公开(公告)号：EP1098067B1

公开(公告)日：2007-10-03

申请号：EP00118432.4

申请日：2000-08-24

申请人： Hitachi, Ltd.

发明人： Akiyama, Ryou ,  Marushima, Shinya ,  Matsumoto, Manabu ,  Takano, Tsuyoshi

IPC分类号： F01D5/08 ,  F01D5/18 ,  F02C7/12

CPC分类号： F02C7/12 ,  F01D5/081 ,  F01D5/187 ,  F05D2260/205

公开(公告)号：EP2434106A2

公开(公告)日：2012-03-28

申请号：EP11178806.3

申请日：2011-08-25

申请人： Hitachi Ltd.

发明人： Akiyama, Ryou ,  Takahashi, Yasuo ,  Morisaki, Tetsuro ,  Horiuchi, Yasuhiro

IPC分类号： F01D25/14 ,  F01D25/24

CPC分类号： F01D25/246 ,  F01D11/24 ,  F01D25/14 ,  F05D2240/11

摘要： There is provided a shroud structure for gas turbines capable of suppressing a drop in the amount of cooling air for cooling the inner shroud 32, 42, 52, 65, 67 by reducing the amount of cooling air leakage that occurs along the cooling air path when feeding cooling air from the one-piece outer shroud 1, 51 to the inner shroud 32, 42, 52, 65, 67 of the gas turbine and ensure more reliable cooling of the inner shroud 32, 42, 52, 65, 67. The gas turbine shroud structure contains a one-piece outer shroud 1, 51, and an inner shroud 32, 42, 52, 65, 67 retained on the inner circumferential side of the outer shroud 1, 51 in a structure divided into multiple inner shrouds along the periphery. An inner seal plate groove 81, 82; 83; 84, 85; 88 is formed on the outer circumference of the hook 33, 34; 43, 44; 53, 54 formed on the inner shroud 32, 42, 52, 65, 67, a seal plate 35, 36; 46; 55, 56; 61, 62; 71, 72, 73, 74 is inserted in the inner seal plate groove 81, 82; 83; 84, 85; 88 and the seal plate 35, 36; 46; 55, 56; 61, 62; 71, 72, 73, 74 is mounted so that a section of the seal plate protrudes in the gap between the hook mechanism of the outer shroud and the inner shroud.

摘要翻译： 提供了一种用于燃气轮机的护罩结构，其能够通过减少沿着冷却空气路径发生的冷却空气泄漏量来抑制用于冷却内护罩32,42,52,65,67的冷却空气量的下降， 将冷却空气从一体式外护罩1,51送到燃气轮机的内护罩32,42,52,65,67，并确保内护罩32,42,52,65,67的更可靠的冷却。 燃气轮机罩结构包括一体式外护罩1,51以及保持在外护罩1,51的内周侧的内护罩32,42,52,65,67，其以分开多个内护罩的结构沿着 外围。 内密封板槽81,82; 83; 84，85; 88形成在钩33,34的外周上; 43，44; 53,54形成在内罩32,42,52,65,67上，密封板35,36; 46; 55，56; 61,62; 71,72,73,74插入内密封板槽81,82中; 83; 84，85; 88和密封板35,36; 46; 55，56; 61,62; 71,72,73,74安装成使得密封板的一部分在外护罩的钩机构和内护罩之间的间隙中突出。

公开(公告)号：EP1918547A2

公开(公告)日：2008-05-07

申请号：EP08001214.9

申请日：2003-06-23

申请人： Hitachi, Ltd.

发明人： Koganezawa, Tomomi ,  Shibata, Takanori ,  Seiki, Nobuhiro ,  Marushima, Shinya ,  Higuchi, Shinichi ,  Kizuka, Nobuaki ,  Akiyama, Ryou ,  Noda, Masami

IPC分类号： F02C3/13

CPC分类号： F02C3/13 ,  F02C3/04 ,  F05D2230/61 ,  F05D2240/40 ,  Y02E20/14 ,  Y02E20/16 ,  Y02T50/67 ,  Y10T29/49316 ,  Y10T29/4932 ,  Y10T29/49321 ,  Y10T29/49323 ,  Y10T29/49716

摘要： The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.

公开(公告)号：EP1918547A3

公开(公告)日：2008-11-05

申请号：EP08001214.9

申请日：2003-06-23

申请人： Hitachi, Ltd.

发明人： Koganezawa, Tomomi ,  Shibata, Takanori ,  Seiki, Nobuhiro ,  Marushima, Shinya ,  Higuchi, Shinichi ,  Kizuka, Nobuaki ,  Akiyama, Ryou ,  Noda, Masami

IPC分类号： F01D5/00 ,  F02C3/13

CPC分类号： F02C3/13 ,  F02C3/04 ,  F05D2230/61 ,  F05D2240/40 ,  Y02E20/14 ,  Y02E20/16 ,  Y02T50/67 ,  Y10T29/49316 ,  Y10T29/4932 ,  Y10T29/49321 ,  Y10T29/49323 ,  Y10T29/49716

摘要： The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.

摘要翻译： 本发明提供了一种能够应用于各种循环的燃气轮机的生产过程。 基于大致设定的条件预先设定燃气轮机的主要部分，并基于该设定来设定能够提供适合于期望周期的条件的压缩机的级数和涡轮机的级数 主体。 构成燃气轮机的压缩机和设置在主要部分中的具有设定级数的压缩机和涡轮彼此组合。 当压缩机或涡轮机的设定级数在多个期望的循环中不同时，具有形成压缩机或涡轮机的大致环形流动通道的内周壁的外周的大致盘形构件， 组装成具有较少级数的循环，使得在以多个期望的循环操作的燃气轮机中轴承与轴承的距离保持恒定。

公开(公告)号：EP1098067A2

公开(公告)日：2001-05-09

申请号：EP00118432.4

申请日：2000-08-24

申请人： Hitachi, Ltd.

发明人： Akiyama, Ryou ,  Marushima, Shinya ,  Matsumoto, Manabu ,  Takano, Tsuyoshi

IPC分类号： F01D5/08 ,  F01D5/18 ,  F02C7/12

CPC分类号： F02C7/12 ,  F01D5/081 ,  F01D5/187 ,  F05D2260/205

摘要： In a gas turbine having a structure of collecting a refrigerant after cooling the moving blades, a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members are alternately arranged on the rotating axis. A plurality of flow paths through which a refrigerant after cooling the moving blades flows are installed in the spacer members, and the first flow paths interconnect the moving blades arranged on the wheels on the upstream side of gas flow to the downstream side of gas flow of the spacer members, and the second flow paths interconnect the moving blades arranged on the wheels on the downstream side of gas flow to the upstream side of gas flow of the spacer members. The flow paths may be provided with bent parts in the neighborhood of the center of the space members in the axial direction or may be in a linear shape.

摘要翻译： 在具有冷却动叶片之后收集制冷剂的结构的燃气轮机中，具有包括外周部的冷却路径的多个动叶片和多个间隔部件的多个轮交替配置在旋转轴上。 冷却动叶片之后的制冷剂流过的多个流动路径被安装在间隔件中，并且第一流动路径将布置在气流的上游侧的车轮上的动叶连接到气流的下游侧 隔离构件和第二流动路径将布置在气流下游侧的轮上的动叶连接到间隔件的气流的上游侧。 流路可以在轴向方向上在空间构件的中心附近设置弯曲部分，或者可以是直线形状。

公开(公告)号：EP2472127A2

公开(公告)日：2012-07-04

申请号：EP11195801.3

申请日：2011-12-27

申请人： Hitachi Ltd.

发明人： Takahashi, Yasuo ,  Myoren, Chihiro ,  Akiyama, Ryou

IPC分类号： F04D29/54

CPC分类号： F04D29/544 ,  Y10T29/49238 ,  Y10T29/49245

摘要： When a gas turbine is operated with inlet guide vanes (IGVs) closed during part load operation or the like, the degradation of aerodynamic performance and of reliability may potentially occur since the load on rear stage side vanes of a compressor increases. An object of the present invention is to suppress the degradation of the aerodynamic performance and of reliability of an axial compressor.
The axial compressor 1 includes a rotor 22; a plurality of rotor blade rows 31, 32 installed on the rotor 22; a casing 21 located outside of the rotor blade rows 31, 32; a plurality of stator vane rows 34, 35 installed on the casing 21; and exit guide vanes 36, 37 installed on the downstream side of a final stage stator vane row 35 among the stator vane rows 34, 35. An incidence angle of a flow toward the final stage stator vane row 35 is equal to or below a limit line of an incidence operating range 42.

摘要翻译： 当在部分加载操作等期间使进口导叶（IGV）关闭的情况下燃气轮机被操作时，由于压缩机的后级侧叶片上的负载增加，潜在的空气动力性能和可靠性的降低可能会发生。 本发明的目的是抑制轴向压缩机的空气动力学性能和可靠性的劣化。 轴向压缩机1包括转子22; 安装在转子22上的多个转子叶片排31,32; 位于转子叶片排31,32外侧的壳体21; 安装在壳体21上的多个定子叶片排34,35; 以及安装在定子叶片排34,35中的末级定子叶片排35的下游侧的出口导向叶片36,37。朝向最终级定子叶片排35的流动的入射角等于或低于极限 行发生率范围42。

公开(公告)号：EP2431577A2

公开(公告)日：2012-03-21

申请号：EP11178798.2

申请日：2011-08-25

申请人： Hitachi Ltd.

发明人： Takahashi, Yasuo ,  Myoren, Chihiro ,  Akiyama, Ryou ,  Miyoshi, Ichiro

IPC分类号： F01D25/00

摘要： There is provided an axial flow compressor 1 that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor 1 due to a partial load operation of a gas turbine 3. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes 35, 36, 37 are disposed downstream of a last-stage rotor blade that is the rotor blade disposed at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane 35 disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane 36 disposed downstream of the first stator vane 35 by one row.

摘要翻译： 提供了一种轴流式压缩机1，其由于燃气轮机3的部分负载操作而提高了在轴流式压缩机1的最后一级定子叶片上的叶片负载的增加的可靠性。环形流动通道由 具有安装在其上的多个转子叶片的转子和安装有多个定子叶片的壳体，两个或多个定子叶片35,36,37设置在最后一级转子叶片的下游，转子叶片是设置在最下游的转子叶片 在设置在最上游侧的第一定子叶片35上装载的叶片被设定为比设置在第一定子叶片35下游的第二定子叶片36的叶片负载小， 一排

公开(公告)号：EP1098067A3

公开(公告)日：2004-01-14

申请号：EP00118432.4

申请日：2000-08-24

申请人： Hitachi, Ltd.

发明人： Akiyama, Ryou ,  Marushima, Shinya ,  Matsumoto, Manabu ,  Takano, Tsuyoshi

IPC分类号： F01D5/08 ,  F01D5/18 ,  F02C7/12

CPC分类号： F02C7/12 ,  F01D5/081 ,  F01D5/187 ,  F05D2260/205

摘要： In a gas turbine having a structure of collecting a refrigerant after cooling the moving blades, a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members are alternately arranged on the rotating axis. A plurality of flow paths through which a refrigerant after cooling the moving blades flows are installed in the spacer members, and the first flow paths interconnect the moving blades arranged on the wheels on the upstream side of gas flow to the downstream side of gas flow of the spacer members, and the second flow paths interconnect the moving blades arranged on the wheels on the downstream side of gas flow to the upstream side of gas flow of the spacer members. The flow paths may be provided with bent parts in the neighborhood of the center of the space members in the axial direction or may be in a linear shape.

摘要翻译： 在具有冷却动叶片之后收集制冷剂的结构的燃气轮机中，具有包括外周部的冷却路径的多个动叶片和多个间隔部件的多个轮交替配置在旋转轴上。 冷却动叶片之后的制冷剂流过的多个流动路径被安装在间隔件中，并且第一流动路径将布置在气流的上游侧的车轮上的动叶连接到气流的下游侧 隔离构件和第二流动路径将布置在气流下游侧的轮上的动叶连接到间隔件的气流的上游侧。 流路可以在轴向方向上在空间构件的中心附近设置弯曲部分，或者可以是直线形状。

公开(公告)号：EP2428664A2

公开(公告)日：2012-03-14

申请号：EP11178316.3

申请日：2011-08-22

申请人： Hitachi Ltd.

发明人： Myoren, Chihiro ,  Akiyama, Ryou ,  Marushima, Shinya ,  Takahashi, Yasuo ,  Higuchi, Shinichi

IPC分类号： F02C9/18

CPC分类号： F04D29/321 ,  F01D5/085

摘要： An inner bleed structure of the 2-shaft gas turbine includes a slit 51 for leading part of compressed air to a cavity is formed between a wall surface of a rotor wheel 25 of the compressor 2 equipped with a last stage rotor of the compressor 2 which is connected to a first rotating shaft 6 and end of an inner casing 27, and a bleed hole 52 for leading part of compressed air after flowing down the last stage of the compressor 2 to a cavity formed in the inner side of the inner casing 27 at the downstream side of the last stage of the compressor 2.

摘要翻译： 两轴的燃气涡轮的内部泄放结构包括狭缝51用于引导部分压缩空气到腔被限定在压缩机2的转子轮25配备有压缩机2哪一个负载级转子的壁表面之间形成 被连接到第一旋转轴6和一个内壳体27的端部，与压缩机2的负载阶段向下流动到内部壳体27的内侧面形成的腔体后用于压缩空气的前导部分的排出孔52 在压缩机的负载级的下游侧。2

公开(公告)号：EP2253818A2

公开(公告)日：2010-11-24

申请号：EP10162477.3

申请日：2010-05-11

申请人： Hitachi Ltd.

发明人： Myoren, Chihiro ,  Akiyama, Ryou

IPC分类号： F02C3/10 ,  F01D5/14

CPC分类号： F02C3/10 ,  F01D5/142 ,  F05D2220/321

摘要： On a two-shaft gas turbine 1, on at least one of an inner peripheral side or an outer peripheral side of a main flow passage, an outlet of a high-pressure turbine 4 is lower than an inlet of a low-pressure turbine 5, an outer periphery of a flow channel that connects the outlet of the high-pressure turbine 4 and the inlet of the low-pressure turbine 5 includes a first casing shroud 44 that is supported by a casing 12 and located on an outer peripheral side of a final-stage rotor vane 42 of the high-pressure turbine 4, and an initial-stage stator vane 51 of the low-pressure turbine 5, and a connection position of the first casing shroud 44 and the initial-stage stator vane 51 of the low-pressure turbine 5 is closer to the inlet of the initial-stage stator vane 51 of the low-pressure turbine 5 than the outlet of the final-stage rotor vane 42 of the high-pressure turbine 4.

摘要翻译： 在双轴燃气轮机1上，在主流路的内周侧或外周侧的至少一方，高压涡轮4的出口低于低压涡轮5的入口 连接高压汽轮机4的出口和低压汽轮机5的入口的流路的外周部包括：第一壳体护罩44，其由壳体12支撑并位于低压侧的外周侧 高压汽轮机4的末级转子叶片42和低压汽轮机5的初级定子叶片51，以及第一壳体护罩44和初级定子叶片51的连接位置 低压涡轮5比高压涡轮4的末级转子叶片42的出口更靠近低压涡轮5的初级定子叶片51的入口。