专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US4936089A Gas turbine plant system and gas pressure stabilizer thereof in emergency 失效
标题翻译：燃气轮机厂系统及其气压稳定器在紧急情况下
公开(公告)号：US4936089A
公开(公告)日：1990-06-26
申请号：US283270
申请日：1988-12-09
申请人： Shigeru Komiyama , Katsunori Yoshida , Yoshiaki Tsukuda , Eiji Akita , Kenji Imamura
发明人： Shigeru Komiyama , Katsunori Yoshida , Yoshiaki Tsukuda , Eiji Akita , Kenji Imamura
IPC分类号： F02C6/00 , F02C3/22 , F02C7/22 , F02C7/232 , F02C9/26 , F02C9/40 , F02C9/46
CPC分类号： F02C7/232 , F02C3/22 , F02C9/26
摘要： Disclosed herein is a gas turbine system which is supplied with a low-pressure industrial by-product gas as a fuel and equipped coaxially with a gas compressor for compressing the fuel gas, the system providing a bypass pipeline for returning the gas in a high-pressure gas piping on the discharge side of the fuel gas compressor into a low-pressure gas piping on the inlet side of the compressor through a pressure reducing valve and a cooler, and an emergency gas pressure stabilizer having high responsive characteristics, the stabilizer being provided in the bypass pipeline on the outlet side of the cooler, whereby the high-pressure fuel gas on the discharge side of the fuel gas compressor can be returned safely into a low-pressure industrial by-product gas pipeline.

2. 发明授权

US06634175B1 Gas turbine and gas turbine combustor 有权
标题翻译：燃气轮机和燃气轮机燃烧器
公开(公告)号：US06634175B1
公开(公告)日：2003-10-21
申请号：US09762598
申请日：2001-02-09
申请人： Yutaka Kawata , Shigemi Mandai , Yoshiaki Tsukuda , Eiji Akita , Hisato Arimura
发明人： Yutaka Kawata , Shigemi Mandai , Yoshiaki Tsukuda , Eiji Akita , Hisato Arimura
IPC分类号： F23R310
CPC分类号： F23R3/04
摘要： A gas turbine combustor has homogenous air inflow by elimination of turbulence from the air, reducing combustion instability. A combustor 3 has, at its center, a pilot nozzle 8 and eight main nozzles 7 around the pilot nozzle 8. The air flows in around the individual nozzles 7 and 8 to the leading end of the combustor 3 so that it is used for combustion. An annular flow ring 20, having a semicirculat section, is disposed at the upstream end portion of a combustion cylinder 10, and a porous plate 50 and a surrounding rib 51 are disposed downstream of the flow ring 20. The air inflow is smoothly turned at first by the flow ring 20 and then straightened by the porous plate 50 so that the air flows without any disturbance around the individual nozzles 7 and 8 to the leading end, thereby reducing combustion instability.
摘要翻译：燃气轮机燃烧器通过消除来自空气的紊流而具有均匀的空气流入，从而降低燃烧不稳定性。燃烧器3在其中心处具有引导喷嘴8和围绕引燃喷嘴8的八个主喷嘴7.空气在单独的喷嘴7和8周围流到燃烧器3的前端，使其用于燃烧。具有半圆形部分的环形流动环20设置在燃烧气缸10的上游端部，并且多孔板50和周围肋51设置在流动环20的下游。空气流入平滑地转向首先通过流动环20，然后由多孔板50拉直，使得空气在各个喷嘴7和8周围没有任何干扰地流到前端，从而减少燃烧不稳定性。

3. 发明授权

US06244039B1 Combined cycle plant having a heat exchanger for compressed air 失效
标题翻译：具有用于压缩空气的热交换器的联合循环设备
公开(公告)号：US06244039B1
公开(公告)日：2001-06-12
申请号：US09300841
申请日：1999-04-28
申请人： Hideaki Sugishita , Yoshiaki Tsukuda , Kazuo Uematsu , Eiji Akita
发明人： Hideaki Sugishita , Yoshiaki Tsukuda , Kazuo Uematsu , Eiji Akita
IPC分类号： F02C600
CPC分类号： F01K23/106 , Y02E20/16
摘要： A combined cycle plant includes a heat exchanger (3) for recovering heat into compressed air or gas turbine fuel to be supplied into gas turbine (01). The plant is arranged such that steam is used as high temperature side working medium of the heat exchanger (3). Thus, the heating medium supply passage can be made of ordinary steam piping and piping cost is reduced. Also, gas turbine exhaust gas is led directly into a waste heat recovery boiler (02), so that gas turbine efficiency and combined efficiency can be enhanced and plant manufacturing cost is reduced.
摘要翻译：联合循环设备包括用于将热量回收到被供应到燃气轮机（01）中的压缩空气或燃气涡轮燃料中的热交换器（3）。该设备布置成使得蒸汽用作热交换器（3）的高温侧工作介质。因此，加热介质供给通路可以由普通蒸汽管道制成，并且管道成本降低。此外，燃气轮机废气直接引入废热回收锅炉（02），从而可以提高燃气轮机效率和组合效率，降低设备制造成本。

4. 发明授权

US06212873B1 Gas turbine combined cycle 失效
标题翻译：燃气轮机联合循环
公开(公告)号：US06212873B1
公开(公告)日：2001-04-10
申请号：US09256106
申请日：1999-02-24
申请人： Hideaki Sugishita , Hidetaka Mori , Yoshiaki Tsukuda , Kazuo Uematsu , Eiji Akita
发明人： Hideaki Sugishita , Hidetaka Mori , Yoshiaki Tsukuda , Kazuo Uematsu , Eiji Akita
IPC分类号： F02C600
CPC分类号： F01K23/106 , Y02E20/14 , Y02E20/16
摘要： The invention provides a gas turbine combined cycle structured such that an intermediate cooling device for cooling a compression air discharged from a low pressure compressor, so as to reduce a load of a high pressure compressor, is provided. The gas turbine combined cycle in accordance with the invention is structured such as to branch water from a condenser to a steam generating device for generating steam. Exhaust gas discharged from a steam turbine is condensed to water. Compression air discharged from a low pressure compressor is cooled by being supplied to an intermediate cooling device, and is then supplied to a high pressure compressor. Steam which heats and operates the steam turbine is generated by the heat recovered by the cooling of the compression air in the intermediate cooling device. Accordingly, there can be obtained a gas turbine combined cycle having the advantage of the conventional intermediate cooling type gas turbine combined cycle, but exhibiting an improved combined efficiency.
摘要翻译：本发明提供了一种燃气轮机联合循环，其结构使得用于冷却从低压压缩机排出的压缩空气以减少高压压缩机的负荷的中间冷却装置。根据本发明的燃气轮机联合循环被构造为将水从冷凝器分配到用于产生蒸汽的蒸汽发生装置。从汽轮机排出的排气被冷凝成水。从低压压缩机排出的压缩空气通过供给到中间冷却装置而冷却，然后供给高压压缩机。通过中间冷却装置中的压缩空气冷却回收的热量产生加热和操作蒸汽轮机的蒸汽。因此，可以获得具有传统的中间冷却型燃气轮机联合循环的优点的燃气轮机联合循环，但是显示出提高的组合效率。

5. 发明申请

US20050089403A1 Blade structure in a gas turbine 审中-公开
标题翻译：燃气轮机中的叶片结构
公开(公告)号：US20050089403A1
公开(公告)日：2005-04-28
申请号：US10913524
申请日：2004-08-09
申请人： Eisaku Ito , Eiji Akita
发明人： Eisaku Ito , Eiji Akita
IPC分类号： F01D9/02 , F01D5/14 , F01D11/10 , F01D9/00
CPC分类号： F01D5/142 , F01D5/141 , F01D5/145 , F05D2240/12
摘要： In the blade structure in a gas turbine, front-edge including angles are made large. As a result, a curve of a relative relationship between incidence angles ic1 and is1 and pressure loss becomes mild. Entrance metal angles are made small. As a result, it becomes possible to make the incidence angles small. Chord length of a tip portion of a moving blade is made large. As a result, it becomes possible to make small the deceleration on a rear surface of the tip portion of the moving blade. Accordingly, it becomes possible to make the pressure loss small, and therefore, it becomes possible to improve the turbine efficiency.
摘要翻译：在燃气轮机的叶片结构中，使包括角度在内的前缘变大。结果，入射角度ic 1之间的相对关系曲线为1，压力损失变得温和。入口金属角度很小。结果，可以使入射角变小。活动叶片的尖端部分的弦长变大。结果，能够使动叶片的前端部的后表面的减速度变小。因此，可以使压力损失小，能够提高涡轮效率。

6. 发明授权

US06267583B1 Combustor 有权
标题翻译：燃烧器
公开(公告)号：US06267583B1
公开(公告)日：2001-07-31
申请号：US09289606
申请日：1999-04-12
申请人： Shigemi Mandai , Koichi Nishida , Masataka Ota , Eiji Akita
发明人： Shigemi Mandai , Koichi Nishida , Masataka Ota , Eiji Akita
IPC分类号： F23D1484
CPC分类号： F23D23/00 , F23D2206/10 , F23M20/005
摘要： A combustor includes a pilot fuel nozzle and a plurality of main premixing nozzles arranged therearound for forming a premixture of air and fuel supplied from a main fuel nozzle, and is improved so as not to cause vibratory combustion. Pilot fuel nozzle unit 104 comprises a plurality of pilot fuel nozzles 103. A plurality of main premixing nozzles 102 are disposed on a coaxial circumference of the pilot fuel nozzle unit 104. The pilot fuel nozzles 103 are arranged irregularly in a circumferential direction of the pilot fuel nozzle unit 104, so as to form portion 105 where there is no pilot fuel nozzle 103. Premature in the main premixing nozzles 102 positioned corresponding to the pilot fuel nozzle 103 burns with comparatively short flames. Premature in the main premixing nozzles 102 positioned corresponding to the portion 105 of no pilot fuel nozzle 103 burns with long flames because of flames spreading from adjacent main fuel nozzles. Thus, by differences in flame length, heat generation rate distribution is dispersed.
摘要翻译：燃烧器包括导向燃料喷嘴和布置在其周围的多个主预混合喷嘴，用于形成从主燃料喷嘴供应的空气和燃料的预混合物，并且被改进以便不引起振动燃烧。先导燃料喷嘴单元104包括多个先导燃料喷嘴103.多个主要预混合喷嘴102设置在引燃燃料喷嘴单元104的同轴圆周上。引燃燃料喷嘴103沿飞行员的周向不规则地排列燃料喷嘴单元104，以便形成不存在先导燃料喷嘴103的部分105.在对应于引燃燃料喷嘴103定位的主预混合喷嘴102中，过早地燃烧较短的火焰。由于相邻的主燃料喷嘴的火焰蔓延，在与主燃料喷嘴103的部分105对应定位的主预混合喷嘴102中过早地燃烧着较长的火焰。因此，通过火焰长度的差异，分散发热率分布。

7. 发明授权

US06887042B2 Blade structure in a gas turbine 有权
公开(公告)号：US06887042B2
公开(公告)日：2005-05-03
申请号：US10022770
申请日：2001-12-20
申请人： Eisaku Ito , Eiji Akita
发明人： Eisaku Ito , Eiji Akita
IPC分类号： F01D9/02 , F01D5/14 , F01D11/10
CPC分类号： F01D5/142 , F01D5/141 , F01D5/145 , F05D2240/12
摘要： In the blade structure in a gas turbine, front-edge including angles are made large. As a result, a curve of a relative relationship between incidence angles ic1 and is1 and pressure loss becomes mild. Entrance metal angles are made small. As a result, it becomes possible to make the incidence angles small. Chord length of a tip portion of a moving blade is made large. As a result, it becomes possible to make small the deceleration on a rear surface of the tip portion of the moving blade. Accordingly, it becomes possible to make the pressure loss small, and therefore, it becomes possible to improve the turbine efficiency.

8. 发明授权

US07229248B2 Blade structure in a gas turbine 有权
标题翻译：燃气轮机中的叶片结构
公开(公告)号：US07229248B2
公开(公告)日：2007-06-12
申请号：US10913366
申请日：2004-08-09
申请人： Eisaku Ito , Eiji Akita
发明人： Eisaku Ito , Eiji Akita
IPC分类号： F01D1/02
CPC分类号： F01D5/142 , F01D5/141 , F01D5/145 , F05D2240/12
摘要： In the blade structure in a gas turbine, front-edge including angles are made large. As a result, a curve of a relative relationship between incidence angles ic1 and is1 and pressure loss becomes mild. Entrance metal angles are made small. As a result, it becomes possible to make the incidence angles small. Chord length of a tip portion of a moving blade is made large. As a result, it becomes possible to make small the deceleration on a rear surface of the tip portion of the moving blade. Accordingly, it becomes possible to make the pressure loss small, and therefore, it becomes possible to improve the turbine efficiency.
摘要翻译：在燃气轮机的叶片结构中，使包括角度在内的前缘变大。结果，入射角度ic 1之间的相对关系曲线为1，压力损失变得温和。入口金属角度很小。结果，可以使入射角变小。活动叶片的尖端部分的弦长变大。结果，能够使动叶片的前端部的后表面的减速度变小。因此，可以使压力损失小，能够提高涡轮效率。

9. 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。

10. 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。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式