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1. 发明授权

US6105372A Gas turbine combustor 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US6105372A
公开(公告)日：2000-08-22
申请号：US145499
申请日：1998-09-02
申请人： Shigemi Mandai , Masataka Ota , Katsunori Tanaka , Shinji Akamatsu
发明人： Shigemi Mandai , Masataka Ota , Katsunori Tanaka , Shinji Akamatsu
IPC分类号： F02C7/18 , F23R3/10 , F23R3/42 , F02C1/00
CPC分类号： F23R3/10 , F05B2260/202
摘要： A gas turbine combustor having a combustion chamber (10) with a steam-cooled peripheral wall (2) has an air hole (1) for injecting dilution air therethrough bored in the peripheral wall (2) on an upstream side of the combustion chamber (10). The air is thereby supplied through the air hole (1) into the vicinity of an inner surface of the peripheral wall (2) to form a film flow of air, and an increase of the fuel concentration there is suppressed. The dilution air is preferably supplied from a gas turbine compressor (6).
摘要翻译：具有具有蒸汽冷却周边壁（2）的燃烧室（10）的燃气轮机燃烧器具有用于在燃烧室的上游侧的周壁（2）中喷射稀释空气的空气孔（1） 10）。因此，空气通过空气孔（1）供给到周壁（2）的内表面附近，形成空气的膜流，抑制了燃料浓度的增加。稀释空气优选地从燃气涡轮压缩机（6）供给。

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

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。

6. 发明授权

US07694521B2 Installation structure of pilot nozzle of combustor 有权
标题翻译：燃烧器引燃喷嘴安装结构
公开(公告)号：US07694521B2
公开(公告)日：2010-04-13
申请号：US10561927
申请日：2004-03-03
申请人： Masataka Ohta , Shigemi Mandai , Kuniaki Aoyama , Katsunori Tanaka , Shinji Akamatsu , Hisanari Nakajima , Teruya Tachibana , Koichi Nishida , Wataru Akizuki , Yoshikuni Kasai , Jyunji Hashimura
发明人： Masataka Ohta , Shigemi Mandai , Kuniaki Aoyama , Katsunori Tanaka , Shinji Akamatsu , Hisanari Nakajima , Teruya Tachibana , Koichi Nishida , Wataru Akizuki , Yoshikuni Kasai , Jyunji Hashimura
IPC分类号： F02C1/00
CPC分类号： F23R3/343 , F23D2900/00015 , F23R3/286
摘要： Pilot fuel injected from fuel injection ports 21 of a pilot nozzle 2 bumps against an inner wall surface of a tapered portion of an inner circumference of a cone 41 of a pilot cone 4. At this time, the position where a pilot fuel from the fuel injection ports 21 hits is located in a range from a middle of the tapered portion of the inner circumference of a cone 41 to a downstream-side tip thereof.
摘要翻译：从先导喷嘴2的燃料喷射口21喷射的先导燃料抵靠导向锥4的锥体41的内周的锥形部的内壁面。此时，来自燃料的导向燃料的位置喷射口21打击位于从锥体41的内圆周的锥形部分的中部到其下游侧的顶端的范围内。

7. 发明申请

US20070006587A1 Combustor 有权
标题翻译：燃烧器
公开(公告)号：US20070006587A1
公开(公告)日：2007-01-11
申请号：US10561927
申请日：2004-03-03
申请人： Masataka Ohta , Shigemi Mandai , Kuniaki Aoyama , Katsunori Tanaka , Shinji Akamatsu , Hisanari Nakajima , Teruya Tachibana , Koichi Nishida , Wataru Akizuki , Yoshikumi Kasai , Jyunji Hashimura
发明人： Masataka Ohta , Shigemi Mandai , Kuniaki Aoyama , Katsunori Tanaka , Shinji Akamatsu , Hisanari Nakajima , Teruya Tachibana , Koichi Nishida , Wataru Akizuki , Yoshikumi Kasai , Jyunji Hashimura
IPC分类号： F23R3/30
CPC分类号： F23R3/343 , F23D2900/00015 , F23R3/286
摘要： Pilot fuel being injected from fuel injection ports 21 of a pilot nozzle 2 bumps against an inner wall surface of the tapered portion of the inner circumference of a cone 41 of a pilot cone 4. At this time, the position where the pilot fuel from the fuel injection ports 21 hits is located in the range from the middle of the tapered portion of the inner circumference of a cone 41 to the downstream-side tip thereof.
摘要翻译：先导喷嘴2的燃料喷射口21喷射的先导燃料抵靠导向锥4的锥体41的内周的锥形部的内壁面。此时，来自燃料喷射口21的先导燃料的位置位于从锥体41的内周的锥形部的中部到下游侧的前端的范围内。

8. 发明申请

US20120125006A1 GAS TURBINE COMBUSTOR AND GAS TURBINE 有权
标题翻译：气体涡轮机和气体涡轮机
公开(公告)号：US20120125006A1
公开(公告)日：2012-05-24
申请号：US13388204
申请日：2010-11-05
申请人： Keijiro Saito , Shinji Akamatsu , Kenji Sato , Shigemi Mandai
发明人： Keijiro Saito , Shinji Akamatsu , Kenji Sato , Shigemi Mandai
IPC分类号： F23R3/16 , F23R3/54 , F23R3/10
CPC分类号： F23R3/06 , F02C7/18 , F23R3/16 , F23R3/42 , F23R3/46 , F23R2900/03045
摘要： In a gas turbine combustor and a gas turbine, an air passage (54) that supplies combustion high-pressure air, a pilot nozzle (44), a main fuel nozzle (45), and a top hat nozzle (47) that supply fuel, and openings (64) that supply film air (cooling air) are provided with respect to a combustor inner cylinder (42), and contraction members (71, 72, and 73) are arranged along a circumferential direction on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder (42). The contraction members (71, 72, and 73) are provided in a predetermined area in the circumferential direction excluding penetrating portions (74, 75, and 76), which do not disturb the flow of cooling air, thereby enabling to suppress generation of carbon monoxide and the like and to suppress the occurrence of unstable combustion.
摘要翻译：在燃气轮机燃烧器和燃气轮机中，提供燃烧高压空气的空气通道（54），提供燃料的先导喷嘴（44），主燃料喷嘴（45）和顶帽喷嘴（47），并且相对于燃烧器内筒（42）设置供给膜空气（冷却空气）的开口部（64），在内壁面上沿着圆周方向配置收缩部件（71,72,73）在内筒（42）中的燃烧气体的流动方向的下游。收缩构件（71,72和73）设置在不妨碍冷却空气流动的穿透部（74,75,76）的周向的规定区域中，能够抑制碳的产生一氧化物等，并抑制不稳定燃烧的发生。

9. 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。

10. 发明授权

US08950190B2 Gas turbine combustor having contraction member on inner wall surface 有权
标题翻译：燃气轮机燃烧器在内壁表面具有收缩构件
公开(公告)号：US08950190B2
公开(公告)日：2015-02-10
申请号：US13388204
申请日：2010-11-05
申请人： Keijiro Saito , Shinji Akamatsu , Kenji Sato , Shigemi Mandai
发明人： Keijiro Saito , Shinji Akamatsu , Kenji Sato , Shigemi Mandai
IPC分类号： F23R3/06 , F23R3/46 , F23R3/16 , F23R3/42 , F02C7/18
CPC分类号： F23R3/06 , F02C7/18 , F23R3/16 , F23R3/42 , F23R3/46 , F23R2900/03045
摘要： In a gas turbine combustor and a gas turbine, an air passage (54) that supplies combustion high-pressure air, a pilot nozzle (44), a main fuel nozzle (45), and a top hat nozzle (47) that supply fuel, and openings (64) that supply film air (cooling air) are provided with respect to a combustor inner cylinder (42), and contraction members (71, 72, and 73) are arranged along a circumferential direction on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder (42). The contraction members (71, 72, and 73) are provided in a predetermined area in the circumferential direction excluding penetrating portions (74, 75, and 76), which do not disturb the flow of cooling air, thereby enabling to suppress generation of carbon monoxide and the like and to suppress the occurrence of unstable combustion.
摘要翻译：在燃气轮机燃烧器和燃气轮机中，提供燃烧高压空气的空气通道（54），提供燃料的先导喷嘴（44），主燃料喷嘴（45）和顶帽喷嘴（47），并且相对于燃烧器内筒（42）设置供给膜空气（冷却空气）的开口部（64），在内壁面上沿着圆周方向配置收缩部件（71,72,73）在内筒（42）中的燃烧气体的流动方向的下游。收缩构件（71,72和73）设置在不妨碍冷却空气流动的穿透部（74,75,76）的周向的规定区域中，能够抑制碳的产生一氧化物等，并抑制不稳定燃烧的发生。

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