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1. 发明专利

JP2010151045A Turbine blade and gas turbine 有权
标题翻译：涡轮叶片和气体涡轮
公开(公告)号：JP2010151045A
公开(公告)日：2010-07-08
申请号：JP2008330613
申请日：2008-12-25
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UEDA OSAMU , HAMANA HIROYUKI , SEKI NAOYUKI , ARASE KENICHI
IPC分类号： F04D29/54 , F01D25/04
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade and a gas turbine which can attenuate oscillation caused by an excitation force and facilitate assembly and disassembly. SOLUTION: The turbine blade comprises a shroud section 13 disposed at the end of an aerofoil section 12, an end housing 14 which is slidably movable relative to and detachable/attachable from/to the shroud section 13 and forms space between the end housing 14 and the shroud section 13, an elastic section 15 which is disposed in the space and energizes the shroud section 13 and the end housing 14 to be separated from each other, and a friction section 16 disposed between the elastic section 15 and the shroud section 13 while being movable close to and away from the shroud section 13 and being disposed relatively movable to the shroud section 13. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种能够衰减由激励力引起的振荡的涡轮叶片和燃气轮机，并且便于组装和拆卸。解决方案：涡轮叶片包括设置在机翼部分12的端部处的护罩部分13，端部壳体14，其可相对于护罩部分13相对于可拆卸/可拆卸/可连接到壳部分13并且在端部壳体14的端部之间形成空间壳体14和护罩部分13，弹性部分15，其设置在该空间中，并且使护罩部分13和端部壳体14彼此分离，以及设置在弹性部分15和护罩之间的摩擦部分16 部分13，同时能够靠近和远离护罩部分13移动并且被布置成相对于护罩部分13可移动。版权所有（C）2010，JPO＆INPIT

2. 发明专利

JP2004084572A Stationary blade structure of rotating machine 审中-公开
标题翻译：旋转机械的叶片结构
公开(公告)号：JP2004084572A
公开(公告)日：2004-03-18
申请号：JP2002247276
申请日：2002-08-27
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： MORI KAZUISHI , HAMANA HIROYUKI , OWAKI TOSHIKAZU , MATSUI KAZUHIRO
IPC分类号： F01D9/04 , F01D9/02 , F04D29/56
摘要： PROBLEM TO BE SOLVED: To provide a stationary blade structure of a rotating machine, wherein an asymmetric stationary blade structure to reduce cascade interference exciting force can be easily changed and adjusted, and it is materialized at a low cost.
SOLUTION: A stationary blade 1 is fixed between an outside stationary blade ring 2 inserted in a groove in the inside of a vehicle chamber to carry out positioning in the direction of the vehicle chamber and an inside stationary ring 3 provided with a sealing device s to prevent air flow from leaking between the peripheral surface of a rotor 4 and the device. To be concrete, a bolt 1a extending outward from one end of the stationary blade 1 is inserted in a mounting hole 2a opened in the outside stationary blade ring 2 and is fastened by a nut 5. Also, a bolt 1b extending inward from the other end of the stationary blade 1 is inserted in a mounting hole 3a opened in the inside stationary blade ring 3 and is fastened by a nut 6. Optional and different dimensions are set for the arrangement pitches of the mounting holes 2a opened in the outside stationary blade ring 2, and the arrangement pitches of the mounting holes 3a opened in the inside stationary blade ring 3 are set so as to correspond to them.
COPYRIGHT: (C)2004,JPO
摘要翻译：要解决的问题：为了提供一种旋转机械的固定叶片结构，其中可以容易地改变和调整用于减小级联干扰激励力的非对称固定叶片结构，并且以低成本实现。解决方案：固定刀片1固定在插入车室内部的槽中的外侧固定刀片环2之间，以沿着车辆室的方向进行定位，内侧固定环3设置有密封装置，以防止空气在转子4的外周表面和装置之间泄漏。具体而言，从固定叶片1的一端向外侧延伸的螺栓1a被插入到在外侧固定叶片环2上开口的安装孔2a中，并由螺母5紧固。而且，从另一侧向内延伸的螺栓1b 固定刀片1的端部插入到在内侧固定刀片环3中开口的安装孔3a中，并通过螺母6紧固。可选择和不同的尺寸用于在外部固定刀片中打开的安装孔2a的布置间距环2，并且在内侧固定叶片环3中开口的安装孔3a的配置间距被设定为与其对应。版权所有（C）2004，JPO

3. 发明专利

JP2011032869A Operating method of gas turbine and gas turbine 有权
标题翻译：气体涡轮机和气体涡轮机的运行方法
公开(公告)号：JP2011032869A
公开(公告)日：2011-02-17
申请号：JP2009176832
申请日：2009-07-29
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HAMANA HIROYUKI
IPC分类号： F02C9/20 , F02C9/00 , F02C9/28
摘要： PROBLEM TO BE SOLVED: To provide an operating method of a gas turbine and a gas turbine by which the reliability of the gas turbine can be secured and an increase in cost and the deterioration of power generation efficiency can be prevented. SOLUTION: The method is compose of a detection step S1 for detecting a temperature of air sucked by a compressor, an opening degree calculation step S2 for calculating an opening degree of an inlet guide vane at least based on the output of a gas turbine and the temperature of air sucked by a compressor, comparison operation steps S3, S4 for comparing whether or not the calculated opening degree of the inlet guide vane exceeds a limit value of an IGV opening degree which is determined by the temperature of air sucked by the compressor, and a control step S5 for controlling the opening degree of the inlet guide vane to the calculated opening degree when the calculated opening degree of the inlet guide vane does not exceed the limit value of the IGV opening degree and controlling the opening degree of the inlet guide vane to the opening degree not exceeding the limit value of the IGV opening degree when the calculated opening degree of the inlet guide vane exceeds the limit value of the IGV opening degree. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种能够确保燃气轮机的可靠性的燃气轮机和燃气轮机的操作方法，并且可以防止成本的增加和发电效率的劣化。解决方案：该方法包括用于检测由压缩机吸入的空气的温度的检测步骤S1，至少基于气体的输出来计算入口导叶的开度的开度计算步骤S2 涡轮机和由压缩机吸入的空气的温度的比较操作步骤S3，S4，用于比较所计算的入口导叶的开度是否超过由所吸入的空气的温度确定的IGV开度的极限值压缩机，以及控制步骤S5，用于当所计算的入口导叶的开度不超过IGV开度的极限值并控制开口程度时控制入口导叶的开度达到计算的开度当所计算出的入口引导叶片的开度超过t的极限值时，入口导向叶片的开度不超过IGV开度的极限值他IGV开学。版权所有（C）2011，JPO＆INPIT

4. 发明专利

JP2013224636A Evaluation method for blade shape, program for executing the method, and device for executing the method 有权
标题翻译：用于叶片形状的评估方法，用于执行该方法的程序和用于执行该方法的装置
公开(公告)号：JP2013224636A
公开(公告)日：2013-10-31
申请号：JP2012097867
申请日：2012-04-23
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： FUKUHARA YOSHIYA , HAMANA HIROYUKI
IPC分类号： F01D5/14 , F01D25/00 , G01M99/00
摘要： PROBLEM TO BE SOLVED: To efficiently execute sufficient evaluation with respect to a blade shape from viewpoints of the blade vibration and the blade strength.SOLUTION: From each of design data and measured data of a blade 1, the blade thickness for each of a plurality of evaluation locations L1-L8 defined by a location decision rule, is obtained. Next, the blade thickness for each of the plurality of the evaluation locations in the blade design is compared with the blade thickness for each of the plurality of the evaluation locations in the actual blade, the blade shape is evaluated. The plurality of the evaluation locations L1-L8 defined by the location decision rule are locations on a chord central line C, namely, a maximum blade thickness location L4, a predetermined front edge reference location L1 on the front edge side, each of the divided locations L2, 3 in dividing the span ranging from the maximum blade thickness location L4 to the front edge reference location L1 into plurality by the predetermined front side division rule, a predetermined rear edge reference location L8 on the rear edge side, and each of the divided locations L5-7 in dividing the span ranging from the maximum blade thickness location L4 to the rear edge reference location L8 into plurality according to the rear side division rule.
摘要翻译：要解决的问题：从叶片振动和叶片强度的观点来看，有效地执行关于叶片形状的充分评估。解决方案：根据叶片1的设计数据和测量数据，从每个设计数据和多个叶片厚度获得由位置决定规则定义的评价位置L1-L8。接下来，将叶片设计中的多个评估位置中的每一个的叶片厚度与实际叶片中的多个评估位置中的每一个的叶片厚度进行比较，评估叶片形状。由位置决定规则定义的多个评价位置L1〜L8是和弦中心线C上的位置，即最大叶片厚度位置L4，前缘侧的预定前缘基准位置L1，将从最大刀片厚度位置L4到前边缘基准位置L1的范围从预定的前侧分割规则划分成多个的位置L2,3，后边缘侧的规定后边缘基准位置L8，分割位置L5-7根据后方分割规则将从最大叶片厚度位置L4到后边缘基准位置L8的范围分成多个。

5. 发明专利

JP2010151046A Turbine blade and gas turbine 有权
标题翻译：涡轮叶片和气体涡轮
公开(公告)号：JP2010151046A
公开(公告)日：2010-07-08
申请号：JP2008330614
申请日：2008-12-25
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UEDA OSAMU , HAMANA HIROYUKI , SEKI NAOYUKI , ARASE KENICHI
IPC分类号： F01D9/02 , F01D25/00
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade and a gas turbine attenuating vibration caused by excitation force and facilitating replacement of an elastic member such as a spring.
SOLUTION: The turbine blade includes: a shroud part 13 disposed at an end of an airfoil part 12; an end casing 14 which can slide on, be attached to and detached from the shroud part 13, and forms a space with the shroud part 13; and an elastic part 15 which is disposed in the space, energizes the shroud part 13 and a tip casing 14 in a separation direction, and is disposed movably relatively to the shroud part 13.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种涡轮叶片和燃气轮机，其衰减由激励力引起的振动，并且有助于更换诸如弹簧的弹性部件。解决方案：涡轮机叶片包括：设置在翼型部分12的端部处的护罩部分13; 能够在护罩部13上滑动并与护罩部13分离的端部壳体14，与护罩部13形成空间; 以及设置在该空间内的弹性部15，使护罩部13和前端壳14沿分离方向通电，并相对于护罩部13可移动地设置。（C）2010，JPO＆INPIT

6. 发明专利

JP2009002338A Stationary blade ring, axial flow compressor using the same, and method for repairing stationary blade ring 有权
标题翻译：固定式叶片环，使用其的轴流式压缩机以及修理静态叶片环的方法
公开(公告)号：JP2009002338A
公开(公告)日：2009-01-08
申请号：JP2008156728
申请日：2008-06-16
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HAMANA HIROYUKI , NAKAMURA IKUO
IPC分类号： F04D29/54 , F04D29/60
摘要： PROBLEM TO BE SOLVED: To provide a stationary blade ring, capable of restricting risk of thermal deformation and strength deterioration, securing a degree of freedom regarding the shape, and improving compression performance.
SOLUTION: The stationary blade ring is provided with a stationary blade member 21, having an inner shroud part 31 and an outside shroud part 29 integrally formed with both end parts of a stationary blade 27 as parted to correspond to each piece of the stationary blade 27, and a coupling member 23, formed of an arc-shaped plate member, and installed on the opposite side to a plurality of stationary blades 27 on at least either the inner shroud part 31 or the outer shroud part 29 of the stationary member 21 adjoining each other in the circumferential direction. The stationary blade member 21 is welded with the coupling member 23 in part of its circumferential length to form a stationary blade ring segment 19.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供能够限制热变形和强度劣化的风险的固定叶片环，确保形状的自由度，并提高压缩性能。解决方案：固定叶片环设置有固定叶片构件21，其具有与固定叶片27的两个端部一体形成的内部护罩部分31和外部护罩部分29，该固定叶片构件21被分开以对应于每个固定叶片27和由弧形板构件形成的联接构件23，并且安装在与静止叶片27的内部护罩部分31或外部护罩部分29的至少一个上的多个静止叶片27的相对侧上构件21在圆周方向上彼此邻接。固定叶片构件21在其圆周长度的一部分中与联接构件23焊接以形成固定叶片环段19.版权所有（C）2009，JPO＆INPIT

7. 发明专利

JP2010281224A Gas turbine and plant equipped with the same 有权
标题翻译：燃气涡轮机和设备配备
公开(公告)号：JP2010281224A
公开(公告)日：2010-12-16
申请号：JP2009133393
申请日：2009-06-02
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HAMANA HIROYUKI
IPC分类号： F02C9/18 , F01D25/00
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine capable of reducing pressure loss of a working fluid due to the piping configuration to connect a compressor with a gas exhaust duct, allowing compact layout of the piping, and reducting the piping cost, and to provide a plant equipped with such a gas turbine.
SOLUTION: The gas turbine is equipped with a compressor for compressing the working fluid; a combustor to combust the fuel and the compressed working fluid; a turbine rotated by the combustion gas produced by the combustor, the exhaust duct through which the combustion gas having rotated the turbine is led; and a gas bleed pipes 5 through which the working fluid is introduced from the compressor middle stage and led out to the exhaust duct, wherein the gas bleed pipe 5 has a bend 18, and the bend 18 has a bending angle such that the axial direction of the gas bleed pipe 5 connected to the downstream, with respect to the axial direction of the gas bleed pipe 5 connected to the upstream is less than 90°.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：为了提供一种燃气轮机，其能够减少由于配管构造而导致的工作流体的压力损失，从而将压缩机与排气管连接起来，能够实现管路的紧凑布置，还原管路成本，并提供配备有这种燃气轮机的设备。解决方案：燃气轮机配备有用于压缩工作流体的压缩机; 用于燃烧燃料和压缩的工作流体的燃烧器; 通过由燃烧器产生的燃烧气体旋转的涡轮机，引导涡轮机旋转的燃烧气体的排气管道; 以及排气管5，工作流体从压缩机中间段引入其中并被引出到排气管，其中排气管5具有弯曲部18，弯曲部18具有弯曲角度，使得轴向方向连接到下游的排气管5相对于连接到上游的排气管5的轴向小于90°。版权所有（C）2011，JPO＆INPIT

8. 发明专利

JP2003028097A Axial compressor and gas turbine 审中-公开
标题翻译：轴流压缩机和气体涡轮机
公开(公告)号：JP2003028097A
公开(公告)日：2003-01-29
申请号：JP2001217115
申请日：2001-07-17
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： MATSUMOTO KAZUYUKI , UCHIDA SUMIO , HAMANA HIROYUKI
IPC分类号： F02C3/06 , F04D29/38 , F04D29/54
摘要： PROBLEM TO BE SOLVED: To suppress the occurrence of the higher mode resonance of the rotor blades of an axial compressor having thin-walled blades.
SOLUTION: This axial compressor comprises stator blades and rotor blades forming a multi-stage cascade disposed along a rotatably supported rotor. The leading edges 14a of the rotor blades 14 are curved in the same arched shapes as those of the trailing edges of the stator blades 12, or the trailing edges of the stator blades 12 are formed in radially extending linear shapes in the same shapes as those of the leading edges of the rotor blades 14.
COPYRIGHT: (C)2003,JPO
摘要翻译：要解决的问题：为了抑制具有薄壁叶片的轴向压缩机的转子叶片的较高模式共振的发生。解决方案：该轴向压缩机包括定子叶片和转子叶片，其形成沿着可旋转地支撑的转子设置的多级联级联。转子叶片14的前缘14a以与定子叶片12的后缘相同的弓形形状弯曲，或者定子叶片12的后缘形成为径向延伸的直线形状，其形状与的转子叶片14的前缘。

9. 发明专利

JPH11200808A COMPRESSOR STATIONARY BLADE 失效
公开(公告)号：JPH11200808A
公开(公告)日：1999-07-27
申请号：JP151298
申请日：1998-01-07
申请人： MITSUBISHI HEAVY IND LTD
发明人： HAMANA HIROYUKI
IPC分类号： F01D9/02 , F01D9/04
摘要： PROBLEM TO BE SOLVED: To avoid resonance of excitation force and a natural frequency of a moving blade, and to prevent damage of the moving blade by the resonance by setting circumferential directional arrangement of stationary blades to an unequal pitch in the stationary blades to control an air flow flowing in the moving blade arranged on the stationary blade backwash side of a compressor. SOLUTION: In a compressor stationary blade 13 to control an air flow flowing in a moving blade, circumferential directional arrangement of an inserting hole 12 arranged by penetrating through an outside casing 11, is set so as to become different between the stationary blade number of the upper half part of the outside casing 11 and the stationary blade number of the lower half part. That is, a stationary blade 2 arranged in the upper half part of an air passage 7 is set to an upper half pitch angle (θ2 =9.43 deg.), and a stationary blade 2 arranged in the lower half part is set to a lower half pitch angle (θ1 =8.57 deg.). Thus, in the stationary blades 2 respectively arranged in the upper half part and the lower half part of the air passage 7, an interval between adjacent stationary blades 2 is set to a mutually different dimension to avoid generation of resonance of excitation force and a natural frequency of the moving blade.

10. 发明专利

JPH11229898A START-UP CONTROL DEVICE OF GAS TURBINE 失效
公开(公告)号：JPH11229898A
公开(公告)日：1999-08-24
申请号：JP3727898
申请日：1998-02-19
申请人： MITSUBISHI HEAVY IND LTD
发明人： HAMANA HIROYUKI
IPC分类号： F02C3/30 , F02C7/26 , F02C7/268 , F02C7/27 , F02C7/275
摘要： PROBLEM TO BE SOLVED: To increase start-up energy by outputting an OPEN signal to a steam control valve when the detection value of the turbine inlet gas temperature exceeds the limit value at the time of start-up of the gas turbine, sending steam of a predetermined pressure to a combustor, which is then supplied with combustion gas from the combustor to the turbine. SOLUTION: At start-up of the gas turbine, a start-up motor 6 is driven which rotates a compressor 1 and a turbine 5. At this time, the turbine inlet gas temperature rises with the increase in the output of the gas turbine 6. A temperature sensor 11 detects this gas temperature and inputs it to a valve control device 9, where it is compared with the limit value. When the detected gas temperature reaches or exceeds the limit value, a valve opening signal is output to a steam control valve 7. With the opening of this steam control valve 7, steam of a predetermined pressure from a steam pipe 8b is sent to a combustor 4, and is then supplied with combustion gas from the combustor 4 to the turbine 5. As a result, energy during start-up is increased, thereby improving startability.

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