公开(公告)号：EP2693020A2

公开(公告)日：2014-02-05

申请号：EP13178023.1

申请日：2013-07-25

申请人： Hitachi Ltd.

发明人： Takahashi, Fumio ,  Koyama, Kazuhito ,  Hatamiya, Shigeo ,  Kusumi, Naohiro ,  Myoren, Chihiro ,  Agata, Go ,  Sekiai, Takaaki

IPC分类号： F02C3/30 ,  F02C7/141

CPC分类号： F02C7/1435 ,  F02C3/30 ,  F02C7/141 ,  F04D29/5846

摘要： In an atomizer constructed to cool inlet air for a gas turbine by spraying fine droplets of water into the inlet air, a spray nozzle (300) is disposed to spray the finely atomized droplets of water from an outer edge of an atomized airstream into a high-speed zone thereof, towards a central region of the airstream. The atomized airstream meets an airstream of a low-speed zone formed at a downstream side, and after the two kinds of airstreams have been mixed and unified, this mixture is supplied to an axisymmetric compressor. Devices such as a feed water pipe (310) and spray nozzle (300) are placed in the low-speed zone so as not to obstruct the airstream.

摘要翻译： 在通过将细微水滴喷入入口空气来冷却用于燃气轮机的入口空气的雾化器中，设置喷雾喷嘴（300）以将雾化的雾化水滴从雾化空气流的外边缘喷射到高温 其速度区域朝向气流的中心区域。 雾化气流遇到形成在下游侧的低速区的气流，在两种气流混合统一后，将该混合物供给轴对称压缩机。 诸如给水管（310）和喷嘴（300）的装置被放置在低速区域中，以便不妨碍气流。

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。

公开(公告)号：EP2226468A2

公开(公告)日：2010-09-08

申请号：EP10153679.5

申请日：2010-02-16

申请人： Hitachi Ltd.

发明人： Myoren, Chihiro ,  Takahashi, Yasuo

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  Y02T50/673

摘要： A transonic blade is provided that operates in a flow field where flow has a transonic speed or higher in an axial-flow rotating machine and that concurrently achieves a reduction in shock loss and in the local stress of the blade.
The transonic blade includes a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine; a tip cross-sectional surface located furthest from the hub cross-sectional surface in a spanwise direction which is a vertical direction of the rotating shaft; a leading edge located on an upstream side; and a trailing edge located on a downstream side. At least a part of a passing working fluid flow has a transonic speed or higher. A portion of a stacking line which is a line connecting together respective gravity centers of cross-sectional surfaces located from the hub cross-sectional surface to the tip cross-sectional surface is located on a downstream side of a stacking center in a flow direction of a working fluid main flow.

公开(公告)号：EP2749739A2

公开(公告)日：2014-07-02

申请号：EP13193002.6

申请日：2013-11-15

申请人： Hitachi, Ltd.

发明人： Takahashi, Yasuo ,  Morisaki, Tetsuro ,  Myoren, Chihiro ,  Kawamura, Kohta

IPC分类号： F01D11/24 ,  F02C3/30 ,  F02C7/143

CPC分类号： F01D11/24 ,  F01D11/18 ,  F01D25/26 ,  F02C3/305 ,  F02C7/1435 ,  F05D2270/3062 ,  F05D2300/50212 ,  Y02T50/675

摘要： An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor (1), a casing (54) for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row (51) and one continuous stator vane row (53), the axial compressor (1) being structured so that the liquid drops evaporate inside the compressor (1), wherein the casing (54) is provided with a cavity (64) therein, and the cavity (64) is formed by an outer casing (62) and an inner casing (63) which is enclosing a periphery of the rotor blade rows (51) at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity (64) on a downstream side of a region forming the cavity (64) of the inner casing (63).

摘要翻译： 一种轴向压缩机，包括用于将液滴供给到压缩机（1）的工作流体的液滴供给装置，用于形成工作流体向下流动的流动通道的壳体（54），以及多个级 由一个连续的转子叶片排（51）和一个连续的定子叶片排（53）组成，轴向压缩机（1）构造成使得液滴在压缩机（1）内部蒸发，其中壳体（54） 空腔（64），并且空腔（64）由外壳（62）和内壳（63）形成，内壳（63）在多个阶段包围转子叶片排（51）的周边并在内部形成 工作流体的流动路径和流路，用于将工作流体供给到形成内壳体（63）的空腔（64）的区域的下游侧的空腔（64）。

公开(公告)号：EP2669489A2

公开(公告)日：2013-12-04

申请号：EP13169780.7

申请日：2013-05-29

申请人： Hitachi, Ltd.

发明人： Takashi, Yasuo ,  Myoren, Chihiro ,  Kawamura, Kohta

IPC分类号： F02C3/30 ,  F02C7/143

CPC分类号： F04D29/5846 ,  F01D5/145 ,  F01D25/32 ,  F02C3/30 ,  F02C7/1435 ,  F02C9/18 ,  F04D29/706 ,  F05D2260/212 ,  Y02T50/673 ,  Y02T50/675

摘要： An axial compressor that can remove an attachment within a groove of a casing and recover an effect of suppressing stall on rotor blades, and a gas turbine provided with the axial compressor, are provided. The axial compressor includes a compressor body 6 and a sprayer 9 for spraying droplets in suction gas of the compressor body 6 so that the droplets are introduced into the compressor body 6 and evaporate. The compressor body 6 includes a casing 11, a rotor 12, rotor blades 13, and stator vanes 14. A groove 21 is formed in an inner circumferential surface of the casing 11 so as to be positioned around rotor blades 13 arranged on a front stage side. A purge system 23 is provided that supplies high-pressure air to the groove 21 through communication holes 22.

摘要翻译： 一种轴向压缩机，其可以移除壳体的槽内的附件，并且恢复抑制转子叶片上的失速的效果，以及设置有轴向压缩机的燃气轮机。 轴向压缩机包括压缩机主体6和用于在压缩机主体6的吸入气体中喷射液滴的喷雾器9，使得液滴被引入压缩机主体6并蒸发。 压缩机主体6包括壳体11，转子12，转子叶片13和定子叶片14.在壳体11的内周面上形成槽21，以便围绕设置在前级的转子叶片13 侧。 提供吹扫系统23，其通过连通孔22向槽21提供高压空气。

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：EP2441964A2

公开(公告)日：2012-04-18

申请号：EP11185095.4

申请日：2011-10-13

申请人： Hitachi Ltd.

发明人： Takahashi, Yasuo ,  Myoren, Chihiro

IPC分类号： F04D29/32 ,  F04D29/54

CPC分类号： F04D29/324 ,  F04D29/542 ,  F04D29/544 ,  F05B2240/123 ,  F05B2240/301 ,  Y10T29/49316

摘要： A high performance airfoil of a compressor is provided that can achieve a reduction in secondary loss and in cross flow and ensuring of reliability.
An axial compressor includes a plurality of stator vanes 5 attached to an inner surface of a casing 3 defining an annular flow path and a plurality of rotor blades 4 attached to a rotating rotor 2 defining the annular flow path. A flow path is defined between a pressure surface 22 of a stator vane 5 and a suction surface 21 of a stator vane 5, the vanes being circumferentially adjacent to each other, or between a pressure surface 22 of a rotor blade 4 and a suction surface 23 of a rotor blade 4, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length and an axial flow path width distribution extending from the leading edges 23 to trailing edges 24 of the vanes or the blades defining the flow path therebetween has an inflection point on the downstream side of the throat portion.

摘要翻译： 提供了一种压缩机的高性能翼型件，其可以实现二次损失和交叉流动的减小并确保可靠性。 轴向压缩机包括多个定子叶片5，其附接到壳体3的限定环形流路的内表面，以及多个转子叶片4，其连接到限定环形流动路径的旋转转子2。 在定子叶片5的压力表面22和定子叶片5的吸力表面21之间，叶片彼此周向相邻或在转子叶片4的压力表面22和吸力表面 23是转子叶片4，叶片周向地相邻。 流路形成为使得在流路宽度最小的喉部设置在轴向弦长的50％的上​​游侧和从前缘23延伸到后缘24的轴向流路宽度分布 限定其间的流路的叶片或叶片之间具有在喉部的下游侧的拐点。

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