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1. 发明授权

US06553766B2 Cooling structure of a combustor tail tube 有权
标题翻译：燃烧器尾管的冷却结构
公开(公告)号：US06553766B2
公开(公告)日：2003-04-29
申请号：US09832937
申请日：2001-04-12
申请人： Takehiko Shimizu , Satoshi Hada , Kouichi Akagi , Katsunori Tanaka , Ryotaro Magoshi , Mitsuo Hasegawa , Shigemi Mandai , Mitsuru Kondo
发明人： Takehiko Shimizu , Satoshi Hada , Kouichi Akagi , Katsunori Tanaka , Ryotaro Magoshi , Mitsuo Hasegawa , Shigemi Mandai , Mitsuru Kondo
IPC分类号： F23R306
CPC分类号： F23M5/08 , F01D9/023 , F02C7/16 , F05D2260/2322 , F23R3/002
摘要： A cooling structure of a combustor tail tube is capable of avoiding the formation of cracks in the tail tube by lessening thermal stress and preventing thermal deformation, thus extending the service life. A multiplicity of cooling jackets (5) extend in the longitudinal direction of the tail tube of a gas turbine combustor along the entire circumference of the tail tube wall. The passage sectional area of the cooling jackets (5) is varied depending on the metal temperature of parts of the tail tube (4). For example, the passage sectional area of the cooling jackets (5) formed at the rotor side wall and the mutually opposite side walls of the adjacent tail tube is larger than the passage sectional area of the cooling jackets (5) formed at the casing side wall.
摘要翻译：燃烧器尾管的冷却结构能够通过减少热应力和防止热变形来避免尾管中的裂纹的形成，延长使用寿命。多个冷却套（5）沿着尾管壁的整个圆周在燃气轮机燃烧器的尾管的纵向方向上延伸。冷却套（5）的通道截面积根据尾管（4）的部件的金属温度而变化。例如，形成在转子侧壁的冷却套（5）和相邻尾管的相对侧壁的通道截面积大于形成在壳体侧的冷却套（5）的通道截面面积壁。

2. 发明授权

US07360363B2 Premixing nozzle, combustor, and gas turbine 有权
标题翻译：预喷嘴，燃烧器和燃气轮机
公开(公告)号：US07360363B2
公开(公告)日：2008-04-22
申请号：US10415649
申请日：2002-07-05
申请人： Shigemi Mandai , Keijirou Saitoh , Katsunori Tanaka , Wataru Akizuki
发明人： Shigemi Mandai , Keijirou Saitoh , Katsunori Tanaka , Wataru Akizuki
IPC分类号： F23R3/14
CPC分类号： F23R3/14 , F23C2900/07001 , F23R3/286 , F23R3/343
摘要： A premixing nozzle includes swirler blades for agitating combustion air inside a nozzle body. Each one end of the swirler blades is fitted to the nozzle body, and the other end is connected to a hub, respectively. The tip portion of a fuel nozzle shaft is conical, and a part of the tip portion is arranged inside the hub. A combustion gas flows into the hub from a space between the tip portion of the fuel nozzle shaft and the upstream end of the hub, passes through between the tip portion and the inner peripheral surface of the hub, and flows toward the downstream of the hub.
摘要翻译：预混合喷嘴包括用于搅拌喷嘴体内的燃烧空气的旋流器叶片。旋流器叶片的每一端安装到喷嘴体上，另一端分别连接到轮毂。燃料喷嘴轴的前端部是锥形的，顶端部的一部分配置在轮毂内。燃烧气体从燃料喷嘴轴的前端部和轮毂的上游端部之间的空间流入轮毂，在轮毂的前端部和内周面之间通过，并且向毂的下游侧流动。

3. 发明授权

US06973790B2 Gas turbine combustor, gas turbine, and jet engine 有权
标题翻译：燃气轮机燃烧器，燃气轮机和喷气发动机
公开(公告)号：US06973790B2
公开(公告)日：2005-12-13
申请号：US10464499
申请日：2003-06-19
申请人： Kiyoshi Suenaga , Shigemi Mandai , Masaki Ono , Katsunori Tanaka
发明人： Kiyoshi Suenaga , Shigemi Mandai , Masaki Ono , Katsunori Tanaka
IPC分类号： F23M99/00 , F02C7/24
CPC分类号： F23M20/005 , F23D2210/00 , F23R2900/00014
摘要： For the purpose of reduced NOx gas emission, a gas turbine engine comprises a cylinder having a combustion region inside of the cylinder; a resonator having a cavity and provided around the surface of the cylinder and sound absorption holes formed on the cylinder and having opening ends on the cylinder.
摘要翻译：为了减少NOx气体排放的目的，燃气涡轮发动机包括在气缸内部具有燃烧区域的气缸; 具有腔体并且设置在气缸表面周围的谐振器和形成在气缸上并且在气缸上具有开口端的吸声孔。

4. 发明授权

US06668557B2 Pilot nozzle of gas turbine combustor 失效
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
CPC分类号： F23R3/20 , F23R3/343
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.

5. 发明授权

US06837050B2 Gas turbine combustor 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US06837050B2
公开(公告)日：2005-01-04
申请号：US10124413
申请日：2002-04-18
申请人： Shigemi Mandai , Kiyoshi Suenaga , Kuniaki Aoyama , Kazufumi Ikeda , Katsunori Tanaka
发明人： Shigemi Mandai , Kiyoshi Suenaga , Kuniaki Aoyama , Kazufumi Ikeda , Katsunori Tanaka
IPC分类号： F02C7/18 , F23M99/00 , F23R3/00 , F23R3/06 , F23R3/10 , F23R3/30 , F02C7/25
CPC分类号： F23R3/06 , F23D2211/00 , F23M20/005 , F23R3/005 , F23R2900/00001 , F23R2900/00014
摘要： A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

6. 发明授权

US06662547B2 Combustor 有权
公开(公告)号：US06662547B2
公开(公告)日：2003-12-16
申请号：US09987519
申请日：2001-11-15
申请人： Shigemi Mandai , Masataka Ohta , Satoshi Tanimura , Katsunori Tanaka , Koichi Nishida
发明人： Shigemi Mandai , Masataka Ohta , Satoshi Tanimura , Katsunori Tanaka , Koichi Nishida
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.

7. 发明授权

US06594999B2 Combustor, a gas turbine, and a jet engine 失效
标题翻译：燃烧器，燃气轮机和喷气发动机
公开(公告)号：US06594999B2
公开(公告)日：2003-07-22
申请号：US09908637
申请日：2001-07-20
申请人： Shigemi Mandai , Yutaka Kawata , Atsushi Maekawa , Katsunori Tanaka , Masaharu Nishimura , Soichiro Tomimoto
发明人： Shigemi Mandai , Yutaka Kawata , Atsushi Maekawa , Katsunori Tanaka , Masaharu Nishimura , Soichiro Tomimoto
IPC分类号： F02C300
CPC分类号： F23R3/26 , F23D2210/00 , F23D2900/00008 , F23D2900/14004 , F23R3/14 , F23R3/54 , F23R2900/00014 , Y02T50/675
摘要： A combustor can simultaneously reduce the amount of NOx exhaust and combustion oscillation. The combustor has an internal cylinder which accommodates a premixing nozzle and an external cylinder which accommodates the internal cylinder, and includes an air flow passage which supplies air from a compressor to the premixing nozzle. The air flow passage is provided with a punched metal plate near the maximum velocity fluctuation position whereat the velocity fluctuation of the air flow increases to a maximum.
摘要翻译：燃烧器可以同时减少NOx排放量和燃烧振荡。燃烧器具有内筒，其容纳预混合喷嘴和容纳内筒的外筒，并且包括将空气从压缩机供给到预混合喷嘴的空气流动通道。空气流路在最大速度波动位置附近设置有冲孔金属板，空气流的速度波动最大化。

8. 发明授权

US06460339B2 Gas turbine fuel injector with unequal fuel distribution 有权
标题翻译：具有不均等燃料分配的燃气轮机燃油喷射器
公开(公告)号：US06460339B2
公开(公告)日：2002-10-08
申请号：US09828138
申请日：2001-04-09
申请人： Koichi Nishida , Katsunori Tanaka , Shigemi Mandai , Yutaka Kawata , Masataka Ohta
发明人： Koichi Nishida , Katsunori Tanaka , Shigemi Mandai , Yutaka Kawata , Masataka Ohta
IPC分类号： F02G300
CPC分类号： F23R3/343 , F23R3/286
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。

9. 发明授权

US07832211B2 Gas turbine combustor and a gas turbine equipped therewith 有权
标题翻译：燃气轮机燃烧器和配备有燃气轮机的燃气轮机
公开(公告)号：US07832211B2
公开(公告)日：2010-11-16
申请号：US10525004
申请日：2003-11-28
申请人： Kazufumi Ikeda , Shigemi Mandai , Yutaka Kawata , Kuniaki Aoyama , Masaki Ono , Katsunori Tanaka
发明人： Kazufumi Ikeda , Shigemi Mandai , Yutaka Kawata , Kuniaki Aoyama , Masaki Ono , Katsunori Tanaka
IPC分类号： F02C7/24 , F23M5/00
CPC分类号： F23R3/04 , F05B2260/962 , F23M20/005 , F23R2900/00014 , Y02T50/675
摘要： In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor (3) is provided with a first box body (30), which is installed outside an object body (20) such as a combustor basket (6), a transition piece (7) or a bypass duct (11) so as to form a first internal space (31) having a predetermined capacity; and a first throat (32) having a predetermined length which has one end (32a) open to a side wall (20a) of the object body (20) and has the other end (32b) open to a first internal space (31); wherein, a first resistive element (33) having a multiple number of through-holes is inserted and engaged to one end (32a). Fluid particles serving as vibration elements of combustion vibration caused in a combustion region are effectively trapped by the first resistive element (33) and at the same time resonate with the air of the first internal space (31) being connected through the first throat (32) and vibrate in the neighborhood of the first resistive element (33), thereby damping vibration amplitude thereof.
摘要翻译：为了实现NOx的稳定降低，提供能够减少燃烧振动的燃气轮机燃烧器。燃烧器（3）设置有第一箱体（30），其安装在诸如燃烧器筐（6），过渡件（7）或旁通管道（11）的物体（20）的外部，以便以形成具有预定容量的第一内部空间（31）; 以及具有一定长度的第一喉部（32），所述第一喉部（32）的一端（32a）朝向所述物体（20）的侧壁（20a）开口，并且另一端（32b）向第一内部空间（31）开放， ; 其中，具有多个通孔的第一电阻元件（33）被插入并接合到一端（32a）。作为在燃烧区域中产生的燃烧振动的振动元件的流体颗粒被第一电阻元件（33）有效地捕获，同时与通过第一喉部（32）连接的第一内部空间（31）的空气共振）并且在第一电阻元件（33）附近振动，从而阻尼振动振幅。

10. 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。

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