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    • 8. 发明专利
    • Gas turbine blade
    • 气体涡轮叶片
    • JP2014169667A
    • 2014-09-18
    • JP2013042496
    • 2013-03-05
    • Hitachi Ltd株式会社日立製作所
    • YOKOYAMA TAKASHI
    • F01D5/18F01D5/20
    • F01D5/186F01D5/20
    • PROBLEM TO BE SOLVED: To provide a cooling structure which suppresses the generation of a temperature difference by uniformly cooling a tip, suppresses a rise of local stress accompanied by the processing of a cooling hole, and reduces the damage of the tip in operation.SOLUTION: In a gas turbine blade in which a cooling passage 16 is formed, and which has an isolation part 14 for isolating the cooling passage 16 from the outside at its tip, the isolation part 14 has, at the radial outside of the isolation part 14 and the inside of a tip wall 15 formed at an extension of a blade 7, a reinforcing part 19 which is integrally formed with the blade 7 in a position being the radial inside rather than the tip of the gas turbine, and connects the isolation part 14 and the tip wall 15. There are formed an external face cooling hole 17 which communicates with an external face 15a of the tip wall from the cooling passage 16, and an internal face cooling hole 18 which communicates with an internal face 15b of the tip wall through the isolation part 14 from the cooling passage 16.
    • 要解决的问题:为了提供通过均匀地冷却尖端来抑制温度差的产生的冷却结构,抑制伴随着冷却孔的处理的局部应力的上升,并且减少了操作中的尖端的损坏。 :在形成有冷却通路16的燃气轮机叶片中,隔离部14在隔离部14的径向外侧具有用于将冷却通路16与其外部隔离的隔离部14, 以及形成在叶片7的延伸部的前端壁15的内部,与刀片7一体形成在径向内侧而不是燃气轮机的前端的加强部19,并且将隔离部 形成有从冷却通路16与前端壁的外表面15a连通的外表面冷却孔17,以及与内部连通的内表面冷却孔18 l通过隔离部分14从冷却通道16面向尖端壁面15b。
    • 9. 发明专利
    • Gas turbine blade
    • 气体涡轮叶片
    • JP2013064366A
    • 2013-04-11
    • JP2011204050
    • 2011-09-20
    • Hitachi Ltd株式会社日立製作所
    • YOKOYAMA TAKASHI
    • F01D5/18F01D9/02F02C7/18
    • F01D5/186F05D2240/303
    • PROBLEM TO BE SOLVED: To provide a gas turbine blade for reducing stress and strain generated around a hole, by restraining stress concentration, in consideration that a film cooling structure having a plurality of through-holes becomes a stress concentration part and thereby there is a possibility of generating the large stress causing a crack.SOLUTION: A plurality of cooling holes 10 arranged in the blade height direction of the gas turbine blade leading edge portion 11 and penetrating a cooling flow passage formed inside a gas turbine blade, is characterized in that a radius of curvature of a hole part contacting with the major axis direction is larger than a radius of curvature of a hole part contacting with the minor axis direction, with the main strain direction of the turbine blade leading edge portion 11 as the major axis direction.
    • 要解决的问题:考虑到具有多个通孔的膜冷却结构成为应力集中部分,因此通过抑制应力集中来提供一种用于减小在孔附近产生的应力和应变的燃气轮机叶片 可能产生产生裂纹的大应力。 解决方案:沿燃气轮机叶片前缘部分11的叶片高度方向布置并穿过形成在燃气轮机叶片内的冷却流道的多个冷却孔10的特征在于,孔的曲率半径 与主轴方向接触的部分比涡轮叶片前缘部11的主应变方向为长轴方向大,与短轴方向接触的孔部的曲率半径大。 版权所有(C)2013,JPO&INPIT