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公开(公告)号：US06224327B1
公开(公告)日：2001-05-01
申请号：US09250733
申请日：1999-02-16
IPC分类号： F04D2958
CPC分类号： F01D5/085 , F02C7/16 , F05D2260/2322
摘要： A steam-cooling gas turbine in which cooling steam is fed from a center portion of a rotating shaft and recovered through passages disposed at the outer side of the center portion with steam leaking through a seal portion from a feeding steam being effectively recovered. Feed steam (30) serving as coolant is supplied to a cavity (27) from a inner cylinder (10) and hence fed to moving blades (11, 12) through recesses (40) formed in a coupling portion (26) interposed between a final-stage disk (24) and a turbine shaft (1), steam feeding pipes (15) and steam feeding passages (11a, 12a). After cooling of the moving blades, steam (31) is recovered through steam recovering passages (11b, 12b), steam recovering pipes (16), radial steam-recovering passages (17), axial steam-recovering passages (18) and outlet openings (5a). The coupling portion (26) is forced to hermetically close under thermal stress, whereby leakage of the feed steam (30) is prevented. Steam leaking through a seal portion constituted by stationary and rotatable seal fin assemblies (4a, 4b) can be effectively recovered. The inner cylinder (10) can move in the axial direction through cooperation of piston rings (43) and a centering piece (6) adapted for absorbing thermal stress induced in the inner cylinder (10). Upstream tip end portions of steam feeding pipes (15) and steam recovering pipes (16) are secured onto a side surface of the first-stage disk (21) through sleeves removably fitted thereto.
摘要翻译： 一种蒸汽冷却燃气轮机，其中冷却蒸汽从旋转轴的中心部分进给并通过设置在中心部分的外侧的通道被回收，蒸汽通过密封部分从进料蒸汽泄漏得到有效回收。 作为冷却剂的进料蒸汽（30）从内筒（10）供给到空腔（27），从而通过形成在连接部分（26）中的连接部分（26）的凹部（40）供给到活动叶片（11,12） 末级盘（24）和涡轮轴（1），蒸汽供给管（15）和蒸汽供给通道（11a，12a）。 在运动叶片冷却后，蒸汽（31）通过蒸汽回收通道（11b，12b），蒸汽回收管（16），径向蒸汽回收通道（17），轴向蒸汽回收通道（18）和出口 （5a）。 耦合部分（26）在热应力下被迫气密地闭合，从而防止进料蒸汽（30）的泄漏。 可以有效地回收通过由固定和可旋转的密封翅片组件（4a，4b）构成的密封部分泄漏的蒸汽。 内筒（10）可以通过活塞环（43）和适于吸收在内筒（10）中感应的热应力的定心件（6）的配合而沿轴向移动。 蒸汽供给管（15）和蒸汽回收管（16）的上游末端部分通过可移除地装配在其上的套筒固定在第一级盘（21）的侧表面上。
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公开(公告)号：US5971707A
公开(公告)日：1999-10-26
申请号：US109379
申请日：1998-07-02
申请人： Kazuo Uematsu , Rintaro Chikami , Yasuoki Tomita , Hiroki Fukuno , Sunao Aoki , Toshiaki Sano , Yukihiro Hashimoto , Kiyoshi Suenaga , Kazuharu Hirokawa
发明人： Kazuo Uematsu , Rintaro Chikami , Yasuoki Tomita , Hiroki Fukuno , Sunao Aoki , Toshiaki Sano , Yukihiro Hashimoto , Kiyoshi Suenaga , Kazuharu Hirokawa
CPC分类号： F01D5/18 , F01D11/006 , F05D2260/2322
摘要： A gas turbine moving blade steam cooling system in which leakage of steam for cooling a moving blade is prevented and thermal stress at a blade root end portion is mitigated. Each end portion of a blade root portion (3) of the moving blade (1) is projected so as to form a projection portions (4a, 4b). A steam passage 5 is provided between the projection portions (4a, 4b) and a steam supply port 5a and a steam recovery port (5b) are provided downwardly with the respect to the steam passage 5. The steam supply port (5a) connects to a steam supply passage (20) and the steam recovery port (5b) connects to a steam recovery passage (21). Steam is supplied from the steam supply port (5a) into a blade interior and is recovered through the steam recovery port (5b). Side surface seal plates (6, 7 and 8) are provided for preventing steam leakage. The steam cools the moving blade (1) and can be recovered without leakage and stress concentration due to heat at the projection portions (4a, 4b) of the blade root end portion.
摘要翻译： 一种燃气轮机动叶片蒸汽冷却系统，其中防止用于冷却动叶片的蒸汽泄漏并减轻叶片根部端部处的热应力。 活动叶片（1）的叶片根部（3）的每个端部突出以形成突出部分（4a，4b）。 蒸汽通道5设置在突出部分（4a，4b）和蒸汽供应口5a之间，蒸汽回收口（5b）相对于蒸汽通道5向下设置。蒸汽供应口（5a）连接到 蒸汽供应通道（20）和蒸汽回收口（5b）连接到蒸汽回收通道（21）。 蒸汽从蒸汽供给口（5a）供给到叶片内部，并通过蒸汽回收口（5b）回收。 侧面密封板（6,7和8）用于防止蒸汽泄漏。 蒸汽冷却活动叶片（1），并且可以在叶片根部的突出部分（4a，4b）处由于热量而没有泄漏和应力集中而恢复。
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公开(公告)号：US06189892B1
公开(公告)日：2001-02-20
申请号：US09214384
申请日：1998-12-30
IPC分类号： F16J15447
CPC分类号： F01D11/02 , F16J15/4472
摘要： A high differential pressure type end rotor seal that is applicable to a steam cooled type gas turbine with the aim to reduce steam leakage to a minimum without being affected by deviation of fins due to thermal elongation. An end rotor rotational seal of a double strip seal type is structured such that fins (3,5) on a stator side (1) and fins (4,6) on a rotor side (2) are arranged in a confronting arrangement and an alternating arrangement. A fin-to-fin pitch (P) is set in a range of 2 to 6 mm and a clearance (C) between apexes of the fins is set in a range of 0.3 to 1.0 mm, thereby a high differential pressure type rotational seal is obtained having minimum steam leakage without being affected by deviation of fins due to thermal elongation between the stator side and the rotor side.
摘要翻译： 适用于蒸汽冷却式燃气轮机的高压差型末端转子密封件，其目的是将蒸汽泄漏减少至最小，而不受热伸长引起的翅片偏差的影响。 双带密封型的端转子旋转密封结构使得定子侧（1）上的翅片（3,5）和转子侧（2）上的翅片（4,6）以相对的方式布置，并且 交替安排。 翅片间翅距（P）设定在2〜6mm的范围内，翅片顶点之间的间隙（C）设定在0.3〜1.0mm的范围内，由此形成高压差型旋转密封 获得具有最小的蒸汽泄漏，而不受定子侧和转子侧之间的热伸长的翅片偏差的影响。
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公开(公告)号：US6000909A
公开(公告)日：1999-12-14
申请号：US27191
申请日：1998-02-20
CPC分类号： F01D5/081 , F05D2260/205
摘要： A gas turbine moving blade having a cooling medium flow path constructed so that a concave spherical surface (C) is formed on a inside surface of an end portion of the cooling medium path (B) formed in a blade root portion. A hollow pipe (6) is provided in the cooling medium flow path between the blade root portion and a disc. The hollow pipe has a convex spherical surface (D) at one end thereof which engages the concave spherical surface (C) and the other end of the pipe has a convex spherical surface (F) which engages an inside surface of a cooling medium path (E) formed in the disc. The hollow pipe (6) provides communication between the cooling medium path (B) on the blade side and the cooling medium path (E) on the disc side. A supporting structure (7, 8, 9) is provided for holding the hollow pipe in the communicating position.
摘要翻译： 一种燃气轮机动叶片，其具有构造成在形成在叶根部的冷却介质路径（B）的端部的内表面上形成凹球面（C）的冷却介质流路。 在叶片根部和盘之间的冷却介质流动路径中设置中空管（6）。 中空管的一端具有与球形凹部（C）接合的凸球面（D），管的另一端具有与冷却介质路径（内侧面）接合的凸状球面（F） E）。 中空管（6）提供叶片侧的冷却介质路径（B）与盘侧的冷却介质路径（E）之间的连通。 提供支撑结构（7,8,9），用于将中空管保持在连通位置。
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5.发明授权
公开(公告)号：US6095751A
公开(公告)日：2000-08-01
申请号：US150370
申请日：1998-09-10
申请人： Kazuharu Hirokawa , Rintaro Chikami
发明人： Kazuharu Hirokawa , Rintaro Chikami
CPC分类号： F01D11/005 , F01D5/066 , F16J15/0887
摘要： A seal device between a fastening bolt and a bolthole in a gas turbine disc reduces cooling steam leaking from a gap between the fastening bolt and the bolthole. A gas turbine disc 31 carrying moving blades, a fastening bolt 33 for fixing the disc 31 passes through a bolthole 32. On a low pressure side of the disc 31, a bolthole diameter enlarged portion 39 having a larger diameter than that of the bolthole 32 is provided. Fastening bolt 33 is provided with a shaft diameter enlarged portion 33a. Seal piece 1 is fitted at one end around the shaft diameter enlarged portion 33a and is engaged at the other end with a stepped portion of the bolthole diameter enlarged portion 39. In operation of the gas turbine, the bolt 33 is biased outwardly be centrifugal force, and the gap between the bolt 33 and the bolthole 32 deforms. Nevertheless, the seal piece 1, having flexibility, deforms at bent portions R.sub.1 and R.sub.2 to maintain close contact and steam 43 is prevented from leaking from the high pressure side to the low pressure part 38, and the sealing ability is maintained.
摘要翻译： 在燃气涡轮盘中的紧固螺栓和螺栓孔之间的密封装置减少了从紧固螺栓和螺栓孔之间的间隙泄漏的冷却蒸汽。 承载移动叶片的燃气轮机盘31，用于固定盘31的紧固螺栓33穿过螺栓孔32.在盘31的低压侧，具有比螺栓32的直径大的螺栓直径扩大部分39 被提供。 紧固螺栓33设有轴径扩大部33a。 密封件1的一端围绕轴径扩大部分33a安装，并且在另一端处与螺栓直径扩大部分39的阶梯部分接合。在燃气轮机的操作中，螺栓33向外偏压为离心力 并且螺栓33和螺栓32之间的间隙变形。 然而，具有柔性的密封件1在弯曲部分R1和R2处变形，以保持紧密接触，并且防止蒸汽43从高压侧泄漏到低压部分38，并且保持密封能力。
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公开(公告)号：US06327861B2
公开(公告)日：2001-12-11
申请号：US09862468
申请日：2001-05-23
申请人： Yoshichika Sato , Yoji Kochi , Koichi Akagi , Kazuya Kobayashi , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Kotaro Miyauchi , Rintaro Chikami , Shigemi Mandai , Masataka Ota
发明人： Yoshichika Sato , Yoji Kochi , Koichi Akagi , Kazuya Kobayashi , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Kotaro Miyauchi , Rintaro Chikami , Shigemi Mandai , Masataka Ota
IPC分类号： F02C100
CPC分类号： F23L7/00 , F23C9/00 , F23D2900/00008 , F23L2900/07002 , F23R3/005 , F23R3/14 , F23R3/343 , F23R3/60
摘要： In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.
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公开(公告)号：US06282886B1
公开(公告)日：2001-09-04
申请号：US09437146
申请日：1999-11-10
申请人： Yoshichika Sato , Yoji Kochi , Koichi Akagi , Kazuya Kobayashi , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Kotaro Miyauchi , Rintaro Chikami , Shigemi Mandai , Masataka Ota
发明人： Yoshichika Sato , Yoji Kochi , Koichi Akagi , Kazuya Kobayashi , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Kotaro Miyauchi , Rintaro Chikami , Shigemi Mandai , Masataka Ota
IPC分类号： F02C300
CPC分类号： F23L7/00 , F23C9/00 , F23D2900/00008 , F23L2900/07002 , F23R3/005 , F23R3/14 , F23R3/343 , F23R3/60
摘要： In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.
摘要翻译： 在燃烧器20的内管28的中心部分，引导燃料喷嘴22和引导锥体33布置，并且主燃料喷嘴21和主旋流器32在其周围。 进气部（X-1）设有用于使进气均匀的整流管11。 在进气部分（X-2）中，在内管28的周向壁上设有适当数量的气孔。在主旋流器部分（X-3）和先导锥体部分（X-4）中， 使用主旋流器32，并且分别采用对先导式旋流器33的热应力影响较小的优化焊接结构。 尾管冷却部（X-5）具有对热应力影响较小的冷却结构，均匀地冷却尾管24的凸缘部71。 通过部分（X-1）至（X-5）的改进，燃烧器20中获得较高温度的障碍物被溶解并且燃烧器性能提高。
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公开(公告)号：US20060239814A1
公开(公告)日：2006-10-26
申请号：US11316900
申请日：2005-12-27
申请人： Takuya Uwami , Rintaro Chikami
发明人： Takuya Uwami , Rintaro Chikami
IPC分类号： F01D25/26
CPC分类号： F01D11/008 , F01D11/005
摘要： A gas turbine, wherein annular overhang portions are formed on adjacent surfaces of a plurality of rotor discs so as to face each other, surrounding the rotor axis, groove portions are provided circumferentially to the surfaces of the overhang portions facing each other, and sealing structures being annularly installed to the inside of the groove portions are provided, comprises sealing plate assemblies which include the overhang portions, the groove portions and a plurality of plates being formed annularly by being mutually piled up; and detachable retaining members which are provided so as to fix the overhang portions and the sealing plate assemblies together by way of disc engagement portions being provided to the overhang portions and sealing plate engagement portions being provided to the sealing plate assemblies.
摘要翻译： 一种燃气轮机，其中环形突出部分形成在多个转子盘的相邻表面上以便彼此面对，围绕转子轴线，槽部分周向地设置在彼此面对的突出部分的表面上，密封结构 设置有环形安装在槽部内侧的密封板组件，包括通过相互堆叠而形成为环状的突出部，槽部和多个板的密封板组件。 以及可拆卸的保持构件，其设置成通过设置在突出部分上的盘接合部分以及密封板接合部分设置在密封板组件上而将悬伸部分和密封板组件固定在一起。
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公开(公告)号：US06261063B1
公开(公告)日：2001-07-17
申请号：US09230848
申请日：1999-02-02
申请人： Rintaro Chikami , Kaoru Sakata , Takeshi Nakamura
发明人： Rintaro Chikami , Kaoru Sakata , Takeshi Nakamura
IPC分类号： F01D530
CPC分类号： F01D5/066 , F01D5/22 , F01D11/005 , F05D2220/31
摘要： In a steam cooling type gas turbine, a sealing structure for improving sealing performance between an interior of a rotor and a gas path of a turbine section which performs inter-disk sealing such that leakage of cooling steam and self-induced vibration of a baffle plate are prevented. A groove is formed along a circumferential direction in an end face of at least one of disk lands which protrude in opposition to each other between adjacent rotor disks, and an annular sealing member having an interior space is disposed in a sandwiched fashion, being brought into contact under pressure with an inner wall surface of the groove and an end face of the other disk land, or alternatively, an inner wall surface of a groove formed in the other disk land to thereby realize the inter-disk sealing structure for the gas turbine. Upon rotation of the turbine, sealing surface pressure is increased by centrifugal force to thereby reliably maintain sealing between the disks of the gas turbine, and the sealing performance in the gas turbine is improved.
摘要翻译： 在蒸汽冷却型燃气轮机中，提供一种用于改善转子内部和涡轮部分的气体路径之间的密封性能的密封结构，其进行盘间密封，使得冷却蒸汽的泄漏和挡板的自身引起的振动 被阻止 在相邻的转子盘之间彼此相对突出的至少一个盘凸台的端面中沿着圆周方向形成有槽，并且具有内部空间的环形密封构件以夹持方式设置， 在压力下与槽的内壁面和另一个盘片的端面接触，或者形成在另一个盘片区域中的槽的内壁面，从而实现燃气轮机的盘间密封结构 。 在涡轮旋转时，通过离心力增加密封面压力，从而可靠地保持燃气轮机的盘之间的密封，并提高燃气轮机的密封性能。
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公开(公告)号：US06578363B2
公开(公告)日：2003-06-17
申请号：US10072865
申请日：2002-02-12
IPC分类号： F02C712
摘要： Cooling air passages are formed in the wall of an exhaust casing connected to a turbine casing of a gas turbine. Low pressure air extracted from the low pressure stage of an air compressor of the gas turbine is supplied to the cooling air passage from the portion near the downstream end of the exhaust casing. Cooling air flows through the cooling air passage toward the upstream end of the exhaust casing and then flows into an annular cavity formed in the turbine casing near the portion corresponding to the last turbine stage. Therefore, the metal temperature of the exhaust casing near the upstream end (near the joint between the exhaust casing and the turbine casing) is lowered by the cooling air and, as cooling air of a relatively high temperature is supplied to the cavity in the turbine casing, the metal temperature of the turbine casing near the downstream end becomes higher than that provided by a conventional cooling system. Therefore, the difference between the metal temperatures of the turbine casing and the exhaust casing becomes very small and the thermal stress exerted on the exhaust casing due to the temperature difference can be largely reduced.
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