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1. 发明授权

US06250065B1 Gas turbine combustion system and combustor ignition method therefor 有权
标题翻译：燃气轮机燃烧系统及燃烧器点火方法
公开(公告)号：US06250065B1
公开(公告)日：2001-06-26
申请号：US09292385
申请日：1999-04-15
申请人： Shigemi Mandai , Tetsuo Gora , Koichi Nishida , Masataka Ota , Ichiro Fukue , Shinji Akamatsu , Satoshi Tanimura , Hideki Haruta , Tomohisa Takasaki , Teruya Tachibana
发明人： Shigemi Mandai , Tetsuo Gora , Koichi Nishida , Masataka Ota , Ichiro Fukue , Shinji Akamatsu , Satoshi Tanimura , Hideki Haruta , Tomohisa Takasaki , Teruya Tachibana
IPC分类号： F02B300
CPC分类号： F02C7/232
摘要： Liquid fuel purge device uses water, not compressed air as in the prior art, thereby prevented are rapid load change of gas turbine due to sudden discharge of liquid fuel and coking of remaining liquid fuel. Upon supply of liquid fuel to fuel nozzle (05) being stopped, water purge system (15) having stop valve (16) supplies water into fuel system including liquid fuel system (08) and fuel nozzle (05) and liquid fuel remaining therein is purged by water into combustion chamber (013) from the fuel nozzle (05).
摘要翻译：液体燃料净化装置如现有技术那样使用水而不是压缩空气，由此防止了由于液体燃料的突然排放和剩余的液体燃料的焦化引起的燃气轮机的快速负荷变化。在向燃料喷嘴（05）停止供应液体燃料时，具有截止阀（16）的净水系统（15）将水供应到包括液体燃料系统（08）和燃料喷嘴（05）的燃料系统中，其中残留的液体燃料是从燃料喷嘴（05）通过水从燃烧室（013）中清除。

2. 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。

3. 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.

4. 发明授权

US06282886B1 Gas turbine combustor 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US06282886B1
公开(公告)日：2001-09-04
申请号：US09437146
申请日：1999-11-10
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： F02C300
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.
摘要翻译：在燃烧器20的内管28的中心部分，引导燃料喷嘴22和引导锥体33布置，并且主燃料喷嘴21和主旋流器32在其周围。进气部（X-1）设有用于使进气均匀的整流管11。在进气部分（X-2）中，在内管28的周向壁上设有适当数量的气孔。在主旋流器部分（X-3）和先导锥体部分（X-4）中，使用主旋流器32，并且分别采用对先导式旋流器33的热应力影响较小的优化焊接结构。尾管冷却部（X-5）具有对热应力影响较小的冷却结构，均匀地冷却尾管24的凸缘部71。通过部分（X-1）至（X-5）的改进，燃烧器20中获得较高温度的障碍物被溶解并且燃烧器性能提高。

5. 发明授权

US6158223A Gas turbine combustor 失效
标题翻译：燃气轮机燃烧器
公开(公告)号：US6158223A
公开(公告)日：2000-12-12
申请号：US140011
申请日：1998-08-26
申请人： Shigemi Mandai , Masataka Ota , Satoshi Tanimura , Hideki Haruta
发明人： Shigemi Mandai , Masataka Ota , Satoshi Tanimura , Hideki Haruta
IPC分类号： F23R3/10 , F23D23/00 , F23R3/02 , F23R3/14 , F23R3/20 , F23R3/28 , F23R3/32 , F23R3/54
CPC分类号： F23R3/286 , F23D23/00 , F23R3/02 , F23R3/54
摘要： In gas turbine combustor in which combustion air flows on outer periphery of cylinder body and turns to enter the cylinder body while being mixed with fuel in main burner to form pre-mixture, there is provided upstream of the main burner 101 in the combustor 103 a rectifier 106 or 108 for rectifying the combustion air so as to make flow velocity of the combustion air uniform, thereby shortcomings in the prior art of concentration non-uniformity of the pre-mixture of main fuel and combustion air, high concentration of NO.sub.x generated from the main burner 101 in combustion, etc. are eliminated and larger combustion range to maintain stable combustion is attained.
摘要翻译：在燃气轮机燃烧器中，燃烧空气在气缸本体的外周上流动，并与主燃烧器中的燃料混合而进入气缸本体以形成预混合物，在燃烧器103a中的主燃烧器101的上游用于整流燃烧空气的整流器106或108，以使燃烧空气的流速均匀，从而在主燃料和燃烧空气的预混合物的浓度不均匀性的现有技术中存在缺点，由燃烧时的主燃烧器101等被消除，燃烧范围更大，能够保持稳定的燃烧。

6. 发明授权

US06209326B1 Gas turbine combustor 失效
标题翻译：燃气轮机燃烧器
公开(公告)号：US06209326B1
公开(公告)日：2001-04-03
申请号：US09244030
申请日：1999-02-04
申请人： Shigemi Mandai , Koichi Nishida , Masataka Ota , Tatsuo Ishiguro , Mitsuru Inada , Hideki Haruta
发明人： Shigemi Mandai , Koichi Nishida , Masataka Ota , Tatsuo Ishiguro , Mitsuru Inada , Hideki Haruta
IPC分类号： F02C100
CPC分类号： F23R3/286 , F23C7/004 , F23D14/02 , F23D2205/00 , F23D2206/10 , F23D2900/14021
摘要： To prepare a more homogeneous premixture than that of the device of the prior art thereby to suppress an NOx emission and to lower a fuel feed pressure. A gas turbine combustor comprising: an outer cylinder 106 having main swirlers 101 therein and adapted to be fed with air; and an annular fuel feed manifold 110 disposed at the outer circumference of the outer cylinder 106 on the upstream or downstream side of the main swirlers 101 and having a plurality of nozzle ports 111 communicating with the inside of the outer cylinder 106, so that a fuel is injected from the outer circumference to the center of the air flowing in the outer cylinder 106.
摘要翻译：为了制备比现有技术的装置更均匀的预混合物，从而抑制NOx排放并降低燃料供给压力.1。一种燃气轮机燃烧器，包括：外筒106，其中具有主旋流器101，并适于供给空气; 以及环形燃料供给歧管110，其设置在主旋流器101的上游侧或下游侧的外筒106的外周，并具有与外筒106的内部连通的多个喷嘴口111，从外圆周喷射到在外筒106中流动的空气的中心。

7. 发明授权

US06301900B1 Gas turbine combustor with fuel and air swirler 有权
标题翻译：燃气涡轮燃烧器与燃料和空气旋流器
公开(公告)号：US06301900B1
公开(公告)日：2001-10-16
申请号：US09554447
申请日：2000-07-06
申请人： Shigemi Mandai , Masataka Ohta , Hideki Haruta , Koichi Nishida , Shinji Akamatsu , Masahiro Kamogawa
发明人： Shigemi Mandai , Masataka Ohta , Hideki Haruta , Koichi Nishida , Shinji Akamatsu , Masahiro Kamogawa
IPC分类号： F23R314
CPC分类号： F23D11/38 , F23D11/107 , F23D2900/00016 , F23R3/28
摘要： A nozzle cap (10) is disposed downstream of a nozzle body (1) of a combustor for a gas turbine, an inner surface part (12) of which is of a conical shape diverging downstream to define a fuel-jet guide (17) for guiding fuel jet ejected from one or more nozzle holes (3) provided at the center of a downstream end surface of the nozzle body. Fuel ejected from the one or more nozzle holes smoothly runs along the fuel-jet guide without remaining there to join with a swirl stream (S) in a swirl path (9), and to burn without generating smoke. Air introduced into a first auxiliary air path (6) defined between the nozzle body and a partition (5) at a position upstream thereof passes through a second auxiliary air path (16) defined between a downstream end surface (2) of the nozzle body (1) and an upstream end surface (13) of the nozzle cap and reaches an entrance (19) of the fuel-jet guide. The air then flows along the fuel-jet guide to cool the nozzle cap and prevent the fuel ejected from the one or more nozzle holes from sticking to the nozzle cap.
摘要翻译：喷嘴盖（10）设置在用于燃气轮机的燃烧器的喷嘴主体（1）的下游，其内表面部分（12）具有向下游扩散的锥形形状，以限定燃料喷射引导件（17）用于引导从设置在喷嘴体的下游端面的中心的一个或多个喷嘴孔（3）喷出的燃料喷射。从一个或多个喷嘴孔喷出的燃料沿燃料喷射导向装置平滑地延伸，而不残留在漩涡路径（9）中的旋流（S），并且燃烧而不产生烟雾。被引入第一辅助空气通道（6）中的空气通道（6），其限定在喷嘴主体和分隔件（5）之间的位于其上游的位置处，通过限定在喷嘴体的下游端面（2）之间的第二辅助空气通道（1）和喷嘴盖的上游端表面（13）到达燃料喷射引导件的入口（19）。然后空气沿着燃料喷射引导件流动以冷却喷嘴帽，并且防止从一个或多个喷嘴孔喷出的燃料粘附到喷嘴帽。

8. 发明申请

US20120180490A1 FUEL NOZZLE, GAS TURBINE COMBUSTOR WITH THE SAME, AND GAS TURBINE WITH THE SAME 有权
标题翻译：燃油喷嘴，带有相同气体的燃气轮机，以及与之相同的燃气涡轮
公开(公告)号：US20120180490A1
公开(公告)日：2012-07-19
申请号：US13216966
申请日：2011-08-24
申请人： Eiji Takami , Katsunori Tanaka , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Tomo Kawakami , Kei Inoue
发明人： Eiji Takami , Katsunori Tanaka , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Tomo Kawakami , Kei Inoue
IPC分类号： F23R3/28 , B05B15/00
CPC分类号： F23R3/14 , F23R3/28 , F23R3/283 , F23R3/36 , F23R2900/03044
摘要： A fuel nozzle for a gas turbine combustor includes: an internal cylinder; a burner cylinder concentrically provided on the outer circumference of the internal cylinder in the vicinity of its distal end to surround the distal end portion of the internal cylinder; an air passage provided between the burner cylinder and the internal cylinder for delivering combustion air; a space provided at an axial center of the internal cylinder and extending in the axial direction of the internal cylinder; a plurality of inner passages provided at approximately equal intervals in the circumferential direction of the internal cylinder for injecting fluid through its distal end portion; and at least one communication portion provided on the upstream side of the distal end portion of the internal cylinder and extending from the outer wall of the internal cylinder toward the inner side in the radial direction to communicate with the space.
摘要翻译：一种用于燃气轮机燃烧器的燃料喷嘴，包括：内筒; 燃烧器筒同心地设置在内圆筒的远端附近的外周上，以包围内筒的前端部; 设置在燃烧器筒和内筒之间用于输送燃烧空气的空气通道; 设置在所述内筒的轴心且在所述内筒的轴向延伸的空间; 多个内通道，其在所述内筒的圆周方向上以相等的间隔设置，用于通过其前端部分喷射流体; 以及至少一个连通部，其设置在所述内筒的前端部的上游侧，并且从所述内筒的外壁向径向内侧延伸，与所述空间连通。

9. 发明授权

US09062885B2 Fuel nozzle, gas turbine combustor with the same, and gas turbine with the same 有权
标题翻译：燃油喷嘴，燃气轮机与燃气轮机相同，与燃气轮机相同
公开(公告)号：US09062885B2
公开(公告)日：2015-06-23
申请号：US13216966
申请日：2011-08-24
申请人： Eiji Takami , Katsunori Tanaka , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Tomo Kawakami , Kei Inoue
发明人： Eiji Takami , Katsunori Tanaka , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Tomo Kawakami , Kei Inoue
IPC分类号： F23R3/28 , B05B15/00 , F23R3/14 , F23R3/36
CPC分类号： F23R3/14 , F23R3/28 , F23R3/283 , F23R3/36 , F23R2900/03044
摘要： A fuel nozzle for a gas turbine combustor includes: an internal cylinder; a burner cylinder concentrically provided on the outer circumference of the internal cylinder in the vicinity of its distal end to surround the distal end portion of the internal cylinder; an air passage provided between the burner cylinder and the internal cylinder for delivering combustion air; a space provided at an axial center of the internal cylinder and extending in the axial direction of the internal cylinder; a plurality of inner passages provided at approximately equal intervals in the circumferential direction of the internal cylinder for injecting fluid through its distal end portion; and at least one communication portion provided on the upstream side of the distal end portion of the internal cylinder and extending from the outer wall of the internal cylinder toward the inner side in the radial direction to communicate with the space.
摘要翻译：一种用于燃气轮机燃烧器的燃料喷嘴，包括：内筒; 燃烧器筒同心地设置在内圆筒的远端附近的外周上，以包围内筒的前端部; 设置在燃烧器筒和内筒之间用于输送燃烧空气的空气通道; 设置在所述内筒的轴心且在所述内筒的轴向延伸的空间; 多个内通道，其在所述内筒的圆周方向上以相等的间隔设置，用于通过其前端部分喷射流体; 以及至少一个连通部，其设置在所述内筒的前端部的上游侧，并且从所述内筒的外壁向径向内侧延伸，与所述空间连通。

10. 发明授权

US06324829B1 Steam cooled system in combined cycle power plant 有权
标题翻译：联合循环发电厂蒸汽冷却系统
公开(公告)号：US06324829B1
公开(公告)日：2001-12-04
申请号：US09237845
申请日：1999-01-27
申请人： Yoshiyuki Kita , Tomoka Tanaka , Yasuhiro Hashimoto , Masayuki Takahama , Jun Yasuraoka , Hidetoshi Iida , Koichi Akagi , Hideki Haruta
发明人： Yoshiyuki Kita , Tomoka Tanaka , Yasuhiro Hashimoto , Masayuki Takahama , Jun Yasuraoka , Hidetoshi Iida , Koichi Akagi , Hideki Haruta
IPC分类号： F02C600
CPC分类号： F01K23/108 , Y02E20/16 , Y02P80/152
摘要： A gas turbine steam cooled system has a high temperature portion 8 outlet steam temperature maintained to a predetermined value without a cooling steam pressure becoming lower than the pressure in the gas turbine cylinder. Steam coming from an intermediate pressure superheater 10 of a waste heat recovery boiler 2 is led into the high temperature portion 8 of the gas turbine for cooling thereof. The temperature of the cooling steam at the outlet of the high temperature portion 8 is detected by a high temperature portion outlet steam temperature detector 15, and a signal thereof is sent a lower value selector 19 via a temperature controller 11. Pressure in the gas turbine cylinder is detected by a gas turbine cylinder pressure detector 17, and pressure of the cooling steam at the high temperature portion 8 outlet is detected by a high temperature portion outlet steam pressure detector 16. A differential signal thereof is sent to a pressure controller 18. Signals from the temperature controller 11 and the pressure controller 18 are inputted into the lower selector 19, and temperature control valve 12 is controlled by the lower value thereof to be opened and closed.
摘要翻译：燃气轮机蒸汽冷却系统具有保持预定值的高温部分8出口蒸汽温度，而冷却蒸汽压力变得低于燃气轮机气缸中的压力。来自废热回收锅炉2的中压过热器10的蒸汽被引入燃气轮机的高温部8，以进行冷却。高温部分8出口处的冷却蒸汽的温度由高温部分出口蒸气温度检测器15检测，其信号通过温度控制器11送到低值选择器19.燃气轮机中的压力气缸由燃气轮机气缸压力检测器17检测，高温部分8出口处的冷却蒸汽的压力由高温部分出口蒸汽压力检测器16检测。其差分信号被发送到压力控制器18。来自温度控制器11和压力控制器18的信号被输入到下部选择器19中，并且温度控制阀12被其较低的值控制为打开和关闭。

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