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1. 发明授权

US06631614B2 Gas turbine combustor 失效
标题翻译：燃气轮机燃烧器
公开(公告)号：US06631614B2
公开(公告)日：2003-10-14
申请号：US09756188
申请日：2001-01-09
申请人： Shigemi Mandai , Tetsuo Gora , Katsunori Tanaka , Kouichi Nishida
发明人： Shigemi Mandai , Tetsuo Gora , Katsunori Tanaka , Kouichi Nishida
IPC分类号： F23R330
CPC分类号： F23D23/00 , F23D17/002 , F23D2900/00008 , F23R3/286 , F23R3/34
摘要： A gas turbine combustor, in which plural pre-mixers that inject fuel into swirling air passages are arranged to surround a pilot burner, and a pilot flame, guided by a pilot cone in the shape of a flaring pipe and provided at the rear end of the pilot burner, is mixed with a pre-mixture blown out from the pre-mixers to obtain a combustion gas, comprising flame-stabilizing means. The flame-stabilizing means lower the disturbance in a region where the pre-mixture and the pilot flame are mixed or stabilize the pilot flame, so that the flame generated by igniting the pre-mixture with the pilot flame is stabilized. By stabilizing the flame, combustion with a leaner air-fuel ratio is possible, and thereby the amount of NOx can be decreased.
摘要翻译：一种燃气轮机燃烧器，其中将燃料喷射到旋流空气通道中的多个预混合器被布置成围绕引燃燃烧器和引燃火焰，引导火焰由扩口管形式的先导锥体引导并且设置在引燃燃烧器与从预混合器吹出的预混合物混合以获得包含火焰稳定装置的燃烧气体。火焰稳定装置降低预混合物和引燃火焰混合或稳定引燃火焰的区域中的扰动，使得通过用引燃火焰点燃预混合物而产生的火焰是稳定的。通过稳定火焰，可以用较稀的空燃比进行燃烧，从而可以减少NOx的量。

2. 发明授权

US5410884A Combustor for gas turbines with diverging pilot nozzle cone 失效
标题翻译：燃气轮机燃油机具有发散的先导喷嘴锥体
公开(公告)号：US5410884A
公开(公告)日：1995-05-02
申请号：US137343
申请日：1993-10-18
申请人： Ichiro Fukue , Shigemi Mandai , Katsunori Tanaka , Hitoshi Kawabata , Nobuo Sato , Hiroyuki Nishida , Tetsuo Gora
发明人： Ichiro Fukue , Shigemi Mandai , Katsunori Tanaka , Hitoshi Kawabata , Nobuo Sato , Hiroyuki Nishida , Tetsuo Gora
IPC分类号： F23D17/00 , F23R3/28 , F23R3/34 , F23R3/36 , F02C1/00
CPC分类号： F23R3/286 , F23D17/002 , F23R3/34 , F23R3/36 , F23D2205/00
摘要： A gas turbine combustor suppresses the generation of NOx by mixing a fuel and air homogeneously. A pilot nozzle is provided at the center of the gas turbine combustor. A plurality of main nozzles surround the pilot nozzle. A diverging cone projects from the vicinity of the injection port of the pilot nozzle such that the flame from the main nozzles is sustained by the pilot nozzle and NOx is suppressed. The main nozzles can be provided upstream of the injection port of the pilot nozzle in which case an annular premixing nozzle having a throttled exit end is disposed downstream of the main nozzles. The main nozzle may also be in the form of a fuel nozzle having a plurality of tubes, a gaseous fuel being injected through one of the tubes, and liquid fuel being injected into the annular premixing nozzle through the other of the tubes so that the liquid fuel is atomized to mix the fuel and air homogeneously.
摘要翻译：燃气轮机燃烧器通过均匀混合燃料和空气来抑制NOx的产生。在燃气轮机燃烧器的中心设置有先导喷嘴。多个主喷嘴包围引燃喷嘴。发散锥从引燃喷嘴的喷射口附近突出，使得来自主喷嘴的火焰被导向喷嘴维持，并且抑制了NOx。主喷嘴可以设置在先导喷嘴的喷射口的上游，在这种情况下，具有节流出口端的环形预混喷嘴设置在主喷嘴的下游。主喷嘴也可以是具有多个管的燃料喷嘴的形式，气体燃料通过管中的一个喷射，液体燃料通过另一个管注入到环形预混合喷嘴中，使得液体燃料被雾化以均匀地混合燃料和空气。

3. 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。

4. 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。

5. 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.

6. 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。

7. 发明授权

US07032386B2 Gas turbine combustor 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US07032386B2
公开(公告)日：2006-04-25
申请号：US10416515
申请日：2002-06-25
申请人： Shigemi Mandai , Katsunori Tanaka , Masahito Kataoka , Keijirou Saitoh , Wataru Akizuki
发明人： Shigemi Mandai , Katsunori Tanaka , Masahito Kataoka , Keijirou Saitoh , Wataru Akizuki
IPC分类号： F02C1/00 , F23R3/06
CPC分类号： F23R3/04 , F23R2900/03042
摘要： A combustor for a gas turbine has an arrangement to form a layer of cooling-air on an inner surface of a liner of a combustion chamber. This layer of the cooling air extends from a fuel nozzle block of the combustor toward a downstream side with respect to the liner.
摘要翻译：用于燃气轮机的燃烧器具有在燃烧室的衬套的内表面上形成冷却空气层的装置。该冷却空气层从燃烧器的燃料喷嘴块向相对于衬套的下游侧延伸。

8. 发明授权

US06860098B2 Gas turbine combustor having bypass and annular gas passage for reducing uneven temperature distribution in combustor tail cross section 有权
标题翻译：具有旁路和环形气体通道的燃气轮机燃烧器，用于减少燃烧器尾部截面中不均匀的温度分布
公开(公告)号：US06860098B2
公开(公告)日：2005-03-01
申请号：US10098146
申请日：2002-03-15
申请人： Kiyoshi Suenaga , Shigemi Mandai , Katsunori Tanaka
发明人： Kiyoshi Suenaga , Shigemi Mandai , Katsunori Tanaka
IPC分类号： F02C7/18 , F23R3/04 , F23R3/06 , F23R3/26 , F23R3/42 , F02C9/00
CPC分类号： F23R3/045 , F23R2900/00014
摘要： There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through the bypass passage passes in the annular passage in the circumferential direction, and is uniformly supplied into the combustor in the circumferential direction thereof through an opening which connects the combustor and the annular passage. Accordingly, compressed air passing through the bypass passage can be supplied uniformly into a tail portion of the combustor, and unevenness of temperature distribution in a cross section of the combustor tail portion can be reduced.
摘要翻译：提供燃烧燃料的燃烧器，包括连接到燃烧器的一侧以将空气供入燃烧器的旁路通道; 以及环形通道，设置在燃烧器周围并连接到旁通通道，其中通过旁通通道供应的空气在圆周方向上通过环形通道，并且通过一个开口均匀地供应到燃烧器的周向，燃烧器和环形通道。因此，能够将通过旁通路的压缩空气均匀地供给到燃烧器的尾部，能够减少燃烧器尾部的截面的温度分布的不均匀。

9. 发明授权

US06463742B2 Gas turbine steam-cooled combustor with alternately counter-flowing steam passages 失效
标题翻译：燃气轮机蒸汽冷却燃烧器，交替逆流蒸汽通道
公开(公告)号：US06463742B2
公开(公告)日：2002-10-15
申请号：US09825881
申请日：2001-04-05
申请人： Shigemi Mandai , Kiyoshi Suenaga , Katsunori Tanaka
发明人： Shigemi Mandai , Kiyoshi Suenaga , Katsunori Tanaka
IPC分类号： F02C712
CPC分类号： F23R3/06 , F23D2214/00 , F23L7/005 , F23R3/10 , Y02T50/675
摘要： A steam-cooled combustor for a gas turbine has cooling steam passages, the steam flowing in opposite axial directions in adjacent channels.
摘要翻译：用于燃气轮机的蒸汽冷却燃烧器具有冷却蒸汽通道，蒸汽在相邻通道中沿相反轴向流动。

10. 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。

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