-
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。
-
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。
-
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.
-
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。
-
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。
-
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.
-
公开(公告)号：US06502399B2
公开(公告)日：2003-01-07
申请号：US09794134
申请日：2001-02-28
申请人： Shigemi Mandai , Masataka Ohta , Mitsuru Inada , Shinji Akamatsu
发明人： Shigemi Mandai , Masataka Ohta , Mitsuru Inada , Shinji Akamatsu
IPC分类号： F23R314
CPC分类号： F23R3/14
摘要： A pre-mixture forming swirler in a gas turbine pre-mixed flame type low NOx combustor is improved so as to accelerate mixing of fuel and air and to prevent the occurrence of flame stagnation and burning of components. In particular, a three-dimensional swirler is constructed such that each swirler vane is twisted from a hub side thereof to a tip side so that a fitting angle of the tip side relative to a center axis of a fuel nozzle is larger than an angle of the hub side. Thereby, while the angle of the hub side is set smaller so that flame stagnation and burning of components resulted therefrom may be prevented from occurring, the angle of the tip side may be selected so that the shearing flow necessary for appropriate mixing of fuel and air is obtained. Thus, favorable pre-mixing is achieved, life deterioration due to burning, etc., is prevented and combustion efficiency is enhanced.
摘要翻译： 在燃气轮机预混合火焰型低NOx燃烧器中形成旋流器的预混合物得到改善，以加速燃料和空气的混合，并防止部件火焰停滞和燃烧。 特别地，三维旋流器被构造成使得每个旋流器叶片从其轮毂侧扭转到尖端侧，使得尖端侧相对于燃料喷嘴的中心轴线的配合角度大于 集线器侧。 由此，在将轮毂侧的角度设定得较小的同时，能够防止由此引起的部件产生火焰停滞和燃烧的情况下，可以选择前端侧的角度，使得适当地混合燃料和空气所需的剪切流 获得。 因此，可以实现良好的预混合，防止燃烧等引起的寿命劣化，提高燃烧效率。
-
公开(公告)号：US06434945B1
公开(公告)日：2002-08-20
申请号：US09470592
申请日：1999-12-22
IPC分类号： F02C100
CPC分类号： F23D14/48 , F23D11/38 , F23D17/002 , F23D2210/00
摘要： A dual fuel nozzle is provided with two different size injection holes. The first injection holes have larger diameters and are used only for injecting gaseous fuel into a combustion chamber. On the other hand, the second injection nozzles have smaller diameters and are used for injecting either gaseous fuel or liquid fuel as required. When gaseous fuel is used, if the fuel injection amount is large or medium, both of the first and the second injection holes or first injection holes only are used for injecting gaseous fuel depending upon the required fuel injection amount. When the fuel injection amount is low, only the second injection hole is used for injecting gaseous fuel. Therefore, the pressure drop across the fuel nozzle can be kept at sufficiently high level even when the fuel injection amount is low, and thereby combustion vibration is suppressed. Further, when liquid fuel is used, a premixed fuel and steam mixture is injected from the second injection holes. This also keep the pressure drop across the fuel nozzle at high level in order to suppress combustion vibration when the fuel injection amount is low.
摘要翻译： 双燃料喷嘴设有两个不同尺寸的喷射孔。 第一喷射孔具有较大的直径，并且仅用于将气体燃料喷射到燃烧室中。 另一方面，第二喷嘴具有较小的直径，并且用于根据需要喷射气体燃料或液体燃料。 当使用气体燃料时，如果燃料喷射量大或中等，则仅根据所需的燃料喷射量，第一和第二喷射孔或第一喷射孔仅用于喷射气体燃料。 当燃料喷射量低时，仅使用第二喷射孔来喷射气态燃料。 因此，即使燃料喷射量低，燃料喷嘴两端的压降也能保持在足够高的水平，从而抑制燃烧振动。 此外，当使用液体燃料时，从第二喷射孔注入预混燃料和蒸气混合物。 这也可以使燃料喷嘴上的压降保持在高水平，以便在燃料喷射量低时抑制燃烧振动。
-
公开(公告)号：US20060236700A1
公开(公告)日：2006-10-26
申请号：US11334744
申请日：2006-01-19
IPC分类号： F23R3/14
CPC分类号： F23R3/14 , F23C2900/07001 , Y02E20/344 , Y02T50/675
摘要： A combustor of a gas turbine, which is composed of an inner tube and a transition pipe connected together, comprising: an internal swirler composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring; and an external swirler composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring, the internal swirler and the external swirler being disposed within the inner tube.
摘要翻译： 燃气轮机的燃烧器由连接在一起的内管和过渡管构成，包括：内圆筒，其由相对于内管的中心轴线同心设置的圆筒状向内旋流环构成， 设置在所述向内旋流器环的外周面上的向内旋流叶片; 以及设置在向内旋流叶片的外周侧并且相对于向内旋流器环同心地形成的圆柱形向外旋流器的外部旋流器，以及设置在向外旋流器环的外周面上的多个向外旋流叶片 内部旋流器和外部旋流器设置在内管内。
-
公开(公告)号：US07669421B2
公开(公告)日：2010-03-02
申请号：US11334744
申请日：2006-01-19
IPC分类号： F02C3/00
CPC分类号： F23R3/14 , F23C2900/07001 , Y02E20/344 , Y02T50/675
摘要： A gas turbine combustor having an inner tube and a transition pipe connected together is provided. The combustor includes an internal swirler and an external swirler. The internal swirler is composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring. The external swirler is composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring. The internal swirler and the external swirler are disposed within the inner tube.
摘要翻译： 提供了具有连接在一起的内管和过渡管的燃气轮机燃烧器。 燃烧器包括内部旋流器和外部旋流器。 内部旋流器由相对于内管的中心轴线同心设置的圆筒形向内旋流器环以及设置在向内旋流器环的外周表面上的多个向内旋流叶片组成。 外部旋流器由设置在向内旋流叶片的外周侧并相对于向内旋流器环同心的圆柱形向外旋流器环组成，并且设置在外旋流器环的外周表面上的多个向外旋流叶片 。 内部旋流器和外部旋流器设置在内管内。
-
-
-
-
-
-
-
-
-
搜索结果
49 条记录 (耗时 0.033 秒)