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21. 发明授权

US06190130B1 Gas turbine moving blade platform 有权
标题翻译：燃气轮机动叶片平台
公开(公告)号：US06190130B1
公开(公告)日：2001-02-20
申请号：US09255793
申请日：1999-02-23
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2240/81
摘要： A gas turbine moving blade platform having a simplified platform cooling structure. A cooling effect of the platform side end portions is increased resulting in uniform cooling of the entire platform. Cooling passages (2, 3) are bored in the platform (1) front portion so as to communicate with a cooling air passage (52) of the moving blade (51) and open at both platform side end surfaces. The openings are closed by inserting covers (2a, 2b) therein. Cooling passages (6, 4) are bored in platform (1) side end portions so as to communicate with the front end cooling passages (2, 3), respectively, and open in the platform rear end surface. A plurality of cooling holes (5) are bored so as to communicate with the cooling passage (4) and open at the platform side end surface. Thus, the entire platform is cooled uniformly and the platform side portions are cooled by the cooling holes (5) so that an effective cooling performance is ensured and also the workability of the cooling lines is enhanced.
摘要翻译：具有简化的平台冷却结构的燃气轮机动叶片平台。平台侧端部的冷却效果增加，导致整个平台的均匀冷却。在平台（1）的前部分中钻出冷却通道（2,3），以便与活动叶片（51）的冷却空气通道（52）连通并在两个平台侧端面处打开。通过将盖（2a，2b）插入其中来封闭开口。平台（1）的侧端部分分别将冷却通道（6,4）与前端冷却通道（2,3）连通，并在平台后端面开口。多个冷却孔（5）钻孔，以与冷却通道（4）连通并在平台侧端面打开。因此，整个平台被均匀地冷却，并且平台侧部分被冷却孔（5）冷却，从而确保了有效的冷却性能，并且还提高了冷却管线的可加工性。

22. 发明授权

US6152695A Gas turbine moving blade 有权
标题翻译：燃气轮机动叶片
公开(公告)号：US6152695A
公开(公告)日：2000-11-28
申请号：US243821
申请日：1999-02-03
申请人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
发明人： Ichiro Fukue , Eiji Akita , Kiyoshi Suenaga , Yasuoki Tomita
IPC分类号： F01D5/18 , F01D5/20 , F01D5/22
CPC分类号： F01D5/187 , F01D5/225 , F05D2240/81 , F05D2260/22141
摘要： In a gas turbine moving blade 1, the convection of cooling air is promoted to enhance the heat transfer rate, the cooling effect of a shroud 2 is enhanced and the entire cooling effect of the blade is enhanced. An inner cavity 10 is formed in the blade over the entire length thereof. A multiplicity of pin fins 5 are provided in the inner cavity, being fixed to wall thereof. An enlarged cavity 6 is formed in the shroud 2 of a terminal end of the blade 1. Cooling air entering the inner cavity 10 of the blade 1 flows into the enlarged cavity 6 and flows out of the shroud 2 downwardly through holes 7 of a peripheral portion of the enlarged cavity 6. The entire portion of the shroud 2 is cooled uniformly, and the cooling effect of the entire blade is enhanced by an enhanced heat transfer rate in the blade and by uniform cooling of the entire shroud.
摘要翻译：在燃气轮机动叶片1中，促进冷却空气的对流，提高传热速度，提高护罩2的冷却效果，提高叶片的整体冷却效果。在叶片的整个长度上形成内腔10。多个销翅片5设置在内腔中，固定在其壁上。在叶片1的末端的护罩2中形成有扩大的空腔6.进入叶片1的内腔10的冷却空气流入扩大空腔6，并通过周边的孔7向下流出护罩2 扩大的腔体6的部分。护罩2的整个部分被均匀地冷却，并且整个刀片的冷却效果通过增加叶片中的传热速率和整个护罩的均匀冷却来增强。

23. 发明授权

US6142730A Gas turbine cooling stationary blade 有权
标题翻译：燃气轮机冷却固定叶片
公开(公告)号：US6142730A
公开(公告)日：2000-11-07
申请号：US202690
申请日：1998-12-21
申请人： Yasuoki Tomita , Kenichi Arase , Hiroki Fukuno , Hideki Murata , Kiyoshi Suenaga , Tsuyoshi Kitamura
发明人： Yasuoki Tomita , Kenichi Arase , Hiroki Fukuno , Hideki Murata , Kiyoshi Suenaga , Tsuyoshi Kitamura
IPC分类号： F01D9/02 , F01D5/18 , F01D9/04 , F01D9/06 , F02C7/18
CPC分类号： F01D9/065 , F01D5/187 , F05D2240/81 , Y02T50/676
摘要： In a cooled gas turbine stationary blade, both steam cooling and air cooling are utilized to reduce the amount of cooling air. In the stationary blade having outer and inner shrouds 1, 21 and steam passages 10A, 10B, 10C, 10D and 10E which are communicated with each other and in which a sealing air feed tube 2 passes through a central portion thereof, steam covers 3, 4 are provided in the outer shroud 1, and steam S is introduced from a steam feed port 5. The steam S passes through serpentine passages 10A to 10E and is recovered from the steam outlet 12 after cooling the central portion of the outer shroud 1 by means of an impingement plate 8. A portion of the steam of the passage 10A is introduced from the impingement plate 25 to a steam sump 24 to cool the central portion of the inner shroud 21 and pass through the passage 10D to be recovered from the steam outlet port 12. On the other hand, cooling air is fed from cooling air feed ports 6 and 26 to peripheral portions of the outer and inner shrouds 1, 21, and is discharged to the outside from the rear sides thereof, respectively, and the cooling air is further fed from a cooling air feeding port 7 to the passage 10E on the rear edge of the blade to cool the rear edge of the blade. Only the narrow portions where it is difficult for the steam to pass are air-cooled to thereby reduce the amount of the cooling air.
摘要翻译： PCT No.PCT / JP98 / 01959 Sec。 371 1998年12月21日第 102（e）日期1998年12月21日PCT提交1998年4月28日PCT公布。公开号WO98 / 50685 PCT 日期1998年11月12日在冷却式燃气轮机固定叶片中，蒸汽冷却和空气冷却都用于减少冷却空气的量。在具有彼此连通并且密封空气供给管2穿过其中心部分的外护罩1和21以及蒸汽通道10A，10B，10C，10D和10E的固定刀片中，蒸汽罩3， 4设置在外护罩1中，并且蒸汽S从蒸汽供给口5引入。蒸汽S通过蛇形通道10A至10E，并且在冷却外护罩1的中心部分之后从蒸汽出口12回收，冲击板8的装置。通道10A的蒸汽的一部分从冲击板25引入蒸汽槽24，以冷却内护罩21的中心部分，并通过通道10D以从蒸汽中回收另一方面，冷却空气从冷却空气供给口6和26被供给到外护罩1和外护罩21的周边部分，并且分别从其后侧排出到外部，冷却空气很冷她从冷却空气供给口7进入叶片后缘的通道10E，以冷却叶片的后边缘。只有蒸汽难以通过的狭窄部分被空气冷却，从而减少冷却空气的量。

24. 发明申请

US20100226791A1 BLADE COOLING STRUCTURE OF GAS TURBINE 有权
标题翻译：气体涡轮叶片冷却结构
公开(公告)号：US20100226791A1
公开(公告)日：2010-09-09
申请号：US12670912
申请日：2007-08-30
申请人： Daigo Fujimura , Hideaki Sugishita , Masaaki Matsuura , Hiroyuki Yamamoto , Shunsuke Torii , Satoshi Hada , Kiyoshi Suenaga , Yuko Suenaga
发明人： Daigo Fujimura , Hideaki Sugishita , Masaaki Matsuura , Hiroyuki Yamamoto , Shunsuke Torii , Satoshi Hada , Kiyoshi Suenaga , Yuko Suenaga
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/127 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage (15) for flowing cooling air (A) from a proximal end portion (12) toward a blade portion (14) of a moving blade (11), a plurality of turbulators (21) arranged, on both wall surfaces of the cooling passage (15) opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples (22) formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage (15) between the adjacent turbulators (21).
摘要翻译：提供了一种燃气轮机的叶片冷却结构，其可以在不降低传热系数的情况下降低冷却介质的压力损失。叶片冷却结构包括用于使冷却空气（A）从基端部（12）朝向活动叶片（11）的叶片部分（14）流动的冷却通道（15），多个湍流器（21）在相对于冷却空气（A）的流动方向倾斜的方式相互相对的冷却通路（15）的两壁面上形成有多个凹部（22），形成在下游区域（N）在冷却空气（A）的流动方向上在相邻的湍流器（21）之间的冷却通道（15）的壁表面上的中心位置（O）的下游。

25. 发明申请

US20100137498A1 RESIN COMPOSITION AND RESIN PRODUCT 失效
标题翻译：树脂组合物和树脂产品
公开(公告)号：US20100137498A1
公开(公告)日：2010-06-03
申请号：US12452663
申请日：2008-08-08
申请人： Masao Kobayashi , Koichi Ogiso , Katsushi Ito , Kiyoshi Suenaga
发明人： Masao Kobayashi , Koichi Ogiso , Katsushi Ito , Kiyoshi Suenaga
IPC分类号： C08K3/34
CPC分类号： C08L23/10 , C08K3/346 , C08L23/0815 , C08L23/12 , C08L23/16 , C08L53/00 , C08L53/025 , C08L2205/03 , C08L2666/02
摘要： A resin composition is provided which is improved in fluidability, stiffness and impact resistance and therefore can achieve the reduction in wall thickness of a resin product for automotive interior/exterior applications comprising a polypropylene resin; and a resin product produced from the resin composition.The resin composition comprises 30 to 65 mass % of an ethylene-propylene block copolymer having a melt flow rate of 60 to 120 g/10 minutes and a Charpy impact strength of 3 kJ/m2 or more; 0 to 25 mass % of a homopolypropylene resin having a melt flow rate of 10 g/10 minutes or more and a modulus of elasticity of 2000 MPa or more; 5 to 20 mass % of an ethylene-α-olefin copolymer rubber having a Mooney viscosity of 20 to 75 or a styrene-ethylene butylenes-styrene copolymer having a styrene component content of 15 to 30 mass %; and 23 to 37 mass % of talc having an average particle diameter of 8 μm or less.
摘要翻译：提供一种提高了流动性，刚度和耐冲击性的树脂组合物，因此可以实现包含聚丙烯树脂的汽车内部/外部应用的树脂制品的壁厚减小; 和由树脂组合物制成的树脂产品。树脂组合物含有30〜65质量％的熔体流动速率为60〜120g / 10分钟，夏比冲击强度为3kJ / m 2以上的乙烯·丙烯嵌段共聚物， 0〜25质量％的熔体流动速率为10g / 10分钟以上，弹性模量为2000MPa以上的均聚丙烯树脂; 5至20质量％的门尼粘度为20至75的乙烯-α-烯烃共聚物橡胶或苯乙烯组分含量为15-30质量％的苯乙烯 - 乙烯丁烯 - 苯乙烯共聚物; 和23〜37质量％的平均粒径为8μm以下的滑石。

26. 发明申请

US20090019674A1 Clip attaching seat of vehicular interior molded product 审中-公开
标题翻译：夹紧车辆内部模制产品的座椅
公开(公告)号：US20090019674A1
公开(公告)日：2009-01-22
申请号：US12216620
申请日：2008-07-08
申请人： Takahiko Sato , Shuji Inui , Shigeru Yabuya , Kiyoshi Suenaga
发明人： Takahiko Sato , Shuji Inui , Shigeru Yabuya , Kiyoshi Suenaga
IPC分类号： A44B21/00
CPC分类号： F16B21/09 , B60R13/0206 , F16B21/086 , Y10T24/30
摘要： In a clip attaching seat 1 integrally provided to a vehicular interior molded product and attached with a clip having a locking head portion of a bulged shape above a neck portion, on a face of a seating portion 11 in a plate-like shape formed with a clip locking hole 12, ribs (14 through 16) having widths the same as a plate thickness thereof are formed. Thereby, a rigidity of the thin-walled seating portion 11 is ensured while making a wall thickness of a total of the clip attaching seat 1 constant.
摘要翻译：在一体地设置在车辆内部模制产品上的夹子安装座1上，并且具有在颈部上方具有凸起形状的锁定头部的夹子，在座形部分11的表面上形成为板状形状，形成夹具锁定孔12，具有与其板厚相同的宽度的肋（14至16）。由此，可确保薄壁座部11的刚性，同时使夹子安装座1的总体壁厚恒定。

27. 发明授权

US6099253A Gas turbine rotor blade 有权
标题翻译：燃气轮机转子叶片
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
IPC分类号： F01D5/18 , F01D5/20 , F02C7/18
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。

28. 发明授权

US6077034A Blade cooling air supplying system of gas turbine 失效
标题翻译：燃气轮机叶片冷却空气供应系统
公开(公告)号：US6077034A
公开(公告)日：2000-06-20
申请号：US38451
申请日：1998-03-11
申请人： Yasuoki Tomita , Hiroki Fukuno , Yukihiro Hashimoto , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Yukihiro Hashimoto , Kiyoshi Suenaga
IPC分类号： F01D5/08 , F01D5/18 , F01D9/02 , F01D9/04 , F01D9/06 , F01D11/04 , F02C7/18
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。

29. 发明授权

US6036440A Gas turbine cooled moving blade 失效
标题翻译：燃气轮机冷却动叶片
公开(公告)号：US6036440A
公开(公告)日：2000-03-14
申请号：US53559
申请日：1998-04-01
申请人： Yasuoki Tomita , Hiroki Fukuno , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Kiyoshi Suenaga
IPC分类号： F01D5/18 , F02C7/18 , F01D5/08
CPC分类号： F01D5/187 , B22C21/14 , F05D2260/22141 , F05D2260/2322
摘要： The present invention relates to a gas turbine cooled moving blade in order to cool the gas turbine using steam alone. In the moving blade, two cavities are installed in the lower part of the moving blade root section of the moving blade, a steam inlet is located in one cavity, and a steam outlet is installed in the other cavity. Steam is charged from the steam inlet and passes through a serpentine cooling passage consisting of a plurality of steam passages, and discharged to the steam outlet and collected. Bypasses are located near the base of the moving blade in the middle of each steam passage, so that cold steam on the leading edge side can be led into the bypass, mixed with the hot steam which comes from the tip section side and goes into the next downstream section of the steam passage, and flows to an upstream portion of the steam passage, thereby equalizing the steam temperature and cooling the steam over the entire range from the upstream to downstream of the steam flow. A turbulator is installed in the middle of steam passage in order to generate turbulence and enhance heat transfer. Since the moving blade is evenly cooled by steam alone without using air, and the steam is then collected, the performance of the gas turbine can be enhanced.
摘要翻译：本发明涉及一种燃气轮机冷却的动叶片，以便仅使用蒸汽冷却燃气轮机。在移动叶片中，两个空腔安装在动叶片的动叶片根部的下部，蒸汽入口位于一个空腔中，蒸汽出口安装在另一腔中。蒸汽从蒸汽入口充入，并通过由多个蒸汽通道组成的蛇形冷却通道，并排放到蒸汽出口并收集。旁路位于每个蒸汽通道中间的移动叶片的基部附近，使得前缘侧的冷蒸汽可以被引导到旁路中，与来自尖端部分侧的热蒸汽混合并进入蒸汽通道的下游下游部分，并且流到蒸汽通道的上游部分，从而在蒸汽流的上游到下游的整个范围内均衡蒸汽温度并冷却蒸汽。湍流器安装在蒸汽通道的中部，以产生湍流并增强热传递。由于移动叶片在不使用空气的情况下均匀地被蒸汽均匀地冷却，所以随后收集蒸汽，可以提高燃气轮机的性能。

30. 发明授权

US06036436A Gas turbine cooling stationary vane 有权
标题翻译：燃气轮机冷却静止叶片
公开(公告)号：US06036436A
公开(公告)日：2000-03-14
申请号：US155787
申请日：1998-10-02
申请人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
发明人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
IPC分类号： F01D5/20 , F01D5/18 , F01D9/02 , F02C7/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2322
摘要： There is provided a cooled stationary blade of a gas turbine in which the portions which can be cooled sufficiently by air are air-cooled, and the portions which are difficult to cool by air are steam-cooled, by which high temperatures can be overcome. In a stationary blade 1, there is formed a serpentine passage 3 in which cooling steam flows and an air passage 10 adjacent to the trailing edge portion and separated from the serpentine passage 3. Also, an outside shroud 4 is formed with an air cooling passage 16 at the outer edge portion and a steam impingement cooling portion 17 and an air impingement cooling portion 18 on the inside of the air cooling passage 16. An inside shroud 11 is provided with an air cooling passage 19 at the outer edge portion and shaped holes 20 formed on the inside of the air cooling passage 19. The air flowing out through the shaped holes 20 performs film cooling.
摘要翻译： PCT No.PCT / JP98 / 00206 Sec。 371日期：1998年10月2日 102（e）1998年10月2日日期PCT提交1998年1月21日PCT公布。公开号WO98 / 34013 日本1998年8月6日提供了一种燃气轮机的冷却固定叶片，其中可由空气充分冷却的部分被空气冷却，并且由空气难以冷却的部分被蒸汽冷却，由此高温度可以克服。在固定叶片1中，形成有冷却蒸汽流过的蛇形通道3和与后缘部分相邻并与蛇形通道3分离的空气通道10.另外，外部护罩4形成有空气冷却通道 16和外侧边缘部分的蒸汽冲击冷却部分17和空气冷却通道16内部的空气冲击冷却部分18.内部护罩11在外边缘部分设有空气冷却通道19， 20形成在空气冷却通道19的内部。通过成形孔20流出的空气进行膜冷却。

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