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公开(公告)号：US20060177312A1
公开(公告)日：2006-08-10
申请号：US11340510
申请日：2006-01-27
申请人： Yasuoki Tomita , Kouji Watanabe , Masamitsu Okuzono , Masaki Ono
发明人： Yasuoki Tomita , Kouji Watanabe , Masamitsu Okuzono , Masaki Ono
IPC分类号： F01D11/00
CPC分类号： F01D5/081 , F01D5/22 , F01D11/008 , F05C2201/0463 , F05C2201/0466 , F05D2250/29 , F05D2260/20 , Y02T50/671 , Y02T50/676 , Y10S416/50
摘要： A rotating blade body is provided that can restrain vibrations of rotating blades effectively. The rotating blade body comprises rotor disc, a plurality of rotating blades being assembled so as to extend from the outer circumference of the rotor disc in a radial pattern, and sealing pins extending along the direction of the rotating shaft in the gaps between the platforms of the rotating blades being adjacent in circumferential direction. The sealing pins have a through-hole made therein, penetrating axially from one end surface to the other end surface.
摘要翻译： 提供了可以有效地抑制旋转叶片的振动的旋转叶片体。 旋转叶片主体包括转子盘，多个旋转叶片组装成以径向图案从转子盘的外圆周延伸，以及沿着旋转轴的方向在第二平台之间的间隙中延伸的密封销 旋转叶片在圆周方向上相邻。 密封销具有形成在其中的通孔，其从一个端面轴向穿透到另一端面。
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公开(公告)号：US20050135925A1
公开(公告)日：2005-06-23
申请号：US10820744
申请日：2004-04-09
CPC分类号： F01D11/005 , B23K26/389 , F01D5/18 , F01D5/187 , F01D5/188 , F01D9/041 , F05D2240/80 , F05D2240/81 , F05D2260/201 , F05D2260/2212
摘要： The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A low passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.
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33.发明授权Turbine moving blade, turbine stationary blade, turbine split ring, and gas turbine 有权涡轮动叶片，涡轮固定叶片，涡轮分裂环和燃气轮机公开(公告)号：US06811373B2
公开(公告)日：2004-11-02
申请号：US10067947
申请日：2002-02-08
IPC分类号： F01D518
CPC分类号： F01D5/288 , C23C28/00 , F01D9/02 , F05D2230/90 , F05D2240/80 , F05D2300/611
摘要： The present invention provides a turbine moving blade, a turbine stationary blade, and a turbine split ring which are capable of restraining the deterioration and peeling-off of a thermal barrier coating easily and surely, and a gas turbine capable of enhancing the energy efficiency by increasing the temperature of combustion gas. The turbine moving blade provided in a turbine constituting the gas turbine includes a platform having a gas path surface extending in the combustion gas flow direction, and a blade portion erecting on the platform. The thermal barrier coating covering the gas path surface is formed so as to go around from the gas path surface to an upstream-side end face and a downstream-side end face of the outer peripheral faces of the platform.
摘要翻译： 本发明提供了能够容易且可靠地抑制热障涂层的劣化和剥离的涡轮机动叶片，涡轮静叶片和涡轮分裂环，以及能够通过以下方式提高能量效率的燃气轮机 增加燃烧气体的温度。 设置在构成燃气轮机的涡轮机中的涡轮机动叶片具有在燃烧气体流动方向上具有气体流路面的平台和在平台上竖起的叶片部。 覆盖气体路径表面的隔热涂层形成为从气体路径表面到平台的外周面的上游侧端面和下游侧端面。
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公开(公告)号：US6152690A
公开(公告)日：2000-11-28
申请号：US242529
申请日：1999-05-19
申请人： Yasuoki Tomita , Hiroki Fukuno , Katsunori Tanaka , Toshiaki Sano
发明人： Yasuoki Tomita , Hiroki Fukuno , Katsunori Tanaka , Toshiaki Sano
CPC分类号： F01D11/001 , F01D11/025 , F01D11/127
摘要： A seal ring (1) securing inner shroud members (32) of stationary blades (31) is provided with arm portions (2, 3) projecting along lower surfaces of end portions of the inner shroud members (32). Honeycomb seals (4a, 4b) are mounted on the arm portions (2, 3), respectively. The honeycomb seal (4a) is disposed opposite fins (11a) provided on a rotor arm portion (11) of a platform (22) of a moving blade (21) so that a predetermined clearance (t) can be maintained between the honeycomb seal and the fins. On the other hand, the honeycomb seal (4b) is disposed opposite fins (14b) provided on a seal portion (14a) of a sealing plate (14) of the moving blade (21) so that a predetermined clearance (t) can be maintained between the honeycomb seal and the fins. The inner shroud members (32) undergo deformation after operation of the gas turbine. However, because the honeycomb seals (4a, 4b) are mounted on the arm portions (3, 2), respectively, of the seal ring (1) disposed separately and independently from the inner shroud members (32), the honeycomb seals (4a, 4b) can remain unaffected by the deformation of the inner shroud members (32), whereby the predetermined clearances (t) can be consistently maintained.
摘要翻译： PCT No.PCT / JP98 / 02722 Sec。 371日期1999年5月19日 102（e）日期1999年5月19日PCT提交1998年6月18日PCT公布。 WO98 / 58159 PCT公开 日期1998年12月23日固定固定叶片（31）的内罩构件（32）的密封环（1）设置有沿着内护罩构件（32）的端部的下表面突出的臂部（2,3）。 蜂窝密封件（4a，4b）分别安装在臂部分（2,3）上。 蜂窝密封件4a设置在设置在活动叶片（21）的平台（22）的转子臂部分（11）上的翅片（11a）上，从而可以在蜂窝密封件（4a）之间保持预定的间隙（t） 和翅片。 另一方面，蜂窝状密封件4b设置在设置在动叶片21的密封板14的密封部14a上的翅片14b上，从而能够使规定的间隙（t）为 保持在蜂窝状密封件和翅片之间。 内部护罩构件（32）在燃气轮机的操作之后经历变形。 然而，由于蜂窝密封件（4a，4b）分别安装在与内侧护罩构件（32）分开且独立设置的密封环（1）的臂部（3,2）上，蜂窝密封件（4a） ，4b）可以不受内侧护罩构件（32）的变形的影响，由此可以一致地保持预定间隙（t）。
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公开(公告)号：US6099253A
公开(公告)日：2000-08-08
申请号：US203680
申请日：1998-12-01
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
CPC分类号： F01D5/225 , F01D5/187 , Y02T50/676
摘要： A gas turbine rotor blade has a plurality of first cooling holes for the flow of a cooling gas bored in a blade portion along its lengthwise direction and a plurality of second cooling holes for flow of the cooling gas bored in a shroud along its plane direction so as to communicate with the first cooling holes, and is constructed such that the cooling gas can flow in a uniform distribution. The plurality of the first cooling holes 3 for flow of the cooling gas are bored in the blade portion 2 and the plurality of the second cooling holes 5 for flow of the cooling gas are bored in the shroud 1 along its plane direction. The second cooling holes 5 communicate with the first cooling holes 3, hole to hole, via two-step holes 4, and the second cooling holes 5 are bored alternately on the dorsal side and the ventral side of the rotor blade.
摘要翻译： 燃气轮机转子叶片具有多个第一冷却孔，用于沿其长度方向在叶片部分中钻出的冷却气体的流动，以及多个用于沿着其平面方向在护罩中钻出的冷却气体的流动的第二冷却孔， 与第一冷却孔连通，并且被构造成使得冷却气体能够以均匀的分布流动。 多个用于冷却气体流动的第一冷却孔3在叶片部分2中钻孔，并且用于冷却气体流动的多个第二冷却孔5沿其平面方向在护罩1中钻孔。 第二冷却孔5通过两步孔4与第一冷却孔3，孔对孔连通，第二冷却孔5在转子叶片的背侧和腹侧交替地钻孔。
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公开(公告)号：US6092983A
公开(公告)日：2000-07-25
申请号：US202594
申请日：1998-12-17
申请人： Yasuoki Tomita , Sunao Aoki , Kiyoshi Suenaga , Tatsuo Ishiguro
发明人： Yasuoki Tomita , Sunao Aoki , Kiyoshi Suenaga , Tatsuo Ishiguro
CPC分类号： F01D9/065 , F01D5/187 , F01D9/02 , F05D2240/10 , F05D2240/81 , F05D2260/22141
摘要： In a cooled stationary blade assembly for a gas turbine, an interior of a blade and an inner shroud are cooled by steam to eliminate the use of air cooling. Steam passages 33A, 33B, 33C, 33D, 33E and 33F are provided in the stationary blade 30. The cooling steam 39 is introduced from the steam passage 33A on the front edge side through an outer shroud and passes, in order, through the steam passages 33B, 33C, 33D, and 33E to flow into the steam passage 33F at the rear edge side to cool the interior of the blade, and is recovered through the outer shroud from the upper portion of the steam passage 33F. A portion of the steam from the steam passage 33A is introduced into the inner shroud 31, enters to steam passages 20 from a steam introduction passage 22, branches to the right and left through both end portions, and flows out into the steam passage 33F at the rear edge from a steam discharge passage 21. Not only the interior of the blade, but also the interior of the inner shroud 31 is cooled by the steam so that the cooling air is dispensed with.
摘要翻译： PCT No.PCT / JP98 / 01958 371日期1998年12月17日第 102（e）1998年12月17日日期PCT提交1998年4月28日PCT公布。 出版物WO98 / 50684 日期1998年11月12日在用于燃气轮机的冷却固定叶片组件中，叶片和内罩的内部由蒸汽冷却以消除空气冷却的使用。 蒸汽通道33A，33B，33C，33D，33E和33F设置在固定叶片30中。冷却蒸汽39通过外护罩从前边缘侧的蒸汽通道33A引入，并依次通过蒸汽 通道33B，33C，33D和33E在后边缘侧流入蒸汽通道33F以冷却叶片的内部，并通过外护罩从蒸汽通道33F的上部回收。 来自蒸汽通道33A的蒸汽的一部分被引入内罩31，从蒸汽引入通道22进入蒸汽通道20，通过两个端部向右和向左分支，并且流出到蒸汽通道33F中 来自蒸汽排出通道21的后边缘。不仅叶片的内部，而且内部护罩31的内部都被蒸汽冷却，从而省去了冷却空气。
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公开(公告)号：US6077034A
公开(公告)日：2000-06-20
申请号：US38451
申请日：1998-03-11
CPC分类号： F01D5/08 , F01D5/187 , F01D9/065 , F05D2260/2212
摘要： In the present disclosure, an air pipe extends through a stationary blade between outer and inner shrouds. Further, an air passage is directed to a lower portion of the stationary blade and is communicated with the air pipe so that a serpentine cooling passage is formed. The air enters a cavity from the air passage and is discharged to a gas passage through an air hole, a passage and a seal. Thus, the cavity is sealed at a high pressure. Cooling air is supplied from the air passage to a rotating blade through a cooling air hole, a cooling air chamber, a radial hole and a lower portion of a platform. The stationary blade is cooled by the air through the air passage. The cooling air can be supplied to the rotating blade at a low temperature and a high pressure as they are. Accordingly, the air can be also supplied to the rotating blade when a rotor is cooled by vapor.
摘要翻译： 在本公开中，空气管在外护罩和内护罩之间延伸穿过固定刀片。 此外，空气通道被引导到固定叶片的下部并且与空气管连通，从而形成蛇形冷却通道。 空气从空气通道进入空腔，并通过气孔，通道和密封件排放到气体通道。 因此，空腔在高压下被密封。 冷却空气从空气通道通过冷却空气孔，冷却空气室，径向孔和平台的下部供应到旋转叶片。 固定叶片由空气通过空气通道冷却。 冷却空气可以以低温和高压直接供给到旋转叶片。 因此，当转子被蒸汽冷却时，空气也可以供应到旋转叶片。
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公开(公告)号：US6071075A
公开(公告)日：2000-06-06
申请号：US28886
申请日：1998-02-24
申请人： Yasuoki Tomita , Eiji Akita , Masao Terazaki
发明人： Yasuoki Tomita , Eiji Akita , Masao Terazaki
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/2212
摘要： A mechanism for cooling the platform for the drive blades of a gas turbine uses a simple configuration which reliably cools the platform. The mechanism includes cooling channels in the interior of the platform which open out from one of the cooling air channels for cooling the turbine blades and which exit the platform through the edge nearest the tail. Cooling channels in the platform open out from the entrance to blade cooling channels, travel from the head of the blade along the blade sides, and exit through the edge near the tail of the blade. This structure diverts a portion of the cooling air entering the blade from the cooling channel in the base in order to cool the platform. Cooling air channels may extend from an enclosed air space below the platform to the upper surface of the platform at the front or rear side of the blade. Air channels may also extend on the rear of the turbine blade obliquely from the underside of the platform to the trailing edge of the platform. These channels or combinations thereof constitute a cooling structure through which air can flow to cool a platform for the drive blades of a gas turbine in an efficient and effective manner.
摘要翻译： 用于冷却燃气轮机的驱动叶片的平台的机构使用可靠地冷却平台的简单构造。 该机构包括平台内部的冷却通道，其从一个冷却空气通道开口，用于冷却涡轮叶片，并且通过最靠近尾部的边缘离开平台。 平台上的冷却通道从入口到叶片冷却通道开口，沿着叶片侧从叶片的头部行进，并通过靠近叶片尾部的边缘离开。 这种结构将进入叶片的冷却空气的一部分从基座中的冷却通道转移，以便冷却平台。 冷却空气通道可以从平台下方的封闭空气空间延伸到在叶片的前侧或后侧的平台的上表面。 空气通道也可以在涡轮叶片的后部从平台的下侧向平台的后边缘倾斜延伸到平台的后缘。 这些通道或其组合构成了一种冷却结构，通过该冷却结构，空气可以以有效和有效的方式流动以冷却燃气轮机的驱动叶片的平台。
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公开(公告)号：US6065282A
公开(公告)日：2000-05-23
申请号：US960466
申请日：1997-10-29
申请人： Ichiro Fukue , Eiji Akita , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Yasuoki Tomita
CPC分类号： F02C7/185 , F05D2260/205
摘要： A gas turbine comprises: a first closed circuit in which cooling gas is supplied to a casing, allowed to pass through stationary blades, and removed to the outside of casing after cooling the stationary blades; a second closed circuit in which cooling air is supplied to the casing, allowed to pass through moving blades, and removed to the outside of casing after cooling the moving blades; a cooler for cooling the cooling gas in the first and second closed circuits; and a booster for pressurizing and circulating the cooling gas cooled by the cooler.Also, A gas turbine comprises: a first closed circuit in which cooling air cooled after being extracted from a combustor plenum is allowed to pass through stationary blades successively to cool the stationary blades, and then recovered and returned to a compressor on the upstream side of the combustor plenum; and a second closed circuit in which cooling air cooled after being extracted from the combustor plenum is allowed to pass through moving blades successively to cool the moving blades, and then recovered and returned to the compressor.
摘要翻译： 燃气轮机包括：第一闭合回路，其中冷却气体被供给到壳体，允许其通过固定叶片，并且在冷却固定叶片之后被移除到壳体外部; 第二闭合回路，其中冷却空气被供给到壳体，允许通过动叶片，并且在冷却动叶片之后被移除到壳体外部; 用于冷却第一和第二闭合回路中的冷却气体的冷却器; 以及用于对由冷却器冷却的冷却气体进行加压和循环的增压器。 此外，A燃气轮机包括：第一闭合回路，其中在从燃烧室增压室抽出之后冷却的冷却空气被允许依次通过固定叶片以冷却固定叶片，然后回收并返回到压缩机的上游侧 燃烧室增压室; 以及第二闭合回路，其中冷却从冷却室抽出的冷却空气被连续通过运动叶片以冷却动叶片，然后回收并返回压缩机。
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公开(公告)号：US6050776A
公开(公告)日：2000-04-18
申请号：US152797
申请日：1998-09-14
CPC分类号： F01D5/22 , F01D9/04 , F05D2230/60
摘要： A gas turbine stationary blade unit in which two stationary blades are formed in a single segment by divided shrouds functions to lessen the occurrence of cracks. Two stationary blades 1a, 1b are fixed to an outer shroud and an inner shroud, respectively. Each shroud is divided into two sections 2a, 2b and 3a, 3b. Flanges 4a, 4b are provided to connect the section together by bolts via boltholes 7. Likewise, flanges 5a, 5b are provided to form a similar connection or joint. If the two stationary blades 1a, 1b are fixed in a single segment by the shrouds which are not divided, a restraining force becomes larger, local stress occurs due to thermal stress and the frequency of crack occurrence increases. However, since the shrouds are divided respectively into two parts and jointed together by bolts, the crack occurrence is lessened. Also, pinholes are provided in opposing faces at the divided portion of the shrouds. Also, pins are inserted into the pinholes for connection of the divided shrouds, thereby relative movement between the divided shrouds is prevented and a strong jointed blade unit is provided.
摘要翻译： 一种燃气轮机固定叶片单元，其中两个固定叶片通过分隔的护罩形成在单个段中，起到减少裂缝发生的作用。 两个固定叶片1a，1b分别固定在外护罩和内护罩上。 每个护罩分为两个部分2a，2b和3a，3b。 凸缘4a，4b被设置成通过螺栓通过螺栓孔7将部分连接在一起。同样，凸缘5a，5b被设置成形成类似的连接或接头。 如果两个固定叶片1a，1b通过未被分割的护罩固定在单个区段中，则约束力变大，由于热应力而产生局部应力，并且裂纹频率增加。 然而，由于护罩被分成两部分并且通过螺栓接合在一起，因此裂纹发生减少。 此外，在护罩的分割部分处的相对面中设置针孔。 此外，销被插入到针孔中以连接分隔的护罩，从而防止分隔的护罩之间的相对运动，并且提供强的接合的刀片单元。
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