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21. 发明授权

US6132173A Cooled platform for a gas turbine moving blade 失效
标题翻译：用于燃气轮机动叶片的冷却平台
公开(公告)号：US6132173A
公开(公告)日：2000-10-17
申请号：US42701
申请日：1998-03-17
申请人： Yasuoki Tomita , Hiroki Fukuno , Kenichi Arase , Toshiaki Sano
发明人： Yasuoki Tomita , Hiroki Fukuno , Kenichi Arase , Toshiaki Sano
IPC分类号： F01D5/08 , F01D5/18 , F01D5/30 , F02C3/30 , F02C7/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/2212 , F05D2260/2322
摘要： A cooled platform for a gas turbine moving blade which enables the platform to be cooled when the moving blade is cooled by steam. The moving blade is provided with a plurality of steam passages. Steam is introduced from the steam passage at the trailing edge portion, flows in a serpentine passage composed of other steam passages to cool the blade, and flows out to a blade root portion from a base portion of the steam passage at the leading edge portion, being recovered. Part of steam flowing into the platform from the base portion of the steam passage at the trailing edge portion enters first and second steam passages in the platform. On one side, the steam passes through first, third, and fourth steam passages, and on the other hand, the steam passes through second, fifth, and sixth steam passages. The steam is recovered together with the steam having cooled the blade at the base portion of steam passage at the leading edge portion. Therefore, the peripheral portion of a platform can be cooled by steam, air is not needed, and the platform can be cooled by steam when the steam cooling system is used to cool the blade.
摘要翻译：一种用于燃气轮机移动叶片的冷却平台，其使得当移动叶片由蒸汽冷却时能够使平台冷却。动叶片设有多个蒸汽通道。蒸汽从后缘部分的蒸汽通道引入，在由其他蒸汽通道组成的蛇形通道中流动以冷却叶片，并从前缘部分的蒸汽通道的基部部分流出到叶片根部，正在恢复。在后缘部分从蒸汽通道的基部流入平台的蒸汽的一部分进入平台中的第一和第二蒸汽通道。蒸汽一方面通过第一，第三和第四蒸汽通道，另一方面蒸汽通过第二，第五和第六蒸汽通道。蒸汽与在前缘部分处的蒸汽通道的基部处将叶片冷却的蒸汽一起回收。因此，平台的周边部分可以被蒸汽冷却，不需要空气，并且当蒸汽冷却系统用于冷却叶片时，平台可以被蒸汽冷却。

22. 发明授权

US6079944A Gas turbine stationary blade double cross type seal device 有权
标题翻译：燃气轮机固定叶片双十字型密封装置
公开(公告)号：US6079944A
公开(公告)日：2000-06-27
申请号：US175990
申请日：1998-10-21
申请人： Yasuoki Tomita , Kenichi Arase , Naoki Hagi , Hiroki Fukuno
发明人： Yasuoki Tomita , Kenichi Arase , Naoki Hagi , Hiroki Fukuno
IPC分类号： F01D9/02 , F01D11/00 , F02C7/28 , F01D9/04
CPC分类号： F01D11/005 , F05D2240/10 , F05D2240/11
摘要： Seal plates for gas turbine stationary blade inner shrouds are made in a double cross type seal structure with a view to enhance sealing ability. Seal plates 1, 2 are mutually lapped and disposed in a turbine axial direction between inner shrouds 12 of stationary blades 11. End portion seal plate 5 is lapped on an end portion of the seal plate 2 and end portion seal plate 6 is lapped under an end portion of the seal plate 1. All these seal plates are fitted with their side end portions being inserted into groove 9a provided in the inner shrouds 12. Seal plates 3, 4 and seal plates 7, 8 engaged with the seal plates 3, 4 are also fitted between flange portions of the inner shrouds 12 with their side end portions being inserted into grooves 10a, 10b and grooves 9b, 9c, respectively. All the seal plates 1 to 8 are fitted between mutually opposing inner shrouds in turbine circumferential direction so as to cover cavity 24 between mutually adjacent shrouds, so that gaps between engaged portions of each seal plate and between the seal plates and seal ring support ring 13 are eliminated, thereby seal air 20 is prevented from leaking from the cavity 24.
摘要翻译：用于燃气轮机固定叶片内护罩的密封板以双交叉密封结构制成，以提高密封能力。密封板1,2在固定叶片11的内护罩12之间相互重叠配置在涡轮轴向。端部密封板5在密封板2的端部上搭接，并将端部密封板6在所有这些密封板都装配有它们的侧端部插入到设置在内罩12中的槽9a中。密封板3,4和与密封板3,4接合的密封板7,8 也装配在内护罩12的凸缘部分之间，其侧端部分别插入槽10a，10b和槽9b，9c中。所有的密封板1至8均安装在涡轮机周向上相互相对的内护罩之间，以便覆盖彼此相邻的护罩之间的空腔24，使得每个密封板的接合部分之间以及密封环和密封环之间的间隙支撑环13 被消除，从而防止密封空气20从空腔24泄漏。

23. 发明授权

US6152690A Sealing apparatus for gas turbine 有权
标题翻译：燃气轮机密封装置
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
IPC分类号： F01D5/30 , F01D11/00 , F01D11/02 , F01D11/04 , F01D11/12 , F02C7/28 , F01D5/00
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）。

24. 发明授权

US6086329A Seal plate for a gas turbine moving blade 失效
标题翻译：用于燃气轮机动叶片的密封板
公开(公告)号：US6086329A
公开(公告)日：2000-07-11
申请号：US38070
申请日：1998-03-11
申请人： Yasuoki Tomita , Hiroki Fukuno , Eisaku Ito
发明人： Yasuoki Tomita , Hiroki Fukuno , Eisaku Ito
IPC分类号： F01D5/22 , F01D5/02 , F01D11/00 , F01D11/04 , F02C7/28
CPC分类号： F01D11/006
摘要： A seal plate at the platform portion of a gas turbine moving blade. The seal plate is inserted in a gap between the adjacent platforms at each end portion of a seal pin to prevent air from leaking to the outside. A groove is provided at each of four corners of the end portion of platform of the moving blade, and the seal plate is inserted to cover the gap so as to extend the end portions of the adjacent platforms, by which the gap between the platforms is blocked. A seal pin and end seal pins are inserted between the platforms to seal this portion. However, there is a gap at the end portions, so that cooling air leaks from the lower part of platform. Since the seal plate is inserted in the groove to block the gap, the sealing property is increased.
摘要翻译：在燃气轮机动叶片的平台部分处的密封板。密封板在密封销的每个端部处插入相邻平台之间的间隙中，以防止空气泄漏到外部。在活动叶片的平台的端部的四个角部的每一个处设置有凹槽，并且插入密封板以覆盖间隙，以延伸相邻平台的端部，由此平台之间的间隙为被阻止密封销和端部密封销插入平台之间以密封该部分。然而，在端部处存在间隙，使得冷却空气从平台的下部泄漏。由于密封板插入凹槽以阻挡间隙，所以密封性能增加。

25. 发明授权

US6089822A Gas turbine stationary blade 有权
标题翻译：燃气轮机固定叶片
公开(公告)号：US6089822A
公开(公告)日：2000-07-18
申请号：US179816
申请日：1998-10-28
申请人： Hiroki Fukuno
发明人： Hiroki Fukuno
IPC分类号： F01D9/02 , F01D5/18 , F01D9/04 , F01D9/06 , F02C7/18 , F01D5/14
CPC分类号： F01D5/189 , F01D9/065 , F05D2240/81
摘要： A gas turbine second stage stationary blade has cooling air passages of an inner shroud provided with enhanced cooling efficiency. In inner shroud 126, there are provided a leading edge passage 42 and trailing edge passage 44, both extending from blade portion and mutually separated by a rib 40, and impingement plates 83, 84 having a multiplicity of small holes 101. An opening portion 68 between the blade portion and the inner shroud 126 is closed by a bottom plate 150 and, together with a recess portion 100 at a bottom portion of the leading edge passage 42, connects to a passage 188 of a leading edge portion 41 via a passage 90'. Air from the trailing edge passage 44 flows into cavity 45 to be injected through the small holes 101 of the impingement plates 83, 84 for cooling of the central portion of the inner shroud 126 and is then discharged as air 60 through passages 92 of the trailing edge portion 43. The entire amount of air from the leading edge passage 42 enters the passage 188 is then enhanced in heat transfer effect by turbulators 200, further flows separately into passages 93, 94 of side edge portions for cooling therearound, and is then discharged as air 61. The air amount in the leading edge portion 41 and the side edge portions is increased and the cooling effect is enhanced.
摘要翻译：燃气轮机第二级固定叶片具有提供了增强的冷却效率的内护罩的冷却空气通道。在内护罩126中，设置有从叶片部分延伸并由肋40相互分离的前缘通道42和后缘通道44以及具有多个小孔101的冲击板83,84。开口部分68 在叶片部分和内护罩126之间由底板150封闭，并且与前缘通道42的底部处的凹部100一起通过通道90连接到前缘部分41的通道188 '。来自后缘通道44的空气流入空腔45以通过冲击板83,84的小孔101注入，用于冷却内护罩126的中心部分，然后通过尾部的通道92排出空气60。然后从前缘通道42进入通道188的全部空气通过湍流器200的传热效应增强，另外分别流入侧边缘部分的通道93,94以便在其周围冷却，然后排出作为空气61.前缘部41和侧缘部的空气量增加，冷却效果提高。

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