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1. 发明专利

JP2008031870A Seal structure of gas turbine 审中-公开
标题翻译：气体涡轮机密封结构
公开(公告)号：JP2008031870A
公开(公告)日：2008-02-14
申请号：JP2006203794
申请日：2006-07-26
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NAGAI TOMOHITO
IPC分类号： F02C7/28
摘要： PROBLEM TO BE SOLVED: To provide seal structure of a gas turbine surely suppressing leakage of air from a clearance of a tail pipe seal to the inside of a tail pipe, by properly installing the tail pipe seal.
SOLUTION: In the gas turbine, a plurality of combustors are arranged in a circumferential direction of the turbine, fuel is supplied to compressed air and burnt by the plurality of combustors, and generated combustion gas is supplied to stator blades and moving blades of the turbine so as to acquire rotation power. The gas turbine comprises: the tail pipe seals 50 connecting tail pipes 32 of the plurality of combustors with shrouds 41 of the stator blades and constituted of divided parts 53 which is formed by being circumferentially divided into a plurality of pieces; first seal plates 61 inserted into neighboring divided parts 53 of each tail pipe seal 50 assembled to the tail pipe 32 or the shroud 41 so as to connect them; and a falling-off prevention means 70 preventing slipping off of the first seal plates 61 from the tail pipe seal 50.
COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：通过适当地安装尾管密封件，提供燃气轮机的密封结构，从而可靠地抑制空气从尾管密封件的间隙泄漏到尾管的内部。解决方案：在燃气轮机中，多个燃烧器沿涡轮机的圆周方向布置，燃料被供给到压缩空气并由多个燃烧器燃烧，并且产生的燃烧气体被供应到定子叶片和动叶片以获得旋转动力。燃气轮机包括：尾管密封件50，其将多个燃烧器的尾管32与定子叶片的护罩41连接，并由周向分成多个片形成的分割部分53构成; 第一密封板61插入到组装到尾管32或护罩41上以连接它们的每个尾管密封件50的相邻分隔部分53中; 以及脱离防止装置70，防止第一密封板61从尾管密封件50脱落。版权所有（C）2008，JPO＆INPIT

2. 发明专利

JP2013100747A Gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：JP2013100747A
公开(公告)日：2013-05-23
申请号：JP2011244060
申请日：2011-11-08
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： ISHIKAWA HIROSHI , HIROKAWA KAZUHARU , NAGAI TOMOHITO
IPC分类号： F01D11/00 , F01D25/00 , F02C7/28
摘要： PROBLEM TO BE SOLVED: To provide a sealing structure by which local surface pressure increase due to a rotation preventing member is suppressed, in a gas turbine.SOLUTION: A disc engagement hole 131 is formed in an outer circumferential side ring-like part 130 of an overhung part 100 formed in a rotor disc 11 of a turbine 4. An outer circumferential side seal engagement projection 231 and an outer circumferential side seal engagement hole 232 are formed in the outer circumferential side seal plate pieces 230 of a seal member 200 each comprising a seal plate assembly 210 including an outer circumferential side seal plate piece 230 and an inner circumferential side seal plate piece 220 arranged in a plurality in a ring-like shape along the circumferential direction. An inner circumferential side seal engagement projection 221 is formed in the inner circumferential side seal plate piece 220. By engagement of the disc engagement hole 131 and the outer circumferential side seal engagement projection 231, and the outer circumferential side seal engagement hole 232 and the inner circumferential side seal engagement projection 221, respectively, the outer circumferential side ring-like part 130 and the outer circumferential side seal plate piece 230, and the outer circumferential side seal plate piece 230 and the inner circumferential side seal plate piece 220 are constrained in circumferential movement, respectively.
摘要翻译：要解决的问题：提供一种在燃气轮机中抑制由旋转阻止构件产生的局部表面压力增加的密封结构。解决方案：在涡轮机4的转子盘11上形成的悬臂部分100的外圆周侧环形部分130中形成有盘形啮合孔131.外周侧密封接合突起231和外周侧侧密封接合孔232形成在密封构件200的外周侧密封片230中，密封构件200包括密封板组件210，密封板组件210包括外周侧密封片230和内周侧密封片220，沿圆周方向呈环状。内圆周侧密封接合突起221形成在内周侧密封片件220中。通过盘接合孔131和外周侧密封接合突起231与外周侧密封接合孔232和内周侧密封接合孔232的接合外周侧环状部130和外周侧密封片230以及外周侧密封片230和内周侧密封板片220分别被周向地约束运动。版权所有（C）2013，JPO＆INPIT

3. 发明专利

JP2012189158A Seal structure of rotary shaft 有权
标题翻译：旋转轴的密封结构
公开(公告)号：JP2012189158A
公开(公告)日：2012-10-04
申请号：JP2011053823
申请日：2011-03-11
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： ONISHI TOMOYUKI , HASHIMOTO YUKIHIRO , NAGAI TOMOHITO , KATO EIGO , UEDA MOTOHARU , TEZUKA NORIKAZU
IPC分类号： F16J15/22 , F04B39/00
摘要： PROBLEM TO BE SOLVED: To provide a seal structure for a rotary shaft using a spring whose characteristic is changed according to a displacement amount or an operating situation.SOLUTION: The seal structure of the rotary shaft includes a groove formed annularly at the inside circumference of a casing around the rotary shaft, a plurality of arcuate segments arranged annularly in the groove, and a brush installed at the inside surface of the segments in a way that it comes into contact with the peripheral surface of the rotary shaft to seal the rotary shaft. The seal structure is configured such that an initially coned leaf spring 21 and a coil spring 14 are connected in series to constitute a spring structure and is arranged between the groove inside surface 3b and the peripheral surfaces of the segments, thereby pressing the segments toward the rotary shaft.
摘要翻译：要解决的问题：提供一种使用弹簧的旋转轴的密封结构，该弹簧的特性根据位移量或操作情况而改变。解决方案：旋转轴的密封结构包括围绕旋转轴的壳体的内圆周环形地形成的凹槽，环形地设置在凹槽中的多个弧形段，以及安装在该内侧表面的刷以与旋转轴的圆周表面接触的方式密封旋转轴。密封结构被构造成使得最初的锥形板簧21和螺旋弹簧14串联连接以构成弹簧结构，并且布置在槽内表面3b和段的周边表面之间，从而将段压向旋转轴。版权所有（C）2013，JPO＆INPIT

4. 发明专利

JP2008025910A Gas turbine combustor 审中-公开
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2008025910A
公开(公告)日：2008-02-07
申请号：JP2006198676
申请日：2006-07-20
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NAGAI TOMOHITO , KATO EIGO , NOSE MASAKAZU
IPC分类号： F23R3/28 , F02C7/232 , F23R3/32 , F23R3/34
摘要： PROBLEM TO BE SOLVED: To extend the life in a gas turbine combustor by reducing stress acting on a connection part between a fuel pipe and a cover to thereby improve strength.
SOLUTION: This gas turbine combustor comprises an air passage 44 provided between a combustor outer cylinder 21 and a combustor inner cylinder 32, and a top hat nozzle 37 for injecting top hat fuel to the air passage 44. A fuel cavity 49 is formed along the circumferential direction by forming a recessed part 61 in a top hat 47 constituting the combustor outer cylinder 31 by the top hat nozzle 37, and fixing a cover 62 covering the recessed part 61, and fuel passages 50 and 51 connecting the fuel cavity 49 to a peg 52 fixed to the inside surface of the top hat 47 are provided in the top hat 47. A boss 65 is connected to the tip of a fuel pipe 64. The boss 65 is fitted to a connecting hole 62a formed at the cover 62 and fixed by welding W
4 , and a curved part 65a is formed at the boss 65 by fillet machining.
COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：通过减少作用在燃料管和盖之间的连接部分上的应力来延长燃气轮机燃烧器中的寿命，从而提高强度。解决方案：该燃气轮机燃烧器包括设置在燃烧器外筒21和燃烧器内筒32之间的空气通道44，以及用于将顶帽燃料喷射到空气通道44的顶帽喷嘴37.燃料腔49 通过顶帽喷嘴37在构成燃烧器外筒31的顶帽47中形成凹部61，并且固定覆盖凹部61的盖62和连接燃料腔的燃料通路50,51沿圆周方向形成 49固定在顶帽47的内表面上的栓钉52设置在顶帽47中。凸台65连接到燃料管64的末端。凸台65装配到形成在顶帽47上的连接孔62a 盖62并通过焊接固定W 4 ，并且通过圆角加工在凸台65上形成弯曲部65a。版权所有（C）2008，JPO＆INPIT

5. 发明专利

JP2008261605A Gas turbine combustor 审中-公开
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2008261605A
公开(公告)日：2008-10-30
申请号：JP2007106415
申请日：2007-04-13
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NAGAI TOMOHITO , KATO EIGO , KONISHI SATORU
IPC分类号： F23R3/28 , F02C7/22 , F23R3/30
CPC分类号： F23R3/34 , F02C7/222 , F02C7/224 , F05D2260/20 , F05D2270/082 , F23D2211/00 , F23R3/286 , F23R3/44 , F23R2900/00005
摘要： PROBLEM TO BE SOLVED: To extend a service life by reducing the stress applied to a connection part of a top hat part in a gas turbine combustor.
SOLUTION: A top hat part 47 having top hat nozzles 37 has a top hat body 61 formed with a plurality of first fuel passages 66 in a circumferential direction and formed with a cavity 49 with which the first fuel passages 66 communicate, by covering a recess 65 with a cover 62. An inner ring 63 and an outer ring 64 are connected to the top hat body 61 and connected to each other to form a second fuel passage 67 communicating with the first fuel passages 66. A peg 52 is fixed to the inner ring 63 to communicate with the second fuel passage 67 through a third fuel passage 68. The inner ring 63 and the outer ring 64 are provided with thin-walled parts 63b, 64b serving as a thermal elongation absorbing means for absorbing thermal elongation.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：通过减小施加到燃气轮机燃烧器中的顶帽部分的连接部分的应力来延长使用寿命。解决方案：具有顶帽喷嘴37的顶帽部分47具有顶帽主体61，该顶帽主体61沿圆周方向形成有多个第一燃料通道66，并且形成有第一燃料通道66与之连通的空腔49，用盖62覆盖凹部65.内环63和外环64连接到顶帽主体61并彼此连接以形成与第一燃料通道66连通的第二燃料通道67.钉52是固定在内环63上，通过第三燃料通道68与第二燃料通道67连通。内环63和外环64设有薄壁部分63b，64b，用作热伸长吸收装置，用于吸热伸长。版权所有（C）2009，JPO＆INPIT

6. 发明专利

JP2007309247A Gas turbine 审中-公开
标题翻译：燃气轮机
公开(公告)号：JP2007309247A
公开(公告)日：2007-11-29
申请号：JP2006140198
申请日：2006-05-19
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NAGAI TOMOHITO , HASHIMOTO YUKIHIRO , KATO EIGO , KONISHI SATORU
IPC分类号： F02C7/18 , F02C7/00 , F23R3/42
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine capable of suppressing the occurrence of a crack in an outlet part of a cooling air passage in an inner cylinder or a tail pipe of a combustor.
SOLUTION: This gas turbine is equipped with the combustor for generating combustion gas. Further, the combustor includes the tail pipe and the inner cylinder constituting a passage for the combustion gas, and the cooling air passage 322 in a wall part 321 of the tail pipe or a wall part of the inner cylinder. Further, chamferring is applied to an edge on the combustion gas passage side of the outlet part 324 opening to the combustion gas passage out of the outlet part of the cooling air passage 322.
COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提供一种能够抑制在燃烧器的内筒或尾管中的冷却风道的出口部分发生裂纹的燃气轮机。
解决方案：该燃气轮机配备有用于产生燃烧气体的燃烧器。此外，燃烧器包括构成燃烧气体的通路的尾管和内筒，以及尾管的壁部321或内筒的壁部的冷却空气通路322。此外，在从冷却风通道322的出口部分向燃烧气体通道开口的出口部分324的燃烧气体通道侧上的边缘施加倒角。（C）2008，JPO＆INPIT

7. 发明专利

JP2007120340A Combustor tail pipe seal structure of gas turbine 审中-公开
标题翻译：气体涡轮机尾气管密封结构
公开(公告)号：JP2007120340A
公开(公告)日：2007-05-17
申请号：JP2005310632
申请日：2005-10-26
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NAGAI TOMOHITO , HASHIMOTO YUKIHIRO , KONDO MITSURU , KATO EIGO , KONISHI SATORU , TADA HIROHARU , IMAE TOMOHIRO
IPC分类号： F02C7/28 , F01D9/04 , F01D11/00 , F01D25/00 , F16J15/08
摘要： PROBLEM TO BE SOLVED: To easily realize a connecting structure of a combustor tail pipe outlet and a gas path inlet of a gas turbine by enhancing the seal effect.
SOLUTION: A tail pipe 10 of a combustor is arranged in an annular shape in a plurality, and a first stage stationary blade 20 forming the inlet of a gas path is also constituted by arranging a plurality of stationary blade dividing pieces 20a in an annular shape. A seal 30 for connecting a part between the outlet of the tail pipe 10 and the first stage stationary blade 20 is also constituted by arranging a plurality of seal dividing pieces 30a in an annular shape. The stationary blade dividing pieces 20a are formed as a segment by respectively connecting a plurality. A connecting plate 27 and a bolt 28 are used for the connection.
COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：要解决的问题：通过提高密封效果，能够容易地实现燃气轮机的燃烧器尾管出口和燃气轮机的气体入口的连接结构。解决方案：燃烧器的尾管10以多个环形形式设置，形成气体通道入口的第一级固定叶片20也通过将多个固定叶片分割片20a设置在环形。用于连接尾管10的出口和第一级固定叶片20之间的部分的密封件30还通过将多个密封分割片30a布置成环形而构成。固定叶片分割片20a通过分别连接多个形成为一段。连接板27和螺栓28用于连接。版权所有（C）2007，JPO＆INPIT

8. 发明专利

JP2011190717A Cooling jacket of combustor, combustor equipped with the same, and gas turbine equipped with the combustor 审中-公开
标题翻译：燃烧器的冷却夹板，与其配套的燃气轮机和配备燃气机的燃气涡轮机
公开(公告)号：JP2011190717A
公开(公告)日：2011-09-29
申请号：JP2010056084
申请日：2010-03-12
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NAGAI TOMOHITO , KONISHI SATORU , KINOSHITA YASUKI
IPC分类号： F02C7/18 , F01D25/12 , F02C7/00 , F02C7/20 , F23R3/42
摘要： PROBLEM TO BE SOLVED: To provide a cooling jacket of a combustor which maintains the soundness of the cooling jacket against a generated thermal stress, and to provide the combustor equipped with the same and a gas turbine equipped with the combustor.
SOLUTION: The cooling jacket of the combustor includes a cylindrical wall 2 into which combustion gas flows, an outer cylinder 4 provided annularly around the outer periphery of the wall 2 and forming a refrigerant passage 17 for passage of a refrigerant between the same and the wall 2, and a plurality of ribs 16 connecting the outer cylinder 4 to the wall 2. The plurality of ribs 16 have legs each widening toward the wall 2 and the legs are connected to the wall 2 by welding.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种燃烧器的冷却套，其保持冷却套的健全性抵抗所产生的热应力，并提供配备有相同燃烧器的燃烧器和配备有燃烧器的燃气轮机。解决方案：燃烧器的冷却套包括：燃烧气体流过的圆筒壁2;围绕壁2的外周环形设置的外筒4，并形成制冷剂通道17，用于使制冷剂在其间通过壁2，以及将外筒4连接到壁2的多个肋16.多个肋16具有朝向壁2的朝向两侧的腿部，并且腿通过焊接与壁2连接。版权所有（C）2011，JPO＆INPIT

9. 发明专利

JP2009103097A Gas turbine and rotor for gas turbine 审中-公开
标题翻译：用于气体涡轮的气体涡轮机和转子
公开(公告)号：JP2009103097A
公开(公告)日：2009-05-14
申请号：JP2007277717
申请日：2007-10-25
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NAGAI TOMOHITO , KATO EIGO , UEDA MOTOHARU , TANITSUJI HIRONORI
IPC分类号： F01D5/06 , F01D25/00 , F02C7/00 , F04D29/32 , F04D29/64
摘要： PROBLEM TO BE SOLVED: To provide a rotor for a gas turbine capable of securing necessary strength according to parts while attaining weight reduction.
SOLUTION: In the compressor rotor 20 of the gas turbine 1, some rotor disks 32, 34, 36, 38 among a plurality of rotor disks 24, 26, 28, 32, 34, 36, 38 are connected by welding and the other rotor disks 24, 26, 28 are connected with circumferential bolts 52 arrayed in a circumferential direction of a rotor rotation axis. In the parts where strength is not relatively required, the weight reduction is attained as the entire rotor by connecting the rotor disks 32, 34, 36, 38 by welding to form a welded connection 30 and in the parts where strength is required, the required strength is secured by connecting the rotor disks 24, 26, 28 with the circumferential bolts 52 to form a bolted connection 22.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种能够在减轻重量的同时确保根据部件所需的强度的燃气轮机的转子。解决方案：在燃气轮机1的压缩机转子20中，多个转子盘24,26,28,32,34,36,38中的一些转子盘32,34,36,38通过焊接和其他转子盘24,26,28与沿转子旋转轴的圆周方向排列的周向螺栓52连接。在不需要强度的部位，通过焊接将转子盘32,34,36,38连接起来形成焊接连接部30，并且在需要强度的部位，通过转子盘32,34,36,38的整个转子实现重量减轻，通过将转子盘24,26,28与周向螺栓52连接以形成螺栓连接22来确保强度。版权所有（C）2009，JPO＆INPIT

10. 发明专利

JP2008144617A Gas turbine casing structure 审中-公开
标题翻译：气体涡轮机结构
公开(公告)号：JP2008144617A
公开(公告)日：2008-06-26
申请号：JP2006330135
申请日：2006-12-07
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NAGAI TOMOHITO , KATO EIGO , UEDA MOTOHARU
IPC分类号： F01D25/24 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To prevent the occurrence of oval deformation by eliminating deviation of temperature distribution in a casing. SOLUTION: A rotor 106 is disposed inside the casing 101. The casing 101 comprises an upper casing 102 and a lower casing 103 connected by fastening flanges 102a, 103a with bolts 104. The flanges 102a, 103a are formed with air passages 120, 130, 140, and high temperature gas enters also the air passages 120, 130, 140. Flange connection parts (γ parts) thereby rise/fall in temperature with the same temperature follow-up property as other parts (α, β parts) of the casing 101 to prevent the occurrence of oval deformation. Clearances can thereby be set narrow without considering oval deformation, and the efficiency of a gas turbine is improved. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：通过消除壳体中温度分布的偏差来防止椭圆形变形的发生。解决方案：转子106设置在壳体101的内部。壳体101包括通过具有螺栓104的紧固凸缘102a，103a连接的上壳体102和下壳体103.凸缘102a，103a形成有空气通道120 ，130，140，高温气体也进入空气通道120,130,140。法兰连接部分（γ部分）因此随着其他部分（α，β部分）具有相同的温度追随性而升高/降低以防止椭圆形变形的发生。因此，可以将间隙设定得窄而不考虑椭圆形变形，提高燃气轮机的效率。版权所有（C）2008，JPO＆INPIT

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