-
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：US06701713B2
公开(公告)日：2004-03-09
申请号：US10195412
申请日：2002-07-16
IPC分类号： F02C726
摘要： A pilot nozzle diffusion-injects a fuel. A pilot swirler swirls a pilot air around the pilot nozzle. An air guide is arranged between the outer surface of the pilot nozzle and the pilot swirler. The air guide extends from the pilot swirler to a tip of the pilot nozzle. The air guide has a tip that protrudes beyond the tip of the pilot nozzle and this the tip of the air guide is bent away from a center of the pilot nozzle.
摘要翻译： 先导喷嘴扩散 - 喷射燃料。 先导式旋流器在引燃喷嘴周围旋转飞行员空气。 在引导喷嘴的外表面和先导旋流器之间布置有空气引导件。 空气引导器从先导旋流器延伸到先导喷嘴的尖端。 空气引导件具有突出超过引导喷嘴的尖端的尖端，并且空气引导件的尖端远离引导喷嘴的中心弯曲。
-
公开(公告)号：US07032386B2
公开(公告)日：2006-04-25
申请号：US10416515
申请日：2002-06-25
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。
-
公开(公告)号：US07360363B2
公开(公告)日：2008-04-22
申请号：US10415649
申请日：2002-07-05
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 。
-
公开(公告)号：US06915637B2
公开(公告)日：2005-07-12
申请号：US10790122
申请日：2004-03-02
CPC分类号： F23R3/286 , F23N2041/20 , F23R3/002 , F23R3/04 , F23R3/343 , Y02T50/675 , Y02T50/677
摘要： A gas turbine combustor is provided with a nozzle extension tube having an inclination outward in a diameter direction of a combustor inner cylinder and in a peripheral direction of the combustor inner cylinder. As a result, the premixed gas is transformed to a spiral flow passing into a combustion chamber while turning, i.e., an outward turning flow, thereby sufficiently mixing the premixed gas while the premixed gas is flowing in the combustion chamber.
摘要翻译： 燃气轮机燃烧器具有喷嘴延伸管，该喷嘴延伸管在燃烧器内筒的直径方向和燃烧器内筒的周向方向上向外倾斜。 结果，预混合气转化为在转动时即向外转动流动进入燃烧室的螺旋流，从而在预混合气体在燃烧室中流动的同时充分混合预混合气体。
-
公开(公告)号：US06772594B2
公开(公告)日：2004-08-10
申请号：US10178720
申请日：2002-06-25
IPC分类号： F02C100
CPC分类号： F23R3/286 , F23N2041/20 , F23R3/002 , F23R3/04 , F23R3/343 , Y02T50/675 , Y02T50/677
摘要： A gas turbine combustor is provided with a nozzle extension tube having an inclination outward in a diameter direction of a combustor inner cylinder and in a peripheral direction of the combustor inner cylinder. As a result, the premixed gas is transformed to a spiral flow passing into a combustion chamber while turning, i.e., an outward turning flow, thereby sufficiently mixing the premixed gas while the premixed gas is flowing in the combustion chamber.
摘要翻译： 燃气轮机燃烧器具有喷嘴延伸管，该喷嘴延伸管在燃烧器内筒的直径方向和燃烧器内筒的周向方向上向外倾斜。 结果，预混合气转化为在转动时即向外转动流动进入燃烧室的螺旋流，从而在预混合气体在燃烧室中流动的同时充分混合预混合气体。
-
-
-
-
-
-
搜索结果
7 条记录 (耗时 0.033 秒)
