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1. 发明专利

JP2014058985A Blade body and gas turbine 有权
标题翻译：叶片身体和气体涡轮
公开(公告)号：JP2014058985A
公开(公告)日：2014-04-03
申请号：JP2014000570
申请日：2014-01-06
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HIYAMA TAKASHI , HIRATA NORIFUMI , TAKAMURA KEITA , SHODA JUNICHIRO , ITO EISAKU
IPC分类号： F01D5/18 , F01D5/14
摘要： PROBLEM TO BE SOLVED: To provide a blade body capable of effectively suppressing a bending stress due to a thermal deformation.SOLUTION: A blade body 6 has a blade type cross-section made by connecting a concave positive pressure surface 21 and a convex negative pressure surface 22 via a front edge and a back edge and by arranging a plurality of cooling pores 25a to 25k, which are extended in a blade height direction intersecting the blade type cross-section and serve as channels for a cooling fluid, from the front edge toward the back edge. Therein, the plurality of cooling pores 25a to 25k include a first standard cooling pore 25a formed in a position closest to the front edge and a second standard cooling pore 25k formed in a position closest to the rear edge in such a range that a necessary thickness can be secured, while other cooling pores 25b to 25j are formed between the first standard cooling pore 25a and the second standard cooling pore 25k so that the positive pressure surface 21 side is cooled more than the negative pressure surface 22 side, and all of the other cooling pores 25b to 25j are formed only on the positive pressure surface 21 side from a camber line P.
摘要翻译：要解决的问题：提供一种能够有效地抑制由于热变形引起的弯曲应力的刀体。解决方案：刀体6具有通过将凹正压面21和凸负压连接而形成的叶片型横截面表面22经由前边缘和后边缘并且通过布置多个冷却孔25a至25k，所述多个冷却孔25a至25k沿着与叶片型横截面相交的刀片高度方向延伸并用作冷却流体的通道，朝向后边缘。其中，多个冷却孔25a至25k包括形成在最靠近前边缘的位置的第一标准冷却孔25a和形成在最靠近后边缘的位置的第二标准冷却孔25k，可以固定，而在第一标准冷却孔25a和第二标准冷却孔25k之间形成其他冷却孔25b至25j，使得正压表面21侧比负压表面22侧冷却，并且全部其它冷却孔25b〜25j仅在正压面21侧形成为弯曲线P.

2. 发明专利

JP2011122495A Intermediate product of gas turbine blade, gas turbine blade, gas turbine, method of manufacturing intermediate product of gas turbine blade, and method of manufacturing gas turbine blade 有权
标题翻译：气体涡轮叶片的中间产品，气体涡轮叶片，气体涡轮机，制造气体涡轮叶片中间产品的方法和制造气体涡轮叶片的方法
公开(公告)号：JP2011122495A
公开(公告)日：2011-06-23
申请号：JP2009279830
申请日：2009-12-09
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HIRATA NORIFUMI , TAKAMURA KEITA , ARASE KENICHI , KOYABU TOSHIMICHI , HANEDA SATORU , SHODA JUNICHIRO , TSUKAGOSHI KEIZO
IPC分类号： F02C7/00 , F01D5/14
摘要： PROBLEM TO BE SOLVED: To provide an intermediate product of a gas turbine blade allowing performance of both external working and internal working while securing desired accuracy, a method of manufacturing the intermediate product, the gas turbine blade, a method of manufacturing the gas turbine blade, and a gas turbine.
SOLUTION: The intermediate product 20 of the gas turbine blade includes: a first reference point group provided on the external face and constituted of a plurality of first reference points 21 for performing positioning when machining the shape of the external face; and a second reference point group provided on the external face and constituted of a plurality of second reference points 22 for performing positioning when machining holes, among which at least one place is provided at a position different from the first reference points 21.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种允许外部加工和内部工作同时确保期望精度的燃气轮机叶片的中间产品，制造中间产品的方法，燃气轮机叶片，制造方法燃气轮机叶片和燃气轮机。燃气轮机叶片的中间产品20包括：第一参考点组，设置在外表面上并且由多个第一参考点21构成，用于在加工外表面的形状时进行定位; 以及设置在外表面上并由多个第二参考点22构成的第二参考点组，用于在加工孔时进行定位，其中至少一个位置设置在与第一参考点21不同的位置。版权所有（C）2011，JPO＆INPIT

3. 发明专利

JP2011043115A Blade body and gas turbine 有权
标题翻译：叶片身体和气体涡轮
公开(公告)号：JP2011043115A
公开(公告)日：2011-03-03
申请号：JP2009192286
申请日：2009-08-21
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HIYAMA TAKASHI , HIRATA NORIFUMI , TAKAMURA KEITA , SHODA JUNICHIRO , ITO EISAKU
IPC分类号： F01D5/18
摘要： PROBLEM TO BE SOLVED: To provide a blade body effectively suppressing bending stress caused by thermal deformation. SOLUTION: This blade body 6 has an airfoil cross-sectional surface formed by continuously forming a recessed positive pressure surface 21 and a projecting negative pressure surface 22 through a leading edge 20a and a trailing edge 20b, and includes a plurality of cooling holes 25a-25k as flow passages for cooling fluid, which extend in a blade height direction intersecting with the airfoil cross-sectional surface and arranged from the leading edge 20a toward the trailing edge 20b. The cooling holes 25a-25k have the first reference cooling hole 25a formed closest to the leading edge 20a and the second reference cooling hole 25k formed closest to the trailing edge 20b within a range ensuring necessary thickness, and the other cooling holes 25b-25j are formed between the first reference cooling hole 25a and the second reference cooling hole 25k so that a temperature difference in a center area T3 positioned between a front area T1 and a rear area T2 is small with respect to the front area T1 including the first reference cooling hole 25a and the rear area T2 including the second reference cooling hole 25k. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种有效地抑制由热变形引起的弯曲应力的叶片体。解决方案：该叶片主体6具有通过前缘20a和后缘20b连续地形成凹入的正压面21和突出的负压面22而形成的翼型截面，并且包括多个冷却孔25a-25k作为用于冷却流体的流动通道，其沿着与翼型截面表面相交的叶片高度方向延伸并且从前缘20a朝向后缘20b布置。冷却孔25a-25k在确保所需厚度的范围内具有最靠近前缘20a形成的第一基准冷却孔25a和最靠近后缘20b形成的第二基准冷却孔25k，另一个冷却孔25b-25j是形成在第一参考冷却孔25a和第二基准冷却孔25k之间，使得位于前区域T1和后区域T2之间的中心区域T3的温度差相对于包括第一参考冷却并且包括第二基准冷却孔25k的后部区域T2。版权所有（C）2011，JPO＆INPIT

4. 发明专利

JP2010285878A Gas turbine blade and gas turbine 审中-公开
标题翻译：气体涡轮叶片和气体涡轮机
公开(公告)号：JP2010285878A
公开(公告)日：2010-12-24
申请号：JP2009138127
申请日：2009-06-09
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HIYAMA TAKASHI , HIRATA NORIFUMI , SHODA JUNICHIRO , ITO EISAKU
IPC分类号： F02C7/18 , F01D5/16 , F01D5/20 , F01D5/22 , F01D25/12
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine blade capable of effectively cooling the whole shroud and simultaneously realizing the weight reduction of the shroud.
SOLUTION: A gas turbine blade is equipped with: a blade body inside which cooling air flows; and a shroud 5 which is arranged in the end of the blade body and overhanged around a blade back 2A and blade belly face 2B of the blade, and is provided with a plurality of first cooling holes 3A and second cooling holes 3B extended from the blade body and flowing cooling air, to be inserted therethrough. A wall thickness of the shroud 5 is formed so as to be gradually reduced toward an edge end from the blade body side. When a face in a blade height direction in the shroud 5 is taken as the top face, the first cooling holes 3A are arranged so as to open to the top on the way toward an edge end from the blade body side.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种能够有效地冷却整个护罩的燃气轮机叶片，同时实现护罩的重量减轻。解决方案：燃气轮机叶片装备有：冷却空气流过的叶片体; 以及护罩5，其布置在叶片本体的端部并且围绕叶片的叶片背面2A和叶片腹面2B悬伸，并且设置有从叶片延伸的多个第一冷却孔3A和第二冷却孔3B 身体和流动的冷却空气，以插入其中。护罩5的壁厚形成为从刀体侧朝向边缘端部逐渐减小。当将护罩5中的叶片高度方向上的面作为上表面时，第一冷却孔3A布置成朝向从叶片体侧的边缘端的方向向顶部开口。版权所有（C）2011，JPO＆INPIT

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