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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。
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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。
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公开(公告)号:US06668557B2
公开(公告)日:2003-12-30
申请号:US10200165
申请日:2002-07-23
申请人: Masataka Ohta , Kuniaki Aoyama , Mitsuru Inada , Shigemi Mandai , Satoshi Tanimura , Katsunori Tanaka , Koichi Nishida
发明人: Masataka Ohta , Kuniaki Aoyama , Mitsuru Inada , Shigemi Mandai , Satoshi Tanimura , Katsunori Tanaka , Koichi Nishida
IPC分类号: F02C7264
摘要: A pilot nozzle of a gas turbine combustor comprises a first structure, provided near a main nozzle of a combustor that injects fuel oil, having a flow channel for a fuel gas and an outlet for the fuel gas. The first structure diffusion-injecting the fuel gas obliquely forward through the outlet to maintain a flame and to aid ignition of the fuel oil injected from the main nozzle. There is further provided a second structure which circulates in whirls a combustion gas generated due to the combustion of the fuel gas.
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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。
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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。
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公开(公告)号:US06662547B2
公开(公告)日:2003-12-16
申请号:US09987519
申请日:2001-11-15
IPC分类号: F02C330
CPC分类号: F23L7/002 , F23D11/38 , F23D2206/10 , F23D2214/00 , F23R3/343
摘要: A combustor includes a burner and a combustion chamber including a heat chamber to which fuel is supplied from the burner. The burner includes a nozzle having a fuel discharge outlet from which the fuel is discharged into the combustion chamber; and the nozzle includes a plurality of discharge openings around the fuel discharge outlet from which cooling water is discharged toward inside surfaces of the heat chamber. The plurality of discharge openings may be disposed so that the directions of the cooling water discharged from the discharge openings differ in the radial direction.
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公开(公告)号:US06460339B2
公开(公告)日:2002-10-08
申请号:US09828138
申请日:2001-04-09
IPC分类号: F02G300
摘要: A gas turbine combustor improves the fuel distribution from a main fuel nozzle, suppressing fluctuations of internal pressure and elevation of inner tube metal temperature, and enhancing the combustion stability and durability of the combustor. The gas turbine combustor is a multi-nozzle type premixing combustor with a nozzle outer tube (7) for forming and injecting a premixed gas of main fuel and combustion air divided and disposed in plural sections around a cone (4) for forming a diffusion flame by reaction between pilot fuel and combustion air disposed in a center of a section of a combustor inner tube (1). Nozzle holes (5a) of a main fuel nozzle (5) are formed in three positions at equal intervals on the nozzle main body wall, and one of them is disposed at the outer periphery of the combustor inner tube (1) on a diametral line linking between the center of the combustor inner tube (1) and the center of the main fuel nozzle (5), whereby the fuel distribution to the outer periphery is decreased.
摘要翻译: 燃气轮机燃烧器改善来自主燃料喷嘴的燃料分布,抑制内部压力的波动和内管金属温度升高,提高燃烧器的燃烧稳定性和耐久性。 燃气轮机燃烧器是具有喷嘴外管(7)的喷嘴外管(7)的多喷嘴型预混合燃烧器,用于形成并喷射主燃料和燃烧空气的预混合气体,燃烧空气以形成扩散火焰的锥体(4)为中心分成多个部分 通过引燃燃料与设置在燃烧器内管(1)的一部分的中心的燃烧空气之间的反应。 主燃料喷嘴(5)的喷嘴孔(5a)以等间隔在喷嘴主体壁上形成三个位置,其中一个位于燃烧器内管(1)的外径上, 在燃烧器内管(1)的中心与主燃料喷嘴(5)的中心之间连接,从而减少了向外周的燃料分配。
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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
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。
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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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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。
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