用于沿其长度方向在叶片部分中钻出的冷却气体的流动，以及多个用于沿着其平面方向在护罩中钻出的冷却气体的流动的第二冷却孔，与第一冷却孔连通，并且被构造成使得冷却气体能够以均匀的分布流动。多个用于冷却气体流动的第一冷却孔3在叶片部分2中钻孔，并且用于冷却气体流动的多个第二冷却孔5沿其平面方向在护罩1中钻孔。第二冷却孔5通过两步孔4与第一冷却孔3，孔对孔连通，第二冷却孔5在转子叶片的背侧和腹侧交替地钻孔。

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