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1. 发明授权

US08904794B2 Gas turbine having a combustion oscillation suppressing device 有权
标题翻译：具有燃烧振动抑制装置的燃气轮机
公开(公告)号：US08904794B2
公开(公告)日：2014-12-09
申请号：US12671046
申请日：2008-10-17
申请人： Keisuke Matsuyama , Kotaro Miyauchi
发明人： Keisuke Matsuyama , Kotaro Miyauchi
IPC分类号： F02C7/24 , F01D9/02 , F23R3/00
CPC分类号： F02C7/24 , F01D9/023 , F05D2260/96 , F05D2260/963 , F23M20/005 , F23R3/00 , F23R2900/00014
摘要： A gas turbine including a combustion oscillation suppressing device disposed to a transition piece of a combustor to define a gas space S, and having a plurality of vent holes through which a gas space L and the inside of the transition piece communicate. The combustion oscillation suppressing device is formed of a first member and a second member which define the gas space, the second member having the plurality of vent holes, and a portion of a transition piece wall includes the second member. A distance from the second member to the first member in the radial direction of the transition piece is a height of the gas space, and when the height of the gas space varies along an axial direction of the transition piece, an opening ratio σp of each of the plurality of vent holes is adjusted depending on the height of the gas space.
摘要翻译：一种燃气轮机，包括设置在燃烧器的过渡件上以限定气体空间S的燃烧振荡抑制装置，并且具有多个通气孔，气体空间L和过渡件的内部通过该通气孔连通。燃烧振动抑制装置由限定气体空间的第一构件和第二构件形成，具有多个通气孔的第二构件和过渡件壁的一部分包括第二构件。在过渡件的径向方向上从第二构件到第一构件的距离是气体空间的高度，并且当气体空间的高度沿着过渡件的轴向方向变化时，开口率＆sgr 根据气体空间的高度来调节多个通气孔中的每一个。

2. 发明申请

US20100186411A1 GAS TURBINE 有权
标题翻译：燃气轮机
公开(公告)号：US20100186411A1
公开(公告)日：2010-07-29
申请号：US12671046
申请日：2008-10-17
申请人： Keisuke Matsuyama , Kotaro Miyauchi
发明人： Keisuke Matsuyama , Kotaro Miyauchi
IPC分类号： F02C7/24
CPC分类号： F02C7/24 , F01D9/023 , F05D2260/96 , F05D2260/963 , F23M20/005 , F23R3/00 , F23R2900/00014
摘要： An object of the present invention is to provide a gas turbine that improves appearance of a combustion oscillation suppressing device disposed to a transition piece of a combustor. To achieve the object, a combustion oscillation suppressing device 34 is disposed to a transition piece 32 of a combustor to define a gas space S, and has a plurality of vent holes 343 through which a gas space L and the inside of the transition piece 32 communicate with each other. The combustion oscillation suppressing device 34 has: a first member 341 that has a substantially U-shaped cross-section formed by press-working, and is disposed on the outer circumference of the transition piece 32 with a substantially U-shaped cross-section opening thereof facing the transition piece 32; and a second member 342 that defines the gas space S between the first member 341 and the second member 342 by blocking the substantially U-shaped cross-section opening of the first member 341, and has the vent holes 343. In a radial-direction cross section of the transition piece 32, when the outer diameter of the transition piece 32 varies along an axial direction of the transition piece 32, distances d1 and d2 from the axis L of the transition piece 32 to each bent portion of the first member 341 having a substantially U-shaped cross-section are set to be substantially equal.
摘要翻译：本发明的目的在于提供一种能够改善设置在燃烧器的过渡件上的燃烧振动抑制装置的外观的燃气轮机。为了实现该目的，燃烧振动抑制装置34设置在燃烧器的过渡件32上以形成气体空间S，并且具有多个通气孔343，气体空间L和过渡件32的内部相互沟通。燃烧振动抑制装置34具有：第一构件341，其具有通过加压加工形成的大致U字形的截面，并且设置在过渡件32的外周上，具有大致U形的横截面开口面向过渡件32; 以及第二构件342，其通过阻挡第一构件341的大致U形的横截面开口限定第一构件341和第二构件342之间的气体空间S，并且具有通气孔343。当过渡件32的外径沿着过渡件32的轴向方向变化时，过渡件32的横截面为从过渡件32的轴线L到第一件341的每个弯曲部分的距离d1和d2 具有基本上U形的横截面被设定为基本相等。

3. 发明授权

US08813502B2 Cooling structure of gas turbine combustor 有权
标题翻译：燃气轮机燃烧器的冷却结构
公开(公告)号：US08813502B2
公开(公告)日：2014-08-26
申请号：US12598100
申请日：2008-09-24
申请人： Tatsuo Ishiguro , Katsunori Tanaka , Kotaro Miyauchi
发明人： Tatsuo Ishiguro , Katsunori Tanaka , Kotaro Miyauchi
IPC分类号： F02C1/08 , F02G1/055 , F02C7/12 , F23R3/28 , F23R3/00 , F23R3/06
CPC分类号： F23R3/283 , F23R3/005 , F23R3/06 , F23R2900/03042 , F23R2900/03044
摘要： It is required for a gas turbine combustor to exhaust low NOx. The gas turbine combustor is provided with a combustion tube which has a cooling passage through which cooling air flows in a double wall structure. The cooling passage has a main cooling air supply opening opened to a side of a combustion zone. The cooling air supplied from the main cooling air supply opening is guided to a direction along an inner wall surface of the combustion tube by a guide. The cooling air flows through the cooling passage inside the combustion tube, and then is reused for film cooling along the inner wall surface. Thus, it is possible to save cooling air. Therefore, a more part of the air supplied from a compressor can be used as air for combustion and it becomes possible to exhaust low NOx.
摘要翻译：燃气轮机燃烧器需要排出低NOx。燃气轮机燃烧器设置有燃烧管，该燃烧管具有冷却空气以双壁结构流动的冷却通道。冷却通道具有向燃烧区侧面敞开的主冷却空气供给口。从主冷却空气供给口供给的冷却空气通过引导件被引导到燃烧管的内壁面的方向。冷却空气流过燃烧管内的冷却通道，然后再次用于沿内壁表面进行膜冷却。因此，可以节省冷却空气。因此，从压缩机供给的空气的一部分能够用作燃烧用空气，能够排出低NOx。

4. 发明授权

US08490379B2 Gas turbine control device 有权
标题翻译：燃气轮机控制装置
公开(公告)号：US08490379B2
公开(公告)日：2013-07-23
申请号：US12933963
申请日：2009-04-10
申请人： Masumi Nomura , Kozo Toyama , Tomo Kawakami , Kotaro Miyauchi , Kuniharu Fujibayashi
发明人： Masumi Nomura , Kozo Toyama , Tomo Kawakami , Kotaro Miyauchi , Kuniharu Fujibayashi
IPC分类号： F02C9/00
CPC分类号： F02C9/18 , F01D17/04 , F01D17/085 , F02C9/22 , F02C9/28 , F02C9/52 , F02C9/54 , F05D2270/053 , F05D2270/082 , F05D2270/14 , F05D2270/303 , F23N1/022 , F23N5/022 , F23N2021/10 , F23N2023/42 , F23N2025/13 , F23N2037/20 , F23N2041/20 , F23R2900/00013
摘要： A gas turbine controller having a first generator for setting the flow rate of fuel or air being supplied to a combustor in correspondence with a target load, a sensor for detecting intake temperature of a compressor, a second generator for setting a correction amount of a set value of fuel flow rate or air flow rate based on the value detected by the sensor, a third generator for setting a modification amount of the correction amount while taking account of the target load, a first multiplier for operating a modified correction amount from a correction amount set by the second generator and a modification amount set by the third generator, and a second multiplier for calculating the flow rate of fuel or air being supplied to a combustor by adding the modified correction amount to the set value of fuel flow rate or air flow rate.
摘要翻译：一种燃气轮机控制器，具有第一发电机，用于将燃料或空气的流量设定为与目标负荷相对应的燃烧器，用于检测压缩机的进气温度的传感器，用于设定压缩机的校正量的第二发电机基于由传感器检测的值的燃料流量或空气流量的值，用于在考虑目标负载的同时设定修正量的修正量的第三发生器，用于从校正操作修正校正量的第一乘法器由第二发生器设定的量和由第三发生器设定的修正量;以及第二乘法器，用于通过将修正校正量与燃料流量或空气的设定值相加来计算供给燃烧器的燃料或空气的流量流量。

5. 发明申请

US20100180601A1 COOLING STRUCTURE OF GAS TURBINE COMBUSTOR 有权
标题翻译：燃气轮机组的冷却结构
公开(公告)号：US20100180601A1
公开(公告)日：2010-07-22
申请号：US12598100
申请日：2008-09-24
申请人： Tatsuo Ishiguro , Katsunori Tanaka , Kotaro Miyauchi
发明人： Tatsuo Ishiguro , Katsunori Tanaka , Kotaro Miyauchi
IPC分类号： F02C3/14
CPC分类号： F23R3/283 , F23R3/005 , F23R3/06 , F23R2900/03042 , F23R2900/03044
摘要： It is required for a gas turbine combustor to exhaust low NOx. The gas turbine combustor is provided with a combustion tube which has a cooling passage through which cooling air flows in a double wall structure. The cooling passage has a main cooling air supply opening opened to a side of a combustion zone. The cooling air supplied from the main cooling air supply opening is guided to a direction along an inner wall surface of the combustion tube by a guide. The cooling air flows through the cooling passage inside the combustion tube, and then is reused for film cooling along the inner wall surface. Thus, it is possible to save cooling air. Therefore, a more part of the air supplied from a compressor can be used as air for combustion and it becomes possible to exhaust low NOx.
摘要翻译：燃气轮机燃烧器需要排出低NOx。燃气轮机燃烧器设置有燃烧管，该燃烧管具有冷却空气以双壁结构流动的冷却通道。冷却通道具有向燃烧区侧面敞开的主冷却空气供给口。从主冷却空气供给口供给的冷却空气通过引导件被引导到燃烧管的内壁面的方向。冷却空气流过燃烧管内的冷却通道，然后再次用于沿内壁表面进行膜冷却。因此，可以节省冷却空气。因此，从压缩机供给的空气的一部分能够用作燃烧用空气，能够排出低NOx。

6. 发明授权

US6068467A Combustor 有权
标题翻译：燃烧器
公开(公告)号：US6068467A
公开(公告)日：2000-05-30
申请号：US244031
申请日：1999-02-04
申请人： Shigemi Mandai , Koichi Nishida , Masataka Ota , Satoshi Tanimura , Kotaro Miyauchi , Mitsuru Inada , Shinji Akamatsu , Hideki Haruta
发明人： Shigemi Mandai , Koichi Nishida , Masataka Ota , Satoshi Tanimura , Kotaro Miyauchi , Mitsuru Inada , Shinji Akamatsu , Hideki Haruta
IPC分类号： F23D14/02 , F23D23/00 , F23C5/00
CPC分类号： F23D23/00 , F23D14/02 , F23D2206/10 , F23D2209/10 , F23D2900/14021
摘要： A combustor has a pilot nozzle 02 arranged at a central portion of an inner cylinder 01 opening at its end into a combustion chamber 018 and includes a plurality of main nozzles 03 arranged around its outer circumference. Along the outer circumference of a flame holding cone 014 for igniting a fuel F injected from the main nozzles 03 there are disposed elliptical extension pipes 016 of an elliptical sectional shape which are extended from the fronts of the main nozzles 03 to have openings at the axial position of the opening of the flame holding cone 014. As a result, a hot premixed flame 013 does not flow back to a main swirler zone 015 of the circumferential edges of the openings of the main nozzles 03 so that mixing between the fuel F and an air flow A can be improved, reducing the Nox emission while eliminating the burning of a base plate 04 and the main nozzles 03.
摘要翻译：燃烧器具有引导喷嘴02，其设置在内筒01的中心部分处，内筒01在其端部处开放到燃烧室018中，并且包括围绕其外圆周布置的多个主喷嘴03。沿着用于点燃从主喷嘴03喷射的燃料F的火焰保持锥体014的外圆周，设置椭圆形截面形状的椭圆形延伸管016，其从主喷嘴03的前面延伸，以在轴向上具有开口火焰保持锥体014的开口的位置。结果，热预混火焰013不流回到主喷嘴03的开口的周缘的主旋流器区域015，使得燃料F和可以改善空气流A，减少Nox排放，同时消除基板04和主喷嘴03的燃烧。

7. 发明授权

US08701420B2 Gas turbine control method and device 有权
标题翻译：燃气轮机控制方法及装置
公开(公告)号：US08701420B2
公开(公告)日：2014-04-22
申请号：US12673932
申请日：2009-02-23
申请人： Masumi Nomura , Kotaro Miyauchi
发明人： Masumi Nomura , Kotaro Miyauchi
IPC分类号： F02C9/52 , F02C9/00
CPC分类号： F02C9/52 , F02C9/28 , F02C9/54 , F05D2270/114 , F05D2270/14 , F05D2270/301 , F05D2270/3061 , F05D2270/332 , F05D2270/334
摘要： A gas turbine control device having a gas turbine control unit for the gas turbine operation control that computes adjustment increments regarding at least one of the airflow rate into the combustor and the pilot ratio, and makes revisions to the actuating variables comprising the airflow rate and the pilot ratio so that the actuating variables are contrasted with the status signals and the variables are modified toward initial design conditions. The gas turbine control unit resets the revisions made to the actuating variables in a case where the level of the combustion vibration is restrained below the predetermined control criterion for a predetermined time span, and the gas turbine is operated under the control settings of the initial design stage.
摘要翻译：一种燃气轮机控制装置，具有用于燃气轮机运行控制的燃气轮机控制单元，该燃气轮机控制单元计算关于进入燃烧器的气流率和导频比中的至少一个的调节增量，并且对包括气流速率和导频比，使得致动变量与状态信号形成对比，并且将变量修改为初始设计条件。燃气轮机控制单元将在燃烧振动的水平被抑制在预定控制标准下达预定时间间隔的情况下复位对致动变量的修正，并且燃气轮机在初始设计的控制设置下操作阶段。

8. 发明申请

US20100199680A1 GAS TURBINE CONTROL METHOD AND DEVICE 有权
标题翻译：气体涡轮机控制方法和装置
公开(公告)号：US20100199680A1
公开(公告)日：2010-08-12
申请号：US12673932
申请日：2009-02-23
申请人： Masumi Nomura , Kotaro Miyauchi
发明人： Masumi Nomura , Kotaro Miyauchi
IPC分类号： F02C9/50
CPC分类号： F02C9/52 , F02C9/28 , F02C9/54 , F05D2270/114 , F05D2270/14 , F05D2270/301 , F05D2270/3061 , F05D2270/332 , F05D2270/334
摘要： A gas turbine control method for preventing then operation from deviating from the operating state at the ideal fuel and air flow-rates expected when the gas turbine is designed and maintaining an efficient operating state. A gas turbine control device comprises a frequency analyzing means for analyzing the frequencies inside the combustor of a gas turbine, a state grasping means for grasping the combustion state in the gas turbine on the basis of a state signal representing the result of the analysis by frequency band, the amount of operation process including a ratio between the air flow rate and pilot fuel in the gas turbine, the atmosphere state, and the load amount, a combustion characteristic grasping means for grasping the characteristic of the combustion vibration, and a control section for calculating a correction value of at least either the air flow rate supplied to the combustor or the pilot ratio from the grasped combustion vibration characteristic and the grasped combustion state each time the degree of the combustion vibration exceeds a predetermined control value, correcting the initial design values of the air flow rate and the pilot ratio predetermined correspondingly to the amount of operation process and the state signal, and thereby driving the gas turbine. The control section resets the correction of the initial design values when the degree of combustion vibration of the gas turbine is below the predetermined control value for a given period of time and operates the gas turbine using the initial design values.
摘要翻译：一种燃气轮机控制方法，用于防止在设计燃气涡轮机时期望的理想燃料和空气流速下操作偏离操作状态并保持有效的操作状态。燃气轮机控制装置包括：频率分析装置，用于分析燃气轮机的燃烧器内部的频率;状态把持装置，用于根据表示分析结果的状态信号按照频率来获取燃气轮机中的燃烧状态包括燃气轮机中的空气流量与先导燃料之间的比例，气氛状态和负载量的运转处理量，用于掌握燃烧振动特性的燃烧特性获取装置，以及控制部每当燃烧振动的程度超过预定的控制值时，根据所掌握的燃烧振动特性和所掌握的燃烧状态来计算至少提供给燃烧器的空气流量或者先导比的校正值，校正初始设计对应于操作量的空气流量和导频比的值从而驱动燃气轮机。当燃气轮机的燃烧振动程度低于预定控制值一段给定的时间段时，控制部分复位初始设计值的校正，并且使用初始设计值来操作燃气轮机。

9. 发明申请

US20110056180A1 GAS TURBINE CONTROL DEVICE 有权
标题翻译：气体涡轮控制装置
公开(公告)号：US20110056180A1
公开(公告)日：2011-03-10
申请号：US12933963
申请日：2009-04-10
申请人： Masumi Nomura , Kozo Toyama , Tomo Kawakami , Kotaro Miyauchi , Kuniharu Fujibayashi
发明人： Masumi Nomura , Kozo Toyama , Tomo Kawakami , Kotaro Miyauchi , Kuniharu Fujibayashi
IPC分类号： F02C9/00
CPC分类号： F02C9/18 , F01D17/04 , F01D17/085 , F02C9/22 , F02C9/28 , F02C9/52 , F02C9/54 , F05D2270/053 , F05D2270/082 , F05D2270/14 , F05D2270/303 , F23N1/022 , F23N5/022 , F23N2021/10 , F23N2023/42 , F23N2025/13 , F23N2037/20 , F23N2041/20 , F23R2900/00013
摘要： Occurrence of combustion vibration is prevented in a gas turbine plant by enhancing the degree of freedom in setting an airflow rate or a fuel flow rate in correspondence with a target load thereby enhancing combustion stability. A gas turbine controller comprises a first function generator (62) for setting the flow rate of fuel or air being supplied to a combustor (32) in correspondence with a target load, an suction air temperature sensor (22) for detecting intake temperature at the inlet of a compressor, a second function generator (69) for setting a correction amount of a set value of fuel flow rate or air flow rate based on the value detected by the suction air temperature sensor (22), a third function generator (66) for setting a modification amount of the correction amount while taking account of the target load, a first multiplier (68); for operating a modified correction amount from a correction amount set by the second function generator and a modification amount set by the third function generator, and a second multiplier (64) for calculating the flow rate of fuel or air being supplied to a combustor by adding the modified correction amount to the set value of fuel flow rate or air flow rate set by the first function generator.
摘要翻译：通过提高与目标负荷相对应地设定气流速度或燃料流量的自由度，从而提高燃烧稳定性，可以防止燃气轮机厂的燃烧振动的发生。一种燃气轮机控制器包括：第一功能发生器（62），用于根据目标负载设定供给到燃烧器（32）的燃料或空气的流量;吸入空气温度传感器（22），用于检测第二功能发生器（69），用于基于由吸入空气温度传感器（22）检测的值来设定燃料流量或空气流量的设定值的校正量，第三功能发生器（66）），用于在考虑目标负载的同时设定修正量的修正量，第一乘法器（68）; 用于从由第二函数发生器设定的校正量和由第三函数发生器设置的修正量操作修正校正量;以及第二乘法器（64），用于计算通过添加向燃烧器供应的燃料或空气的流量将修正校正量设定为由第一函数发生器设定的燃料流量或空气流量的设定值。

10. 发明授权

US06327861B2 Gas turbine combustor 失效
公开(公告)号：US06327861B2
公开(公告)日：2001-12-11
申请号：US09862468
申请日：2001-05-23
申请人： Yoshichika Sato , Yoji Kochi , Koichi Akagi , Kazuya Kobayashi , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Kotaro Miyauchi , Rintaro Chikami , Shigemi Mandai , Masataka Ota
发明人： Yoshichika Sato , Yoji Kochi , Koichi Akagi , Kazuya Kobayashi , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Kotaro Miyauchi , Rintaro Chikami , Shigemi Mandai , Masataka Ota
IPC分类号： F02C100
CPC分类号： F23L7/00 , F23C9/00 , F23D2900/00008 , F23L2900/07002 , F23R3/005 , F23R3/14 , F23R3/343 , F23R3/60
摘要： In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.

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