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1. 发明授权

US5584171A Gas turbine control method and apparatus 失效
标题翻译：燃气轮机控制方法及装置
公开(公告)号：US5584171A
公开(公告)日：1996-12-17
申请号：US365439
申请日：1994-12-28
申请人： Isao Sato , Fumiyuki Hirose , Minoru Takaba , Akira Shimura , Shoei Takahashi , Hiraku Ikeda
发明人： Isao Sato , Fumiyuki Hirose , Minoru Takaba , Akira Shimura , Shoei Takahashi , Hiraku Ikeda
IPC分类号： F02C9/50
CPC分类号： F02C9/50 , F05D2270/071
摘要： A gas turbine engine control method and apparatus as disclosed for optimizing fuel/air mixture, especially during decreasing load conditions. In a large capacity gas turbine engine system used for generation of electric power, the system is designed to operate at a relatively constant rotational speed of the turbine which drives an electric generator unit. The load of the turbine engine varies throughout the day due to changes in electrical power demands. During normal rated load conditions, the control of the fuel/air mixture is by way of changes in fuel supply, corrected to return the turbine exhaust temperature to a desired rated temperature. During this mode of operation, the compressor inlet guide vanes are maintained in a substantially constant open position. For accommodating decreasing load conditions where the temperature drops below a predetermined temperature level below the rated temperature operation, the system is switched to an inlet guide vane control mode of operation. During the guide vane control mode of operation, the inlet guide vanes are controlled at a more precise temperature correction sensitivity than is the case for normal load operations. This more precise inlet guide vane control during decreasing load conditions assures improved fuel/air mixture during decreasing load and consequent improved efficiency and minimal NO.sub.x compound emissions, especially during changing ambient temperature conditions where cold air would otherwise increase the air supply.
摘要翻译：公开的用于优化燃料/空气混合物的燃气涡轮发动机控制方法和装置，特别是在减小负载条件下。在用于产生电力的大容量燃气涡轮发动机系统中，该系统设计成以驱动发电机单元的涡轮机的相对恒定的转速运行。由于电力需求的变化，涡轮发动机的负载在一整天内变化。在正常的额定负载条件下，燃料/空气混合物的控制是通过燃料供应的变化来进行的，这被校正以将涡轮排气温度恢复到所需的额定温度。在这种操作模式下，压缩机入口导叶保持在基本恒定的打开位置。为了适应温度下降到低于额定温度运行的预定温度水平的降低负载条件，系统被切换到入口导叶控制操作模式。在导叶控制操作模式下，入口导流叶片的控制精度比正常加载操作更为精确。在降低负载条件下，这种更为精确的入口引导叶片控制确保了在减少负载的同时改善了燃料/空气混合物，从而提高了效率和最小化的NOx化合物排放，特别是在其他空气会增加空气供给的环境温度变化的环境中。

2. 发明授权

US5319919A Method for controlling gas turbine combustor 失效
标题翻译：燃气轮机燃烧器的控制方法
公开(公告)号：US5319919A
公开(公告)日：1994-06-14
申请号：US984483
申请日：1992-12-02
申请人： Yoshiharu Nakayama , Isao Sato , Hiraku Ikeda , Michio Kuroda , Nobuyuki Iizuka , Kazuhiko Kumata , Fumiyuki Hirose , Akira Shimura , Minoru Takaba , Shoei Takahashi
发明人： Yoshiharu Nakayama , Isao Sato , Hiraku Ikeda , Michio Kuroda , Nobuyuki Iizuka , Kazuhiko Kumata , Fumiyuki Hirose , Akira Shimura , Minoru Takaba , Shoei Takahashi
IPC分类号： F02C7/26 , F02C9/28 , F23R3/26 , F23R3/28 , F23R3/34
CPC分类号： F23R3/34 , F23R3/26
摘要： A method for controlling a gas turbine combustor which comprises nozzles for injecting fuel into a combustor and which serves to combust the fuel with air in a combustion chamber so as to rotatively drive a gas turbine by combustion gas compressed as a result of combustion of a fuel, wherein the ratio of a flow rate of fuel supplied into the combustor to a flow rate of air supplied into the combustor is changed in accordance with at least one of the states of fuel, air and rotational frequency of the turbine.
摘要翻译：一种用于控制燃气轮机燃烧器的方法，其包括用于将燃料喷射到燃烧器中并且用于使燃料与燃烧室中的空气燃烧的喷嘴，以便由于燃料燃烧而被压缩的燃烧气体旋转地驱动燃气轮机其中，供给燃烧器的燃料的流量与供给燃烧器的空气的流量的比率根据涡轮机的燃料，空气和转速的状态中的至少一种而变化。

3. 发明授权

US5327718A Gas turbine apparatus and method of control thereof 失效
标题翻译：燃气轮机装置及其控制方法
公开(公告)号：US5327718A
公开(公告)日：1994-07-12
申请号：US933317
申请日：1992-08-21
申请人： Naohiko Iwata , Yasuhiko Otawara , Akira Shimura , Nobuyuki Iizuka , Isao Sato , Fumiyuki Hirose , Minoru Takaba , Yasutaka Komatsu , Hiraku Ikeda , Takeshi Iwamiya , Takeshi Ishida
发明人： Naohiko Iwata , Yasuhiko Otawara , Akira Shimura , Nobuyuki Iizuka , Isao Sato , Fumiyuki Hirose , Minoru Takaba , Yasutaka Komatsu , Hiraku Ikeda , Takeshi Iwamiya , Takeshi Ishida
IPC分类号： F02C9/16 , F02C7/228 , F02C9/00 , F02C9/28 , F23C99/00 , F23R3/12 , F23R3/26 , F23R3/28
CPC分类号： F23R3/12 , F02C7/228 , F02C9/28 , F23R3/26
摘要： A gas turbine apparatus has a gas turbine and a plurality of burners for providing combustion gas to drive the turbine. A flow control means of each burner for fuel or combustion air is adjusted by control means to control each said burner individually in dependence on a predetermined combustion characteristic of the respective burner. Sensed quantities relating to the combustion performance of the burners are input to the control means which adjusts the flow control means of each burner in dependence on the sensed quantities and the predetermined combustion characteristic of the respective burner.
摘要翻译：燃气轮机装置具有燃气轮机和用于提供燃烧气体以驱动涡轮机的多个燃烧器。用于燃料或燃烧空气的每个燃烧器的流量控制装置通过控制装置进行调节，以根据相应燃烧器的预定燃烧特性分别控制每个所述燃烧器。与燃烧器的燃烧性能相关的感测量被输入到根据感测量和各个燃烧器的预定燃烧特性来调节每个燃烧器的流量控制装置的控制装置。

4. 发明授权

US5339620A Control apparatus and a control method of a gas turbine combustor 失效
标题翻译：燃气轮机燃烧器的控制装置和控制方法
公开(公告)号：US5339620A
公开(公告)日：1994-08-23
申请号：US872139
申请日：1992-04-22
申请人： Hiraku Ikeda , Tetsuo Sasada , Isao Sato , Yoshikazu Moritomo , Koji Takahashi , Minoru Takaba
发明人： Hiraku Ikeda , Tetsuo Sasada , Isao Sato , Yoshikazu Moritomo , Koji Takahashi , Minoru Takaba
IPC分类号： F02C9/28 , F02C9/50 , F23R3/26
CPC分类号： F23R3/26
摘要： A control apparatus of a gas turbine combustor obtains a stable combustion with limited NOx emission through a control of a fuel flow rate according to a turbine output and a control of a flow rate of intake air mixed with the fuel. The control apparatus includes an apparatus for detecting at least one of the temperature and the humidity of intake air taken into the combustor, an apparatus for determining and storing, in advance, a stable combustion limit line between a stable combustion region and an unstable combustion region, on a plane of coordinates of a ratio of fuel flow rate to an intake air flow rate or an intake air flow rate and the temperature or the humidity of the intake air, on each turbine load, an apparatus for detecting an instant operational point of the combustor on the plane of coordinates, and an apparatus for correcting the intake air flow rate or the ratio of fuel flow rate to the intake air flow rate according to an increase in the detected temperature or humidity so that the instant operational point does not cross the stable combustion limit line.
摘要翻译：燃气轮机燃烧器的控制装置通过根据涡轮机输出控制燃料流量和控制与燃料混合的进气的流量来获得具有有限NOx排放的稳定燃烧。控制装置包括用于检测进入燃烧器的进气的温度和湿度中的至少一个的装置，用于预先确定和存储稳定燃烧区域和不稳定燃烧区域之间的稳定燃烧极限线的装置在每个涡轮机负载上的燃料流量比与进气流量或进气流量之比的坐标平面和进气的温度或湿度之间，检测即时操作点的装置坐标平面上的燃烧器，以及用于根据检测到的温度或湿度的增加来校正进气流量或燃料流量与进气流量比的装置，使得即时操作点不交叉稳定燃烧极限线。

5. 发明授权

US5477670A Control apparatus and a control method of a gas turbine combustor 失效
标题翻译：燃气轮机燃烧器的控制装置和控制方法
公开(公告)号：US5477670A
公开(公告)日：1995-12-26
申请号：US260231
申请日：1994-06-14
申请人： Hiraku Ikeda , Tetsuo Sasada , Isao Sato , Yoshikazu Moritomo , Koji Takahashi , Minoru Takaba
发明人： Hiraku Ikeda , Tetsuo Sasada , Isao Sato , Yoshikazu Moritomo , Koji Takahashi , Minoru Takaba
IPC分类号： F02C9/28 , F02C9/50 , F23R3/26
CPC分类号： F23R3/26
摘要： A control apparatus of a gas turbine combustor for effecting a stable combustion with limited NOx emission through a control of a fuel flow rate according to a turbine output and a control of a flow rate of intake air mixed with the fuel comprises: means for detecting at least one of the temperature and the humidity of an intake air to be taken into the combustor; means for determining and storing, in advance, a stable combustion limit line between a stable combustion region and an unstable combustion region, on a plane of coordinates of a ratio of fuel flow rate/intake air flow rate or an intake air flow rate and the temperature or the humidity of the intake air, on each turbine load; means for detecting an instant operational point of the combustor on the plane of coordinates; and means for correcting an intake air flow rate or a ratio of fuel flow rate to the intake air flow rate according to an increase in the detected temperature or humidity so that the operational point does not cross the stable combustion limit line.
摘要翻译：一种燃气轮机燃烧器的控制装置，用于通过根据涡轮机输出控制燃料流量和控制与燃料混合的进气的流量来实现有限的NOx排放的稳定燃烧，包括：用于在进入燃烧器的进气的温度和湿度中的至少一个; 用于在燃料流量/进气流量或进气流量比的坐标平面上预先确定和存储稳定燃烧区域和不稳定燃烧区域之间的稳定燃烧极限线的装置，以及温度或进气的湿度，在每个涡轮机负载上; 用于在坐标平面上检测燃烧器的即时操作点的装置; 以及用于根据检测到的温度或湿度的增加来校正进气流量或燃料流量与进气流量比的比例的装置，使得操作点不超过稳定燃烧极限线。

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