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1. 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。

2. 发明授权

US5795130A Heat recovery type gas turbine rotor 失效
标题翻译：热回收式燃气轮机转子
公开(公告)号：US5795130A
公开(公告)日：1998-08-18
申请号：US860589
申请日：1997-07-08
申请人： Kiyoshi Suenaga , Yoshikuni Kasai
发明人： Kiyoshi Suenaga , Yoshikuni Kasai
IPC分类号： F01D5/08 , F01D5/18 , F01D25/12 , F02C7/16 , F04D29/58
CPC分类号： F01D5/084 , F01D5/085 , F05D2260/205 , F05D2260/2322
摘要： Disclosed is a gas turbine rotor (5) having multi-stage moving blades, each fitted to a disc (12), characterized in comprising: an inner cavity (9) and an outer cavity (8) provided between each disc (12); a blade cooling passage (6) of each moving blade except a rearmost stage moving blade (4); a cooling steam supply passage (13) extending from a rear portion of the rearmost stage moving blade (4) to a leading edge portion of a foremost stage moving blade (1) in the rotor (5); a bifurcation passage (16) provided in the disc (12) portion of the foremost stage so as to connect at its proximal end to the cooling steam supply passage (13) and to bifurcate at its distal end so that one bifurcation thereof (16a) connects to one end of the blade cooling passage (6) and the other bifurcation (16b) connects to the outer cavity (8); a blade return passage (17) connecting at its proximal end to the other end of the blade cooling passage (6) and at its distal end to the inner cavity (9); a cavity connecting passage (20) for connecting each inner cavity (9); a return passage (11) extending along the cooling steam supply passage (13) from the inner cavity (9) of the rearmost stage moving blade (4); a blade connecting passage (18) provided in each disc (12) except the discs (12) of the foremost stage and the rearmost stage for connecting the blade cooling passage (6) and the outer cavity (8); an inter-cavity passage (19) for connecting the outer cavity (8) and the inner cavity (9) both of the rearmost stage.
摘要翻译： PCT No.PCT / JP96 / 03416 Sec。 371日期1997年7月8日 102（e）日期1997年7月8日PCT提交1996年11月21日PCT公布。 WO97 / 19256 PCT公开号日期1997年5月29日公开是具有多级活动叶片的燃气轮机转子（5），每个叶片均装配在盘（12）上，其特征在于包括：内腔（9）和设置在每个盘（12）; 每个动叶片的叶片冷却通道（6）除了最后级的动叶片（4）之外; 冷却蒸汽供给通路（13），其从所述最后台动叶片（4）的后部延伸到所述转子（5）中的最前段动叶片（1）的前缘部; 设置在最前段的盘（12）部分中的分叉通道（16），以便在其近端处连接到冷却蒸汽供应通道（13）并在其远端分叉，使得其一个分叉（16a）连接到叶片冷却通道（6）的一端，另一分支（16b）连接到外腔（8）; 叶片返回通道（17），其在其近端处连接到叶片冷却通道（6）的另一端并且在其远端连接到内腔（9）; 用于连接每个内腔（9）的空腔连接通道（20）; 从所述最后级动叶片（4）的内腔（9）沿所述冷却蒸汽供应通道（13）延伸的回流通道（11）。设置在每个盘（12）中除了最前一级的盘（12）和用于连接刀片冷却通道（6）和外腔（8）的最后级之外的刀片连接通道（18）。用于连接两个最后阶段的外腔（8）和内腔（9）的腔间通道（19）。

3. 发明授权

US6065931A Gas turbine moving blade 失效
标题翻译：燃气轮机动叶片
公开(公告)号：US6065931A
公开(公告)日：2000-05-23
申请号：US035614
申请日：1998-03-05
申请人： Kiyoshi Suenaga , Yoshikuni Kasai , Kazuo Uematsu
发明人： Kiyoshi Suenaga , Yoshikuni Kasai , Kazuo Uematsu
IPC分类号： F01D5/18 , F01D5/08
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/205 , F05D2260/2322
摘要： A gas turbine moving blade, which has a blade root section, a wing section, and a platform section, comprises a refrigerant supply port provided in the blade root section, a refrigerant recovery port provided in the blade root section, a serpentine passage provided in the wing section and communicating with the refrigerant supply port and the refrigerant recovery port, and a convection-cooling passage provided in the platform section and allowing sealing air and a refrigerant for cooling the platform section by convection to pass therein.
摘要翻译：具有叶片根部，翼部和平台部的燃气轮机动叶片包括设置在叶片根部的制冷剂供给口，设置在叶片根部的制冷剂回收口，设置在叶片根部的蛇形通路所述翼部与所述制冷剂供给口和所述制冷剂回收口连通，所述对流冷却通路设置在所述平台部并且允许密封空气和用于通过对流冷却所述平台部的制冷剂通过。

4. 发明授权

US5873695A Steam cooled blade 失效
标题翻译：蒸汽冷却叶片
公开(公告)号：US5873695A
公开(公告)日：1999-02-23
申请号：US861539
申请日：1997-05-22
申请人： Kenichiro Takeishi , Yoshikuni Kasai
发明人： Kenichiro Takeishi , Yoshikuni Kasai
IPC分类号： F01D5/18 , F02C7/18 , F04D29/32 , F04D29/58 , F04D29/38
CPC分类号： F01D5/187 , F05D2260/205 , F05D2260/2212 , F05D2260/2322
摘要： A steam cooled blade operating in a high temperature gas with a high cooling effect on a trailing edge portion has an impingement plate, disposed in the blade lengthwise direction within a trailing edge side cooling passage formed on a trailing edge side of a moving blade. The impingement plate partitions the trailing edge side cooling passage into a convection cooling steam passage, into which steam is introduced, and an impingement cooling steam passage, formed along a trailing edge of the moving blade. The steam cooled blade further has a by-pass passage 14 for joining the steam, after it is used for cooling the moving blade, flowing from a blade tip side of the impingement cooling steam passage with the steam flowing to a leading edge direction of the moving blade from the convection cooling steam passage.
摘要翻译：在后缘部分具有高冷却效果的高温气体中工作的蒸汽冷却叶片具有在形成于活动叶片的后缘侧的后缘侧冷却通道中沿叶片长度方向设置的冲击板。冲击板将后缘侧冷却通道分隔成引入蒸汽的对流冷却蒸汽通道和沿着动叶片的后缘形成的冲击冷却蒸汽通道。蒸汽冷却叶片还具有用于连接蒸汽的旁通通道14，在用于冷却动叶片之后，蒸汽流经冲击冷却蒸汽通道的叶片末端侧流动，从对流冷却蒸汽通道移动叶片。

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