-
公开(公告)号：US20100269515A1
公开(公告)日：2010-10-28
申请号：US12746579
申请日：2008-12-11
IPC分类号： F02C9/26
CPC分类号： F23R3/346 , F02C9/28 , F02C9/34 , F23N1/002 , F23N2037/02 , F23N2041/20 , F23R3/34
摘要： An object is to reduce a fluctuation in the gas-turbine output in a nozzle switching period. In the nozzle switching period during which a first nozzle group that has been used is switched to a second nozzle group that is going to be used, the amounts of fuel supplied through the first nozzle group and the second nozzle group are adjusted by using at least one adjustment parameter registered in advance, the adjustment parameter registered in advance is updated according to the operating condition of the gas turbine, and the updated adjustment parameter is registered as an adjustment parameter to be used next.
摘要翻译： 目的在于减少喷嘴切换期间的燃气轮机输出的波动。 在已经使用的第一喷嘴组切换到将要使用的第二喷嘴组的喷嘴切换期间中，通过使用至少使用第一喷嘴组和第二喷嘴组而供给的燃料量进行调整 预先登记的一个调整参数，根据燃气轮机的运转状况来更新预先登记的调整参数，将更新的调整参数登记为下一个要使用的调整参数。
-
2.发明授权Fuel control method and fuel control apparatus for gas turbine and gas turbine 有权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
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 。
-
3.发明申请FUEL CONTROL METHOD AND FUEL CONTROL APPARATUS FOR GAS TURBINE AND GAS TURBINE 有权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
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 。
-
公开(公告)号：US08800296B2
公开(公告)日：2014-08-12
申请号：US12746579
申请日：2008-12-11
IPC分类号： F02C9/28
CPC分类号： F23R3/346 , F02C9/28 , F02C9/34 , F23N1/002 , F23N2037/02 , F23N2041/20 , F23R3/34
摘要： An object is to reduce a fluctuation in the gas-turbine output in a nozzle switching period. In the nozzle switching period during which a first nozzle group that has been used is switched to a second nozzle group that is going to be used, the amounts of fuel supplied through the first nozzle group and the second nozzle group are adjusted by using at least one adjustment parameter registered in advance, the adjustment parameter registered in advance is updated according to the operating condition of the gas turbine, and the updated adjustment parameter is registered as an adjustment parameter to be used next.
摘要翻译： 目的在于减少喷嘴切换期间的燃气轮机输出的波动。 在已经使用的第一喷嘴组切换到将要使用的第二喷嘴组的喷嘴切换期间中，通过使用至少使用第一喷嘴组和第二喷嘴组而供给的燃料量进行调整 预先登记的一个调整参数，根据燃气轮机的运转状况来更新预先登记的调整参数，将更新的调整参数登记为下一个要使用的调整参数。
-
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
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。
-
公开(公告)号：US08490744B2
公开(公告)日：2013-07-23
申请号：US13121874
申请日：2009-10-15
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。
-
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
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。
-
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
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。
-
公开(公告)号：US20100313567A1
公开(公告)日：2010-12-16
申请号：US12866419
申请日：2008-11-20
IPC分类号： F02C3/00
CPC分类号： F01D9/023 , F01D5/142 , F01D9/041 , F05D2210/30 , F05D2210/40 , F05D2220/3212
摘要： In a gas turbine that generates rotational power by supplying fuel to compressed air compressed by a compressor and burning the fuel in a combustor and supplying resultant combustion gas to a turbine, a circumferential distance starting from a leading edge of a turbine first stage nozzle toward a trailing edge side of the first stage nozzle and ending at center of transition pieces of such combustors that are adjacent in a circumferential direction is set relative to a circumferential pitch of such first stage nozzles within a range of 0.05≦S/P≦0.15, and an axial distance between a leading edge of the first stage nozzle and a transition piece rear end of the combustor is set relative to the circumferential pitch of the first stage nozzles within a range of 0.00≦L/P≦0.13. By improving the relative position of a transition piece of the combustor and the first stage nozzle, both suppression of inner pressure fluctuations of the combustor and enhancement in aerodynamic efficiency can be achieved.
摘要翻译： 在燃气轮机中，通过向由压缩机压缩的压缩空气供给燃料并燃烧燃烧器中的燃料并将合成的燃烧气体供给到涡轮机而产生旋转动力，从涡轮机第一级喷嘴的前缘朝向 第一级喷嘴的后缘侧并且在这样的燃烧器的周向相邻的过渡件的中心处终止，相对于这种第一级喷嘴的周向间距设定在0.05＆lt; NlE; S / P＆nlE; 0.15的范围内， 并且在第一级喷嘴的前缘与燃烧器的过渡件后端之间的轴向距离相对于第一级喷嘴的周向间距设定在0.00＆amp; llE; L / P＆nlE; 0.13的范围内。 通过改善燃烧器和第一级喷嘴的过渡件的相对位置，可以实现燃烧器的内部压力波动的抑制和空气动力学效率的提高。
-
公开(公告)号：US20100132375A1
公开(公告)日：2010-06-03
申请号：US12519574
申请日：2008-06-04
申请人： Satoshi Tanimura , Sosuke Nakamura
发明人： Satoshi Tanimura , Sosuke Nakamura
IPC分类号： F02C7/20
CPC分类号： F23R3/48 , F02C7/222 , F02C9/28 , F23R2900/00013 , F23R2900/00014
摘要： In order to reduce a manufacturing cost and a running cost, casings (22) each housing a combustion oscillation detecting device (21) are attached in an alternating manner to cross-flame tubes (17) by which a plurality of combustors arranged annularly in a combustor casing are connected to each other.
摘要翻译： 为了降低制造成本和运行成本，将容纳燃烧振动检测装置（21）的壳体（22）交替地安装到交叉火焰管（17）中，多个燃烧器环状配置在 燃烧器壳体彼此连接。
-
-
-
-
-
-
-
-
-
搜索结果
27 条记录 (耗时 0.025 秒)
