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1. 发明公开

EP2037081A1 PLATFORM COOLING STRUCTURE OF GAS TURBINE ROTOR BLADE 有权转让
标题翻译： PLATTFORMKÜHLSTRUKTURFÜREINE GASTURBINENSCHAUFEL
公开(公告)号：EP2037081A1
公开(公告)日：2009-03-18
申请号：EP07849990.2
申请日：2007-11-27
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： TORII, Shunsuke , KUWABARA, Masamitsu , ITO, Eisaku
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/187 , F01D5/18 , F01D25/12 , F05D2240/81
摘要： A platform cooling structure for a gas turbine moving blade is provided which is capable of improving cooling performance of a platform and of improving reliability of a moving blade in such a manner that a portion in the vicinity of a side edge of the platform which is away from moving blade cooling passageways and is easily influenced by thermal stress caused by high-temperature combustion gas, that is, an upper surface of the side edge is effectively cooled by guiding high-pressure cooling air, flowing to the moving blade cooling passageways, to a discharge opening formed in a surface of the platform in the vicinity of the side edge of the platform without particularly attaching an additional member such as a cover plate to the platform. A moving blade cooling passageway 17c is formed in the inside of the gas turbine moving blade. Cooling communication holes 24a and 24b, of which one ends communicate with the moving blade cooling passageway 17c and the other ends communicate with a plurality of discharge openings 22 provided in the surface of the platform in the vicinity of the side edge of the platform 5, are formed through the inside of the platform.
摘要翻译：提供了一种用于燃气轮机动叶片的平台冷却结构，其能够改善平台的冷却性能并提高移动叶片的可靠性，使得平台的侧边附近的部分离开来自动叶片冷却通道，并且容易受到由高温燃烧气体引起的热应力的影响，即通过将高压冷却空气引导至流动叶片冷却通道而有效地冷却侧边缘的上表面，在平台的侧边附近形成在平台的表面中的排出口，而不特别地将诸如盖板的附加构件附接到平台。动叶片冷却通道17c形成在燃气轮机动叶片的内部。一端与动叶片冷却通道17c连通的冷却连通孔24a和24b与另一端连通，平台5的侧边附近设置在平台表面上的多个排放口22，通过平台的内部形成。

2. 发明公开

EP2752622A1 GAS TURBINE 审中-公开
标题翻译：燃气轮机
公开(公告)号：EP2752622A1
公开(公告)日：2014-07-09
申请号：EP12832651.9
申请日：2012-09-12
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： SAKAMOTO, Yasuro , MATSUYAMA, Keisuke , TSUKAGOSHI, Keizo , YURI, Masanori , KISHIDA, Hiroaki , TORII, Shunsuke
IPC分类号： F23R3/42 , F01D9/02 , F23R3/16
CPC分类号： F23R3/002 , F01D9/023 , F05D2250/324 , F05D2250/52 , F05D2250/71 , F23C2201/20 , F23C2900/06043 , F23D11/106 , F23D11/38 , F23D2214/00 , F23R3/16 , F23R3/283 , F23R3/36 , F23R3/42 , F23R3/46 , F23R2900/00014 , F23R2900/03341
摘要： In this gas turbine, at a downstream part of a tail pipe of a combustor, the inner surfaces of a pair of lateral walls facing each other in the circumferential direction of a turbine rotor form inclination surfaces that, going in the downstream axial direction of the tail pipe, incline in a direction approaching the tail pipe of an adjacent other combustor that gradually draws closer, until the inclination surfaces reach the downstream end of the tail pipe.
摘要翻译：在该燃气轮机中，在燃烧器的尾管的下游侧，在涡轮转子的圆周方向上彼此面对的一对侧壁的内表面形成倾斜面，尾管在靠近相邻其他燃烧器的尾管的方向上倾斜，逐渐变得更靠近，直到倾斜表面到达尾管的下游端。

3. 发明公开

EP2623744A1 AIR RECOVERY-TYPE COOLING STRUCTURE FOR AIR-COOLED GAS TURBINE COMBUSTOR 有权转让
标题翻译： KÜHLSTRUKTURMITLUFTRÜCKFÜHRUNGFÜREINENLUFTGEKÜHLTENGASTURBINENKOMPRESSOR
公开(公告)号：EP2623744A1
公开(公告)日：2013-08-07
申请号：EP11828634.3
申请日：2011-08-10
申请人： Mitsubishi Heavy Industries, Ltd. , Tohoku Electric Power Co., Inc.
发明人： MIZUKAMI, Satoshi , ISHIGURO, Tatsuo , MASADA, Junichiro , TAKATA, Kazumasa , TORII, Shunsuke , FUKUNAGA, Yuya , KONISHI, Tetsu , NISHIMURA, Yoshiaki , IGARASHI, Yoshiaki , ISHIKAWA, Shinya
IPC分类号： F02C7/18 , F01D25/00 , F02C7/08 , F02C7/24 , F23R3/06 , F23R3/42
CPC分类号： F02C7/18 , F01D9/023 , F02C7/08 , F02C7/24 , F05D2260/202 , F23R3/005 , F23R3/06 , F23R3/44 , F23R2900/00014
摘要： In a cooling structure for a recovery-type air-cooled gas turbine combustor (30) having a recovery-type air-cooling structure that bleeds, upstream of the combustor (30), and pressurizes compressed air supplied from a compressor, that uses the bled and pressurized air to cool a wall (40), and that recovers and reuses the bled and pressurized air as combustion air for burning fuel in the combustor (30) together with a main flow of the compressed air, wall cooling in which cooling air is supplied to cooling air passages (41) formed in the wall (40) of the combustor (30) to perform cooling involves a downstream wall region, closer to a turbine, that is cooled using the bled and pressurized air as the cooling air and an upstream wall region, closer to a burner, that is cooled using, as the cooling air, bled compressed air bled from a main flow of the compressed air through a housing inner space.
摘要翻译：在具有在燃烧器（30）的上游流出的回收型空气冷却结构的回收型风冷式燃气轮机燃烧器（30）的冷却结构中，对从压缩机供给的压缩空气进行加压，排出和加压空气以冷却壁（40），并且将排出和加压空气作为燃烧空气回收并重新使用作为燃烧器（30）中的燃料的燃烧空气与压缩空气的主流一起冷却，冷却空气被供给到形成在燃烧器（30）的壁（40）中的冷却空气通道（41），以进行冷却，其包括使用作为冷却空气的排出和加压空气来冷却的靠近涡轮机的下游侧壁区域，以及更靠近燃烧器的上游壁区域，其使用作为冷却空气的压缩空气通过壳体内部空间从压缩空气的主流排出。

4. 发明公开

EP2182169A1 BLADE COOLING STRUCTURE OF GAS TURBINE 有权转让
标题翻译：燃气轮机的叶片冷却结构
公开(公告)号：EP2182169A1
公开(公告)日：2010-05-05
申请号：EP07806358.3
申请日：2007-08-30
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： FUJIMURA, Daigo , SUGISHITA, Hideaki , MATSUURA, Masaaki , YAMAMOTO, Hiroyuki , TORII, Shunsuke , HADA, Satoshi
IPC分类号： F01D5/18 , F01D9/02
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).

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