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

US08826666B2 Nozzle, and gas turbine combustor having the nozzle 有权
标题翻译：喷嘴和具有喷嘴的燃气轮机燃烧器
公开(公告)号：US08826666B2
公开(公告)日：2014-09-09
申请号：US13882655
申请日：2012-03-30
申请人： Shuhei Kajimura , Keijiro Saito , Satoshi Takiguchi , Mitsuhiro Nakao , Koichi Nishida , Shinji Akamatsu , Sosuke Nakamura , Masaki Mitani
发明人： Shuhei Kajimura , Keijiro Saito , Satoshi Takiguchi , Mitsuhiro Nakao , Koichi Nishida , Shinji Akamatsu , Sosuke Nakamura , Masaki Mitani
IPC分类号： F02C1/00 , F23R3/34 , F23R3/28 , F23D14/24 , F23R3/14
CPC分类号： F23R3/28 , F23C2900/07021 , F23D14/24 , F23D2900/00014 , F23D2900/00016 , F23R3/14 , F23R3/283 , F23R3/343
摘要： A pilot nozzle, a gas turbine combustor and a gas turbine are provided with a nozzle main body having a fuel passage, a cover ring arranged at an outside of a front end-outer peripheral portion of the nozzle main body at a predetermined interval to form an inner air passage and capable of injecting air toward a front side of the nozzle main body, a plurality of nozzle tips that includes a fuel injection nozzle attached to a front end portion of the cover ring at a predetermined interval in a circumferential direction to communicate with the fuel passage and is able to inject fuel toward an outside of injection air from the inner air passage, and a swirling force application unit that applies a swirling force to air injected through the inner air passage.
摘要翻译：引燃喷嘴，燃气轮机燃烧器和燃气轮机设置有具有燃料通道的喷嘴主体，以预定间隔布置在喷嘴主体的前端部外周部分的外侧的盖环，以形成内部空气通道并且能够朝向喷嘴主体的前侧喷射空气;多个喷嘴头，其包括燃料喷嘴，喷嘴以周向方向以预定间隔安装到盖环的前端部，以便连通并且能够从内部空气通道向喷射空气的外部喷射燃料;以及旋转力施加单元，其通过内部空气通道喷射的空气施加旋转力。

2. 发明申请

US20140041389A1 NOZZLE, GAS TURBINE COMBUSTOR AND GAS TURBINE 有权
标题翻译：喷嘴，气体涡轮机和气体涡轮
公开(公告)号：US20140041389A1
公开(公告)日：2014-02-13
申请号：US13882655
申请日：2012-03-30
申请人： Shuhei Kajimura , Keijiro Saito , Satoshi Takiguchi , Mitsuhiro Nakao , Koichi Nishida , Shinji Akamatsu , Sosuke Nakamura , Masaki Mitani
发明人： Shuhei Kajimura , Keijiro Saito , Satoshi Takiguchi , Mitsuhiro Nakao , Koichi Nishida , Shinji Akamatsu , Sosuke Nakamura , Masaki Mitani
IPC分类号： F23R3/28
CPC分类号： F23R3/28 , F23C2900/07021 , F23D14/24 , F23D2900/00014 , F23D2900/00016 , F23R3/14 , F23R3/283 , F23R3/343
摘要： A pilot nozzle, a gas turbine combustor and a gas turbine are provided with a nozzle main body having a fuel passage, a cover ring arranged at an outside of a front end-outer peripheral portion of the nozzle main body at a predetermined interval to form an inner air passage and capable of injecting air toward a front side of the nozzle main body, a plurality of nozzle tips that includes a fuel injection nozzle attached to a front end portion of the cover ring at a predetermined interval in a circumferential direction to communicate with the fuel passage and is able to inject fuel toward an outside of injection air from the inner air passage, and a swirling force application unit that applies a swirling force to air injected through the inner air passage.
摘要翻译：引燃喷嘴，燃气轮机燃烧器和燃气轮机设置有具有燃料通道的喷嘴主体，以预定间隔布置在喷嘴主体的前端部外周部分的外侧的盖环，以形成内部空气通道并且能够朝向喷嘴主体的前侧喷射空气;多个喷嘴头，其包括燃料喷嘴，喷嘴以周向方向以预定间隔安装到盖环的前端部，以便连通并且能够从内部空气通道向喷射空气的外部喷射燃料;以及旋转力施加单元，其通过内部空气通道喷射的空气施加旋转力。

3. 发明申请

US20100319351A1 GAS TURBINE COMBUSTOR 有权
标题翻译：气体涡轮搅拌机
公开(公告)号：US20100319351A1
公开(公告)日：2010-12-23
申请号：US12666673
申请日：2008-12-19
申请人： Kei Inoue , Keijiro Saito , Yoshikazu Matsumura , Sosuke Nakamura
发明人： Kei Inoue , Keijiro Saito , Yoshikazu Matsumura , Sosuke Nakamura
IPC分类号： F02C7/22 , F02C7/264
CPC分类号： F23D14/70 , F23R3/286 , F23R3/343
摘要： Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.
摘要翻译：提供一种燃气轮机燃烧器，其能够减小在先导火焰和预混合火焰之间形成的先导空气的低温空气层的尺寸，并且提高预混火焰的火焰稳定性。一种燃气轮机燃烧器，其设置有引导式燃烧器，该引燃式燃烧器设置在形成为圆筒状的燃烧器主体的中心部分以形成引燃火焰;以及多个主燃烧器，形成预混火焰的引燃燃烧器包括作为点燃改善部件的减少先导火焰和预混火焰之间形成的先导空气的低温空气层的尺寸的通道阻挡构件。

4. 发明授权

US08794004B2 Gas turbine combustor 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US08794004B2
公开(公告)日：2014-08-05
申请号：US12666673
申请日：2008-12-19
申请人： Kei Inoue , Keijiro Saito , Yoshikazu Matsumura , Sosuke Nakamura
发明人： Kei Inoue , Keijiro Saito , Yoshikazu Matsumura , Sosuke Nakamura
IPC分类号： F02C1/00
CPC分类号： F23D14/70 , F23R3/286 , F23R3/343
摘要： Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.
摘要翻译：提供一种燃气轮机燃烧器，其能够减小在先导火焰和预混合火焰之间形成的先导空气的低温空气层的尺寸，并提高预混火焰的火焰稳定性。一种燃气轮机燃烧器，其设置有引导式燃烧器，该引燃式燃烧器设置在形成为圆筒状的燃烧器主体的中心部分以形成引燃火焰;以及多个主燃烧器，形成预混火焰的引燃燃烧器包括作为点燃改善部件的减少先导火焰和预混火焰之间形成的先导空气的低温空气层的尺寸的通道阻挡构件。

5. 发明授权

US08707671B2 Fuel control method and fuel control apparatus for gas turbine and gas turbine 有权
标题翻译：燃气轮机和燃气轮机的燃油控制方法和燃料控制装置
公开(公告)号：US08707671B2
公开(公告)日：2014-04-29
申请号：US12671473
申请日：2009-07-01
申请人： Sosuke Nakamura , Satoshi Tanimura , Shinji Akamatsu , Shinsuke Nakamura , Takashi Sonoda , Akihiko Saito , Makoto Kishi
发明人： Sosuke Nakamura , Satoshi Tanimura , Shinji Akamatsu , Shinsuke Nakamura , Takashi Sonoda , Akihiko Saito , Makoto Kishi
IPC分类号： F02C9/32 , F02C9/28 , F23R3/34
CPC分类号： F02C9/26 , F02C9/34 , F05D2270/082 , F23K5/005 , F23R3/286 , F23R3/36
摘要： A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced. Because fuel is supplied from the main nozzles of all groups and burned in the entire area of the combustor upon ignition, it is possible to easily propagate a flame to all the other adjacent main nozzle groups, thereby improving the ignition characteristics of the whole gas turbine.
摘要翻译：一种用于具有燃烧器的燃气轮机的燃料控制方法，所述燃气轮机由至少两组用于供应燃料的主喷嘴组成，并且在燃烧器（S1）点火时从所有组的主喷嘴供应燃料，并且供应在燃气轮机的后续加速期间来自组A的三个主喷嘴的燃料（S3）。由于在加速期间从少量主喷嘴喷射燃料，所以每个主喷嘴的燃料流量增加，从而提高燃烧区域的燃料空气比（燃料流量/空气流量），提高燃烧特点因此，一氧化碳和未燃碳氢化合物的产生减少，由此不需要旁通阀并且降低制造成本。因为燃料从所有组的主喷嘴供应并且在点火时在燃烧器的整个区域燃烧，所以可以容易地将火焰传播到所有其他相邻的主喷嘴组，从而提高整个燃气轮机的点火特性。

6. 发明申请

US20110016873A1 FUEL CONTROL METHOD AND FUEL CONTROL APPARATUS FOR GAS TURBINE AND GAS TURBINE 有权
标题翻译：燃油控制方法和燃油控制装置用于气体涡轮机和气体涡轮机
公开(公告)号：US20110016873A1
公开(公告)日：2011-01-27
申请号：US12671473
申请日：2009-07-01
申请人： Sosuke Nakamura , Satoshi Tanimura , Shinji Akamatsu , Shinsuke Nakamura , Takashi Sonoda , Akihiko Saito , Makoto Kishi
发明人： Sosuke Nakamura , Satoshi Tanimura , Shinji Akamatsu , Shinsuke Nakamura , Takashi Sonoda , Akihiko Saito , Makoto Kishi
IPC分类号： F02C9/26 , F02C7/26
CPC分类号： F02C9/26 , F02C9/34 , F05D2270/082 , F23K5/005 , F23R3/286 , F23R3/36
摘要： A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced. Because fuel is supplied from the main nozzles of all groups and burned in the entire area of the combustor upon ignition, it is possible to easily propagate a flame to all the other adjacent main nozzle groups, thereby improving the ignition characteristics of the whole gas turbine.
摘要翻译：一种用于具有燃烧器的燃气轮机的燃料控制方法，所述燃气轮机由至少两组用于供应燃料的主喷嘴组成，并且在燃烧器（S1）点燃时从所有组的主喷嘴供应燃料，并且供应在燃气轮机的后续加速期间来自组A的三个主喷嘴的燃料（S3）。由于在加速期间从少量主喷嘴喷射燃料，所以每个主喷嘴的燃料流量增加，从而提高燃烧区域的燃料空气比（燃料流量/空气流量），提高燃烧特点因此，一氧化碳和未燃碳氢化合物的产生减少，由此不需要旁通阀并且降低制造成本。因为燃料从所有组的主喷嘴供应并且在点火时在燃烧器的整个区域燃烧，所以可以容易地将火焰传播到所有其他相邻的主喷嘴组，从而提高整个燃气轮机的点火特性。

7. 发明授权

US08448451B2 Height ratios for a transition piece of a combustor 有权
标题翻译：燃烧器过渡件的高度比
公开(公告)号：US08448451B2
公开(公告)日：2013-05-28
申请号：US12674352
申请日：2009-04-23
申请人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
发明人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
IPC分类号： F02C3/04 , F02C1/00
CPC分类号： F01D9/023 , F05D2250/50 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , Y02E20/16 , Y10T29/49229 , Y10T29/49348
摘要： Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79≦Dout/Din≦0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.
摘要翻译：提供了一种燃烧器连接结构，其中过渡件出口的横截面积（Dout）相对于过渡件入口的横截面面积（Din）设定在0.79 @ Dout / Din @ 0.9的范围内并且在连接到过渡件出口的涡轮机的第一级涡轮喷嘴中，在内护罩和外护罩的上游端之间的径向方向上的尺寸（Hin）具有与尺寸相同的尺寸（a ）在过渡件出口的径向方向上。在包括在具有与燃气轮机的转子的轴向中心（R）成一角度的中心线（S））并且将燃烧气体引导到涡轮机的燃烧器中的燃烧器过渡件中，横截面积从燃烧气体流过到燃烧气体流出的过渡件出口的过渡件入口单调地减少。

8. 发明申请

US20110265491A1 COMBUSTOR CONNECTION STRUCTURE, COMBUSTOR TRANSITION PIECE, DESIGNING METHOD OF COMBUSTOR TRANSITION PIECE, AND GAS TURBINE 有权
标题翻译： COMBUSTOR连接结构，COMBUSTOR过渡片，COMBUSTOR TRANSITION PIECE和燃气轮机的设计方法
公开(公告)号：US20110265491A1
公开(公告)日：2011-11-03
申请号：US12674352
申请日：2009-04-23
申请人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
发明人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
IPC分类号： F02C7/20 , G06F17/50
CPC分类号： F01D9/023 , F05D2250/50 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , Y02E20/16 , Y10T29/49229 , Y10T29/49348
摘要： Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet (222) is set within a range of 0.79≦Dout/Din≦0.9, relative to a cross-sectional area (Din) of a transition piece inlet (221) of a combustor (2), and in a first stage turbine nozzle (321) of a turbine (3) connected to the transition piece outlet (222), a size (Hin) in a radial direction of an upstream opening is matched with a size (a) in a radial direction of the transition piece outlet (222). In a combustor transition piece (22) that is included in the combustor (2) having a center line (S) arranged with an angle to an axial center (R) of a rotor (4) of a gas turbine and that guides combustion gas to the turbine (3), a cross-sectional area is monotonously reduced from the transition piece inlet (221) in which the combustion gas flows to the transition piece outlet (222) from which the combustion gas flows out.
摘要翻译：提供了一种燃烧器连接结构，其中过渡件出口（222）的横截面面积（Dout）设定在0.79

9. 发明授权

US08857189B2 Gas turbine combustion burner 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US08857189B2
公开(公告)日：2014-10-14
申请号：US13495499
申请日：2012-06-13
申请人： Keisuke Matsuyama , Takanori Ito , Tei Yamato , Koji Maeta , Sosuke Nakamura
发明人： Keisuke Matsuyama , Takanori Ito , Tei Yamato , Koji Maeta , Sosuke Nakamura
IPC分类号： F02C7/24 , F02C1/00 , F23R3/28
CPC分类号： F23R3/28 , F23R2900/00014
摘要： In a gas-turbine combustion burner which is provided, at a distal end thereof, with a fuel spraying hole that sprays fuel into a combustion region formed inside a combustion cylinder of a gas-turbine combustor and in which a fuel flow path that guides the fuel, which is supplied from a fuel source, to the fuel spraying hole is formed in the interior thereof, the impedance of a fuel supply system that guides the fuel from the fuel source to the fuel spraying hole is set so that propagation of pressure fluctuations from the combustion region to the fuel supply system becomes an allowable level or less.
摘要翻译：在一种燃气轮机燃烧器中，在燃气轮机燃烧器的远端设置有燃料喷射孔，该燃料喷射孔将燃料喷射到形成在燃气轮机燃烧器的燃烧气缸内部的燃烧区域中，在其内部形成从燃料源供给到燃料喷射孔的燃料，将燃料从燃料源引导到燃料喷射孔的燃料供给系统的阻抗被设定为使压力波动的传播从燃烧区域到燃料供给系统成为允许水平以下。

10. 发明授权

US08490744B2 Combustor and gas turbine having the same 有权
标题翻译：燃气轮机和燃气轮机相同
公开(公告)号：US08490744B2
公开(公告)日：2013-07-23
申请号：US13121874
申请日：2009-10-15
申请人： Sosuke Nakamura , Taiki Kinoshita , Masaki Ono , Keisuke Matsuyama , Kenta Taniguchi
发明人： Sosuke Nakamura , Taiki Kinoshita , Masaki Ono , Keisuke Matsuyama , Kenta Taniguchi
IPC分类号： F02K1/00
CPC分类号： F23R3/005 , F01D9/023 , F01D25/04 , F23M20/005 , F23R3/06 , F23R3/46 , F23R2900/00014
摘要： An object is to provide a combustor that requires a small mounting space for an acoustic damper, that can achieve size reduction, and that can improve the ease of maintenance. A combustor (5) of the present invention includes a combustion cylinder (19) that defines a combustion area (23) therein and an acoustic damper (31) that has a damper cover having an acoustic-damper resonance space communicating with the combustion area (23). The damper cover is provided along the combustion cylinder (19) so as to extend in a direction intersecting an axial direction (L) of the combustion cylinder (19).
摘要翻译：目的是提供一种需要用于声阻尼器的小的安装空间的燃烧器，其可以实现尺寸减小，并且可以提高维护的便利性。本发明的燃烧器（5）包括在其中限定燃烧区域（23）的燃烧气缸（19）和具有阻尼器盖的声阻尼器（31），所述阻尼器罩具有与燃烧区域连通的声阻尼器谐振空间 23）。阻尼器盖沿着燃烧筒（19）设置成沿与燃烧气缸（19）的轴向（L）相交的方向延伸。

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