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公开(公告)号：US06196798B1
公开(公告)日：2001-03-06
申请号：US09242330
申请日：1999-02-11
IPC分类号： F01D518
摘要： A number of air-transpiration holes (4) are provided at a leading edge portion (2) of a cooled blade (1). Cooling air flowing through a cooling air passage (15) formed inside of the blade blows out to the blade surface of the leading edge portion (2) of the cooled blade (1) by way of the air-transpiration holes (4), to thereby shower-head cool the surface of the leading edge portion (2). The air-transpiration holes (4) are formed so as to extend substantially orthogonal to the leading edge surface of the cooled blade (1) such that the acute-angled portions are eliminated, whereby thermal stress is reduced and cracking is prevented.
摘要翻译： 在冷却叶片（1）的前缘部分（2）处设置有多个空气蒸发孔（4）。 流过形成在叶片内的冷却风道（15）的冷却空气通过空气蒸发孔（4）吹向冷却叶片（1）的前缘部（2）的叶片表面，至 从而喷淋头对前缘部分（2）的表面进行冷却。 空气蒸发孔（4）形成为基本上垂直于冷却叶片（1）的前缘表面延伸，使得锐角部分被消除，从而减少热应力并防止开裂。
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公开(公告)号：US06196791B1
公开(公告)日：2001-03-06
申请号：US09202951
申请日：1998-12-23
申请人： Yasuoki Tomita , Hiroki Fukuno , Sunao Aoki , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Sunao Aoki , Kiyoshi Suenaga
IPC分类号： F01D518
摘要： In gas turbine cooled moving blade, a cooling air passage is made shortest and temperature elevation and pressure drop of the cooling air are suppressed. The cooling air passage (16) is bored in a turbine cylinder wall (15) located below a first stage stationary blade (11). The cooling air passage (16) communicates at one end (16a) with a turbine cylinder and at the other end (16b) with a space (13) between the stationary blade and the moving blade. The passage (16) is directed to an air inflow hole (6) provided in a shank portion (4) of a lower portion of a platform (2) of the moving blade (1). Cooling air is jetted from the cooling air passage (16) toward the air inflow hole (6) so as to flow into the shank portion (4) and then into the moving blade (1) for cooling thereof. An axis (17) of the cooling air passage (16) is directed so as to deviate in a rotational circumferential direction by an angle determined by the velocity of the cooling air jetted from the cooling air passage (16) and the rotational velocity of the moving blade (1) from position of the air inflow hole when the moving blade (1) stands still in row with the stationary blade (11) in rotor axial direction. Thus, the cooling air can be jetted in an optimal direction with the shortest distance, and the temperature elevation and pressure drop of the cooling air can be suppressed to minimum.
摘要翻译： 在燃气轮机冷却动叶片中，冷却空气通道最短，并且冷却空气的温度升高和压降被抑制。 冷却空气通道（16）在位于第一级固定叶片（11）下方的涡轮机气缸壁（15）中钻孔。 冷却空气通道（16）在一端（16a）与涡轮机气缸连通，另一端（16b）在固定叶片和动叶片之间具有空间（13）。 通道（16）被引导到设置在活动叶片（1）的平台（2）的下部的柄部分（4）中的空气流入孔（6）。 冷却空气从冷却空气通路（16）向空气流入孔（6）喷射，从而流入柄部（4），然后进入动叶片（1）进行冷却。 冷却空气通路16的轴线（17）被引导为以从冷却空气通路（16）喷射的冷却空气的速度和旋转速度确定的旋转圆周方向偏离角度 当动叶片（1）在转子轴向与静叶片（11）静置时，从动空气流入孔的位置移动叶片（1）。 因此，可以以最短的距离沿最佳方向喷射冷却空气，并且可以将冷却空气的温度升高和压降降低到最小。
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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
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。
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公开(公告)号：US6089826A
公开(公告)日：2000-07-18
申请号：US180469
申请日：1998-11-09
申请人： Yasuoki Tomita , Sunao Aoki , Hiroki Fukuno , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Sunao Aoki , Hiroki Fukuno , Kiyoshi Suenaga
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141
摘要： A gas turbine cooled blade has leading edge turbulators. A rounded tip portion of the leading edge portion cooling passage (3) is approximated by a triangular cooling passage (1) having orthogonal turbulators (11, 12) and a smoothly curved rear portion thereof of the leading edge portion cooling passage (3) is approximated by a square cooling passage 2 having oblique turbulators (13, 14).
摘要翻译： PCT No.PCT / JP98 / 01482 Sec。 371日期：1998年11月9日 102（e）1998年11月9日PCT PCT 1998年3月31日PCT公布。 第WO98 / 44241号公报 日期1998年10月8日燃气轮机冷却叶片具有前缘湍流器。 前缘部分冷却通道（3）的圆形末端部分由具有正交湍流器（11,12）的三角形冷却通道（1）近似，其前缘部分冷却通道（3）的平滑弯曲的后部是 由具有倾斜湍流器（13,14）的方形冷却通道2近似。
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公开(公告)号：US06264426B1
公开(公告)日：2001-07-24
申请号：US09026643
申请日：1998-02-20
申请人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
发明人： Hiroki Fukuno , Yasuoki Tomita , Kiyoshi Suenaga
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2322
摘要： In cooling a gas turbine stationary blade, steam and air are used as cooling media, the steam is recovered surely without leakage and used effectively, and the amount of air required for cooling is decreased to provide a margin for combustion air, by which the gas turbine efficiency is improved. A steam cooling section is provided at the rear from the blade leading edge, and an air cooling section is provided at the blade trailing edge. The steam cooling is effected by cooling the blade by the cooling steam flowing in the serpentine flow path having turbulators after impingement cooling of an outside shroud and by impingement-cooling an inside shroud during the cooling process, the cooling steam being led to a recovery section from the outside shroud. On the other hand, the air cooling section consists of an air flow path extending from the outside shroud to the inside shroud and slot cooling at the blade trailing edge. Thus, the stationary blade is cooled by both of the steam cooling section and air cooling section.
摘要翻译： 在冷却燃气轮机固定叶片时，蒸汽和空气被用作冷却介质，蒸汽被确保地回收而没有泄漏并被有效地使用，并且减少冷却所需的空气量以提供燃烧空气的余量，由此气体 提高了涡轮效率。 在叶片前缘的后部设有蒸汽冷却部，在叶片后缘设有空气冷却部。 蒸汽冷却通过在具有湍流器的蛇形流动路径中流动的冷却蒸汽在外部护罩的冲击冷却之后冷却叶片并且在冷却过程中通过冲击冷却内部护罩来实现，冷却蒸汽被引导到回收部分 从外面的围墙。 另一方面，空气冷却部由从外侧护罩延伸到内部护罩的气流路径和在叶片后缘的冷却槽构成。 因此，固定叶片由蒸汽冷却部分和空气冷却部分两者冷却。
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公开(公告)号：US06217279B1
公开(公告)日：2001-04-17
申请号：US09230820
申请日：1999-02-10
申请人： Toshishige Ai , Masanori Yuri , Yasuoki Tomita , Kiyoshi Suenaga , Sunao Aoki , Hiroki Fukuno
发明人： Toshishige Ai , Masanori Yuri , Yasuoki Tomita , Kiyoshi Suenaga , Sunao Aoki , Hiroki Fukuno
IPC分类号： F01D518
CPC分类号： F01D9/065 , F01D11/001 , F02C7/18
摘要： A sealing device for a gas turbine stator blade, in which an outer shroud (32) is mounted by heat insulating rings (32a,32b) on a blade ring (50). The blade ring (50) has a first air hole (1), which communicates with a space (53), and a second air hole (51), which communicates with a seal tube (2). The seal tube (2) is inserted into the second air hole (51), and a spring (6) is arranged between a projection (4) of the tube (2) and a retaining portion (5) of the air hole (51) to removably secure the seal tube (2). Cooling air (54) flows through the first air hole (1) to cool the shrouds and the inside of a stator blade (31) until it is released from the trailing edge of the blade. The cooling air also flows into a cavity (36) so that a high pressure can be maintained without a pressure loss because the tube (2) is independent of the space (53) in the blade ring.
摘要翻译： 一种用于燃气轮机定子叶片的密封装置，其中外护罩（32）通过隔离环（32a，32b）安装在叶片环（50）上。 叶片环（50）具有与空间（53）连通的第一空气孔（1）和与密封管（2）连通的第二空气孔（51）。 密封管（2）插入到第二空气孔（51）中，弹簧（6）布置在管（2）的突出部（4）和气孔（51）的保持部分（5）之间 ）以可拆卸地固定密封管（2）。 冷却空气（54）流过第一空气孔（1）以冷却护罩和定子叶片（31）的内部，直到其从叶片的后缘释放。 冷却空气也流入空腔（36），从而由于管（2）独立于叶片环中的空间（53）而能够保持高压而没有压力损失。
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公开(公告)号：US06190128B1
公开(公告)日：2001-02-20
申请号：US09230942
申请日：1999-02-04
IPC分类号： F01D508
摘要： A cooled moving blade for a gas turbine which has a blade profile capable of more effectively reducing thermal stress in a blade base portion and, thus, preventing cracks from occurring. A moving blade (1) is fixedly secured to a platform (2). On the other hand, a cooling air passage (3) is formed in a serpentine pattern inside of the blade for cooling with cooling air. The moving blade (1) has a base portion of a profile formed by an elliptically curved surface (11) and a rectilinear surface portion (12), wherein the rectilinear surface portion (12) is provided at a hub portion of the blade where thermal stress is large. The cross-sectional area of the blade is increased by providing the rectilinear surface portion (12) The heat capacity is increased, compared with the conventional blade, due to the increased cross-sectional area of the blade. This, in turn, results in a decrease of the temperature difference due to the thermal stress. Thus, the thermal stress can be suppressed more effectively than with the conventional blade.
摘要翻译： 一种用于燃气轮机的冷却的移动叶片，其具有能够更有效地降低叶片基部中的热应力并因此防止裂纹发生的叶片轮廓。 活动叶片（1）固定地固定到平台（2）上。 另一方面，冷却空气通路（3）形成为叶片内的蛇形图案，用冷却空气冷却。 活动叶片（1）具有由椭圆曲面（11）和直线表面部分（12）形成的轮廓的基部，其中直线表面部分（12）设置在叶片的毂部，其中热 压力很大 通过提供直线表面部分（12）来提高叶片的横截面面积。与常规叶片相比，由于叶片的横截面面积增加，热容量增加。 这又导致由于热应力引起的温度差的降低。 因此，与常规叶片相比，可以更有效地抑制热应力。
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公开(公告)号：US06189891B1
公开(公告)日：2001-02-20
申请号：US09028664
申请日：1998-02-24
申请人： Yasuoki Tomita , Kazuharu Hirokawa , Hiroki Fukuno , Kiyoshi Suenaga , Yukihiro Hashimoto , Eisaku Ito
发明人： Yasuoki Tomita , Kazuharu Hirokawa , Hiroki Fukuno , Kiyoshi Suenaga , Yukihiro Hashimoto , Eisaku Ito
IPC分类号： F16J15447
CPC分类号： F01D11/02 , F01D11/001
摘要： A gas turbine seal structure provided between end portions of a moving blade platform and a stationary blade inside shroud. The sealing performance of the seal structure is improved by increasing the resistance to the flow of air. A seal plate (21, 31) is mounted to an end portion of a platform (2, 2′) of the moving blade (1) and a seal portion is formed by seal fins (22, 32) and a honeycomb seal (16, 17) disposed on a lower surface of an end portion (12a, 12b) of an inside shroud (12) of a stationary blade (11). Sealing air from the stationary blade (11) produces a high temperature in a cavity (14) and flows into a space (18, 19), and also air leaking from the cooling air of the moving blade (1) is able to escape into a high temperature combustion gas passage through a seal portion. However, since the seal plate has three seal fins (22, 32) that are inclined in a direction so as to oppose the air flow, air resistance is increased and the flow of air into the combustion gas passage is prevented.
摘要翻译： 一种燃气轮机密封结构，其设置在活动叶片平台的端部和固定叶片内部的护罩内。 通过增加对空气流动的阻力来改善密封结构的密封性能。 密封板（21,31）安装在活动叶片（1）的平台（2,2'）的端部，密封部分由密封翅片（22,32）和蜂窝密封件（16）形成 ，17），其设置在固定叶片（11）的内侧护罩（12）的端部（12a，12b）的下表面上。 来自固定叶片（11）的密封空气在空腔（14）中产生高温并流入空间（18,19），并且从活动叶片（1）的冷却空气泄漏的空气也能够逸出 通过密封部分的高温燃烧气体通道。 然而，由于密封板具有在与空气流相对的方向上倾斜的三个密封翅片（22,32），因此空气阻力增加，并且防止了进入燃烧气体通道的空气流。
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公开(公告)号：US6099244A
公开(公告)日：2000-08-08
申请号：US38376
申请日：1998-03-11
申请人： Yasuoki Tomita , Hiroki Fukuno , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Kiyoshi Suenaga
CPC分类号： F01D5/18 , F02D9/02 , F05D2260/22141 , Y02T10/14
摘要： In the present invention, seal air passes through a tube extending in a stationary blade from an outside shroud to an inside shroud, flows into a cavity to keep the pressure in the cavity high so as to seal the high-temperature combustion gas, and is discharged to a passage. Part of cooling air flows into an air passage to cool the leading edge portion, passes through the peripheral portion of the inside shroud to cool the same, and is discharged to a passage. The remaining cooling air flows into a passage, passes through a serpentine cooling flow path consisting of air passages having turbulators, and is discharged through air cooling holes formed at the trailing edge. The cooling air passing through the passage at the leading edge portion cools the peripheral portion of the inside shroud as well as the leading edge portion of blade, by which the cooling efficiency is increased.
摘要翻译： 在本发明中，密封空气通过从外侧护罩延伸到内侧护罩的固定刀片的管道流入空腔，以将空腔内的压力保持在较高高度以密封高温燃烧气体，并且是 排到通道。 一部分冷却空气流入空气通道以冷却前缘部分，通过内侧护罩的周边部分使其冷却，并且排出到通道中。 剩余的冷却空气流入通道，通过由具有湍流器的空气通道组成的蛇形冷却流路，并通过形成在后缘的空气冷却孔排出。 通过前缘部分的通道的冷却空气冷却内部护罩的周边部分以及叶片的前缘部分，从而冷却效率提高。
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公开(公告)号：US5997245A
公开(公告)日：1999-12-07
申请号：US64987
申请日：1998-04-23
申请人： Yasuoki Tomita , Hiroki Fukuno , Hideki Murata , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Hiroki Fukuno , Hideki Murata , Kiyoshi Suenaga
CPC分类号： F01D9/041 , F01D5/187 , F05D2240/81 , F05D2260/2212
摘要： The invention relates to a cooled shroud in a gas turbine stationary blade which is able to flow a cooling air in the entire area of an inner shroud for cooling thereof. Three stationary blades are fixed to the inner shroud 2, a cover 13, 14 is provided to form a space 21 and space 22a, 22b and 22c, respectively. The cooling air is introduced through an independent air passage 3A of a leading edge of each stationary blade into the spaces 22a, 22b and 22c and is flown therefrom through a tunnel 18 and air reservoirs 19-2, 19-3 and 19-4 to be blown out of a trailing edge while cooling surfaces of the shrouds and the trailing edges. Also, a portion of the cooling air from the space 22b is flown into the space 21 through a tunnel 11, a leading edge side passage 12 and an endmost tunnel 11 and is then blown out of the trailing edge through a tunnel 18 and an air reservoir 19-1, so that the leading edge portion, the endmost portion and the endmost trailing edge portion are cooled. By use of the independent air passage, the cooling air is introduced to cool the entire area of the shroud.
摘要翻译： 本发明涉及一种能够在内护罩的整个区域内流动冷却空气的燃气轮机固定叶片中的冷却罩，用于冷却。 三个固定叶片固定在内护罩2上，盖13,14设置成分别形成空间21和空间22a，22b和22c。 冷却空气通过每个固定叶片的前缘的独立空气通道3A引入空间22a，22b和22c中，并且通过隧道18和空气储存器19-2,19-3和19-4从其中流动到 从后缘吹出，同时冷却护罩和后缘的表面。 此外，来自空间22b的一部分冷却空气通过隧道11，前缘侧通道12和最终通道11流入空间21，然后通过隧道18和空气吹出后缘 储存器19-1，使得前缘部分，最末端部分和最末端后缘部分被冷却。 通过使用独立的空气通道，引入冷却空气以冷却护罩的整个区域。
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