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1. 发明专利

JP2014194221A Fluid channel structure and gas turbine exhaust diffuser 有权
标题翻译：流体通道结构和气体涡轮排气歧管
公开(公告)号：JP2014194221A
公开(公告)日：2014-10-09
申请号：JP2014139971
申请日：2014-07-07
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： SAKAMOTO YASUAKI , ITO EISAKU , WAKAZONO SUSUMU
IPC分类号： F01D25/30 , F01D25/24 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To provide a fluid channel structure which suppresses the generation of a pressure loss, and a gas turbine exhaust diffuser.SOLUTION: In a fluid channel structure, constructions 12, 13 extend in a direction intersecting with a main flow direction along a main flow of fluid E which flows in a fluid channel P from wall faces 10b, 11b forming the fluid channel P, and a cross section area of the fluid channel P is varied as progressing toward the main flow direction due to the occupation of a part of the fluid channel P by the constructions 12, 13 in a fluid channel cross section which interests with the main flow. The fluid channel structure has recess forming regions 20, 30 in which recesses 21, 22, 31 and 32 are formed at the wall faces 10b, 11b all over a range including the constructions 12, 13 in the main flow direction and a circumferential direction.
摘要翻译：要解决的问题：提供抑制压力损失产生的流体通道结构和燃气轮机排气扩散器。解决方案：在流体通道结构中，结构12,13沿与主流动方向相交的方向延伸流体通道P从形成流体通道P的壁面10b，11b流动的流体E的主流以及流体通道P的横截面积随着主流动方向的进行而变化在与主流感兴趣的流体通道截面中的结构12,13的流体通道P的一部分。流体通道结构具有凹部形成区域20,30，在壁面10b，11b中，在主流动方向和圆周方向上包括构造体12,13的范围内形成有凹部21,22,31,32。

2. 发明专利

JP2013076412A Blade body and rotary machine 有权
标题翻译：叶片机和旋转机
公开(公告)号：JP2013076412A
公开(公告)日：2013-04-25
申请号：JP2013013722
申请日：2013-01-28
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： SAKAMOTO YASUAKI , ITO EISAKU , KITAGAWA HITOSHI , WAKAZONO SUSUMU
IPC分类号： F01D5/14 , F01D1/04 , F04D29/38
摘要： PROBLEM TO BE SOLVED: To provide a blade body and a rotary machine, that can reduce flow losses resulted from wakes from a blade trailing edge which is generated by separation of the flow on the blade surface, and reduce flow path resistance.SOLUTION: The blade body includes a body portion 4 having a dorsal surface 2 and a ventral surface 3, and a trailing edge portion 6 connecting the dorsal surface 2 and the ventral surface 3 with a continuous curved surface 5. The curved surface 5 of the trailing edge portion 6 is reduced in a radius of curvature gradually toward a trailing end 7 which is located at the most downstream side in a flow direction of fluid from either one of the dorsal surface 2 and the ventral surface 3 so that the radius of curvature is the smallest at the trailing end 7. The radius of curvature is then gradually increased from the trailing end 7 toward the other blade side of the dorsal surface 2 or the ventral surface 3, and the curved surface reaches the other of the dorsal surface 2 and the ventral surface 3, and the trailing end 7 is disposed on an extension line 10 of a camber line 9 of the body portion 4.
摘要翻译：要解决的问题：提供一种刀片体和旋转机械，其可以减少由叶片表面上的流动分离而产生的叶片后缘产生的擦拭而导致的流动损失，并减小流路阻力。解决方案：刀体包括具有背表面2和腹面3的主体部分4以及将背面2和腹面3连接成具有连续弯曲表面5的后缘部分6。后缘部6的后端部5的曲率半径逐渐朝着从背面2和腹面3中的任一个流体的流动方向位于最下游侧的后端7，曲率半径在尾端7处最小。然后，曲率半径从后端7朝向背面2或腹面3的另一个叶片侧逐渐增加，并且曲面到达另一个背表面2和腹面3，后端7设置在主体部分4的弯曲线9的延伸线10上。（C）2013，JPO和INPIT

3. 发明专利

JP2012202280A Gas turbine cooling structure 审中-公开
标题翻译：气体涡轮冷却结构
公开(公告)号：JP2012202280A
公开(公告)日：2012-10-22
申请号：JP2011066981
申请日：2011-03-25
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： SAKAMOTO YASUAKI , ITO EISAKU , HANEDA SATORU
IPC分类号： F01D5/18 , F02C7/18
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine cooling structure capable of improving cooling performance by causing film air to flow along a wall surface of a gas turbine composition member without peeling the film air at the outlet of a cooling hole even when the extension ratio of the cooling hole is increased.SOLUTION: The gas turbine cooling structure includes the cooling hole 1 for causing the film air to flow along the wall surface of the constitutional member on the wall part of the gas turbine composition member, wherein a concave part 2 having a smooth curved surface is formed at least on the wall surface 11a of the upstream side of the cooling hole 1 in the flow direction of the main flow of combustion gas.
摘要翻译：解决的问题：提供一种能够通过使膜空气沿着燃气轮机组合构件的壁面流动而能够改善冷却性能的燃气轮机冷却结构，而不会在冷却孔的出口处剥离膜空气，即使当冷却孔的伸长率增加。解决方案：燃气轮机冷却结构包括用于使膜空气沿着燃气轮机组合构件的壁部上的构成构件的壁面流动的冷却孔1，其中，具有平滑弯曲的凹部表面至少形成在主燃烧气体流动方向上的冷却孔1的上游侧的壁面11a上。版权所有（C）2013，JPO＆INPIT

4. 发明专利

JP2011241836A Platform cooling structure of gas turbine moving blade 审中-公开
标题翻译：气体涡轮叶片平台冷却结构
公开(公告)号：JP2011241836A
公开(公告)日：2011-12-01
申请号：JP2011169064
申请日：2011-08-02
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： TORII SHUNSUKE , KUWABARA MASAMITSU , ITO EISAKU
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F05D2240/81
摘要： PROBLEM TO BE SOLVED: To provide a platform cooling structure of a gas turbine moving blade in which high pressure cooling air flowing in a moving blade cooling passage is introduced to an exhaust opening provided on a platform surface near a side edge of the platform without attaching an additional object such as a cover plate, thereby effectively cooling a part near the side edge, particularly, an upper surface of the side edge of the platform susceptible to thermal stress due to high temperature combustion gas, which is away from the moving blade cooling passage, so that cooling performance of the platform is improved and the reliability as the moving blade is improved.SOLUTION: The moving blade cooling passage 17c which is formed inside the gas turbine moving blade and through which cooling air circulates, and cooling communication holes 24a, 24b having one end communicated with the moving blade cooling passage 17c and another end communicated with the plurality of exhaust openings 22 provided on the platform surface near the side edge of the platform 5 are formed passing through the inside of the platform.
摘要翻译：要解决的问题：提供一种燃气轮机动叶片的平台冷却结构，其中在动叶片冷却通道中流动的高压冷却空气被引入设置在靠近侧面的平台表面上的排气口平台，而不附加诸如盖板的附加物体，从而有效地冷却侧边缘附近的部分，特别是易受高温燃烧气体引起的热应力的平台的侧边缘的上表面，该高温燃烧气体远离移动叶片冷却通道，从而提高了平台的冷却性能，提高了动叶片的可靠性。解决方案：形成在燃气轮机动叶片内并通过冷却空气循环的动叶片冷却通道17c，一端与动叶片冷却通道17c连通的冷却连通孔24a，24b与另一端连通设置在靠近平台5的侧边缘的平台表面上的多个排气口22穿过平台的内部。版权所有（C）2012，JPO＆INPIT

5. 发明专利

JP2011213520A Method for manufacturing powder for thermal spray, turbine member, and gas turbine 有权
标题翻译：用于制造热喷涂粉末，涡轮部件和气体涡轮的方法
公开(公告)号：JP2011213520A
公开(公告)日：2011-10-27
申请号：JP2010081961
申请日：2010-03-31
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NANBA KATSUMI , TORIGOE TAIJI , NAGANO ICHIRO , KANEKO HIDEAKI , MATSUI TAKUYA , SHIDA MASAHITO , OKADA IKUO , MORI KAZUTAKA , TSURU YASUHIKO , ITO EISAKU , OKAJIMA YOSHIFUMI
IPC分类号： C04B35/628 , C23C4/00
摘要： PROBLEM TO BE SOLVED: To provide a method for manufacturing a powder for thermal spray capable of efficiently manufacturing a powder of an optional particle size in relatively easy operation.SOLUTION: A slurry 13 formed by mixing a raw material of the powder for thermal spray, water and a dispersing agent is adjusted to have a solid concentration of 60 wt.% or higher and 86 wt.% or lower. The slurry 13 is then supplied to a disk-type atomizer 12 of a spray dryer 10, of which the rotation speed is adjusted so that the discharging velocity of the slurry 13 from the atomizer 12 is 30 m/s or higher and 110 m/s or lower. The slurry 13 is dried in the spray dryer 10 to form a powder body 22 for thermal spray, which is subjected to heat treatment to obtain the powder for thermal spray having an optional particle size distribution.
摘要翻译：要解决的问题：提供一种制造用于热喷涂的粉末的方法，其能够在相对容易的操作中有效地制造任选粒径的粉末。溶液：通过将用于热喷涂的粉末的原料混合而形成的浆料13，将水和分散剂调节至固体成分浓度为60重量％以上且86重量％以下。然后将浆料13供给到喷雾干燥器10的盘式雾化器12，其中调节转速使得来自雾化器12的浆料13的排出速度为30m / s以上且110m / s或更低。将浆料13在喷雾干燥器10中干燥，形成用于热喷涂的粉末体22，进行热处理，得到具有任意粒度分布的热喷涂用粉末。

6. 发明专利

JP2011032985A Rotor blade seal structure and turbine using the same 审中-公开
标题翻译：转子叶片密封结构和使用它的涡轮机
公开(公告)号：JP2011032985A
公开(公告)日：2011-02-17
申请号：JP2009182360
申请日：2009-08-05
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： YAMAMOTO HIROYUKI , ITO EISAKU
IPC分类号： F01D11/00 , F01D5/14 , F01D25/00 , F02C7/28
摘要： PROBLEM TO BE SOLVED: To provide a rotor blade seal structure and a turbine using the same capable of efficiently preventing cooling air on an inner circumferential side of an arm section from leaking into a high temperature gas passage when the turbine is operated, and maintaining a sealing property between arms over a long period of time. SOLUTION: The rotor blade seal structure is used in a turbine in which a plurality of rotor blades 11, 12 are disposed on a circumferential surface of a shaft body rotating about an axis line, adjacently to each other in a circumferential direction. In the turbine, arms 21A, 22A are formed extending from platforms 21, 22 of the rotor blades 11, 12. On the one arm 21A which is disposed adjacent to the other arm 22A in the circumferential direction, a groove 23 is formed facing the other arm. The groove 23 extends in a direction of the axis line and has a tapered portion at an outer circumferential side thereof. A seal pin 25 is disposed at the groove. In a portion of the other arm 22A facing the one arm 21A, and the seal pin 25 is movable in a radial direction of the shaft body. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：为了提供一种转子叶片密封结构和使用该涡轮机的涡轮机，能够有效地防止在涡轮机操作时臂部的内周侧的冷却空气泄漏到高温气体通道中，并且在长时间内保持臂之间的密封性。解决方案：转子叶片密封结构用于涡轮机，其中多个转子叶片11,12设置在围绕轴线旋转的轴体的圆周表面上，在圆周方向上彼此相邻。在涡轮机中，臂21A，22A形成为从转子叶片11,12的平台21,22延伸。在沿着圆周方向与另一个臂22A相邻设置的一个臂21A上形成有面向其他手臂槽23沿着轴线的方向延伸，在其外周侧具有锥形部。密封销25设置在凹槽处。在另一个臂22A的面向一个臂21A的部分中，并且密封销25可沿轴体的径向移动。版权所有（C）2011，JPO＆INPIT

7. 发明专利

JP2011017290A Blade body and rotary machine 有权
标题翻译：叶片机和旋转机
公开(公告)号：JP2011017290A
公开(公告)日：2011-01-27
申请号：JP2009162701
申请日：2009-07-09
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： SAKAMOTO YASUAKI , ITO EISAKU , KITAGAWA HITOSHI , WAKAZONO SUSUMU
IPC分类号： F01D5/14 , F04D29/38
摘要： PROBLEM TO BE SOLVED: To provide a blade body and a rotary machine, that can reduce flow losses resulted from wakes from a blade trailing edge which is generated by separation of the flow from the blade surface, and reduce a flow path resistance.SOLUTION: The blade body includes a body portion 4 having a dorsal surface 2 and a ventral surface 3, a trailing edge portion 6 connecting the dorsal surface 2 and the ventral surface 3 with a continuous curved surface 5. The curved surface 5 of the trailing edge portion 6 is reduced in a radius of curvature gradually toward a trailing end 7 which is located at the downstream end of a flow of fluid from either one of the dorsal surface 2 and the ventral surface 3 so that the radius of curvature is the smallest at the trailing end 7. The radius of curvature is gradually increased from the trailing end 7 toward the other blade side (the dorsal surface 2 or the ventral surface 3) and the curved surface 5 reaches the other of the dorsal surface 2 and the ventral surface 3.
摘要翻译：要解决的问题：提供一种叶片体和旋转机械，其可以减少由叶片后缘分离的叶片后缘产生的来自叶片表面的流动所产生的流动损失，并减少流动阻力。解决方案：叶片主体包括具有背面2和腹面3的主体部分4，后缘部分6，后缘部分6将背面2和腹面3连接成连续的曲面5.后缘部分的弯曲表面5 6的曲率半径逐渐朝向位于来自背面2和腹面3之一的流体流的下游端的后端7减小，使得曲率半径在后端7.曲率半径从尾端7朝向另一叶片侧（背面2或腹侧面3）逐渐增大，曲面5到达背面2a的另一侧和腹面3。

8. 发明专利

JP2010144656A Gas turbine blade and gas turbine 有权
标题翻译：气体涡轮叶片和气体涡轮机
公开(公告)号：JP2010144656A
公开(公告)日：2010-07-01
申请号：JP2008324353
申请日：2008-12-19
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： KITAMURA TAKESHI , ITO EISAKU , TORII SHUNSUKE
IPC分类号： F01D9/02
摘要： PROBLEM TO BE SOLVED: To reduce stress concentration resulting from thermal stress, and to improve a fatigue life.
SOLUTION: A gas turbine blade 8 is provided with: a blade body 53 having an outer surface along which combustion gas flowing from an upstream side to a downstream side in a gas turbine passes; and a shroud 60, 61 arranged on at least one of opposite sides in a height direction H of the blade body, supporting the blade body and forming a part of a partition wall of a combustion gas flow path F in which the combustion gas flows. The blade body and the shroud are respectively provided with blade body side connection parts 58, 59 and shroud side connection parts 66, 67, which extend in the height direction outside the combustion gas flow path, and the blade body side connection part and the shroud side connection part are connected in parts of their projection ends 70, 71 projecting outside the combustion gas flow path and are not connected at base ends 72, 73 situated on a combustion gas flow path side.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：减少由热应力引起的应力集中，并提高疲劳寿命。解决方案：燃气轮机叶片8设置有：具有外表面的叶片体53，燃烧涡轮机中的从上游侧流向下游侧的燃烧气体沿着该外表面通过; 以及设置在叶片主体的高度方向H上的相对侧中的至少一个上的护罩60,61，支撑刀片体并形成燃烧气体流动的燃烧气体流路F的分隔壁的一部分。叶片体和护罩分别设置有叶片体侧连接部58,59和护罩侧连接部66,67，其沿高度方向在燃烧气体流路的外侧延伸，并且叶片主体侧连接部和护罩侧连接部分连接在突出于燃烧气体流动路径外侧的突出端部70,71的部分中，并且不连接在位于燃烧气体流路侧的基端72,73处。版权所有（C）2010，JPO＆INPIT

9. 发明专利

JP2009174330A Turbine blade train end wall 有权
标题翻译：涡轮叶片火车端壁
公开(公告)号：JP2009174330A
公开(公告)日：2009-08-06
申请号：JP2008010921
申请日：2008-01-21
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： SAKAMOTO YASUAKI , ITO EISAKU , OTOMO HIROYUKI
IPC分类号： F01D9/02
CPC分类号： F01D9/041 , F01D5/143 , F01D11/08 , F05D2250/71
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade train end wall for restraining curling generated at a back face of a turbine stationary blade, and reducing secondary flow loss due to the curling.
SOLUTION: The turbine blade train end wall 10 that positions on a tip side of a plurality of the turbine stationary blades B arrayed in an annular includes a pressure gradient mediating means 11 mediating pressure gradient generated at the back face of the turbine stationary blades B in a blade height direction by clearance leakage flow leaking from a gap between a tip of turbine moving blades located on the upstream side of the turbine stationary blades B and the tip end wall arrayed facing the tip of the turbine moving blades.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于限制在涡轮静止叶片的背面产生的卷曲的涡轮机叶片系列端壁，并且减少由于卷曲引起的二次流动损失。解决方案：位于环形排列的多个涡轮机固定叶片B的顶端侧的涡轮叶片驱动端壁10包括压力梯度调节装置11，该压力梯度调节装置11调节在涡轮机静台面的后面产生的压力梯度叶片B处于叶片高度方向上，其间隙泄漏流从位于涡轮机固定叶片B的上游侧的涡轮动叶片的顶端与面对涡轮动叶片的顶端排列的顶端壁之间的间隙泄漏。版权所有（C）2009，JPO＆INPIT

10. 发明专利

JP2008202547A Platform cooling structure of gas turbine moving blade 有权
标题翻译：气体涡轮叶片平台冷却结构
公开(公告)号：JP2008202547A
公开(公告)日：2008-09-04
申请号：JP2007041489
申请日：2007-02-21
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
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： PROBLEM TO BE SOLVED: To provide platform cooling structure of a gas turbine moving blade, improving cooling property of a platform and also improving reliability as a moving blade, by leading high-pressure cooling air flowing in a moving blade cooling passage to blowoff openings formed to a platform surface near a side edge of the platform without attaching an additional object such as a cover plate, and by effectively cooling near the side edge of the platform, particularly an upper surface of the side edge, disposed away from a moving blade cooling passage and susceptible to thermal stress caused by high-temperature combustion gas. SOLUTION: The moving blade cooling passage 17c formed inside the gas turbine moving blade to pass cooling air therein is provided, and cooling communication holes 24a, 24b one ends of which communicates with the moving blade cooling passage 17c and the other ends of which communicates with a plurality of blowoff openings 22 formed to the platform surface near the side edge of the platform 5, are formed through the inside of the platform. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：为了提供燃气轮机动叶片的平台冷却结构，提高平台的冷却性能，并且通过将在动叶片冷却通道中流动的高压冷却风引导到吹扫开口形成在平台的侧边缘附近的平台表面，而不附加附加的物体，例如盖板，并且通过有效地冷却平台的侧边缘，特别是侧边缘的上表面，远离移动叶片冷却通道并易受高温燃烧气体引起的热应力。解决方案：设置形成在燃气轮机动叶片内部以使冷却空气通过的动叶片冷却通道17c，以及冷却连通孔24a，24b，其一端与动叶片冷却通道17c连通，另一端与平台5的侧缘附近形成在平台面上的多个吹出开口22连通。版权所有（C）2008，JPO＆INPIT

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