Shroud integral type moving blade and split ring of gas turbine
    1.
    发明授权
    Shroud integral type moving blade and split ring of gas turbine 有权
    护罩一体式动力叶片和燃气轮机的开环

    公开(公告)号:US06736596B2

    公开(公告)日:2004-05-18

    申请号:US10167608

    申请日:2002-06-13

    IPC分类号: F01D1102

    摘要: A gas turbine comprises a shroud integral type moving blade and a split ring. The moving blade includes a shroud provided from a leading edge of a tip of a moving blade to a trailing edge and whose outer side surface is provided with a seal fin. A radius of a tip end of the seal fin is substantially equal to a radius of a shroud trailing edge end. The split ring has a structure in which a radius of its inner peripheral surface is slightly larger than a radius of the seal fin tip end and the radius of the shroud trailing edge end.

    摘要翻译: 燃气轮机包括护罩一体式动作叶片和分裂环。 活动叶片包括从活动叶片的尖端的前缘到后缘提供的护罩,并且其外侧表面设置有密封翅片。 密封翅片的尖端的半径基本上等于护罩后缘端部的半径。 开口环具有其内周面的半径略大于密封翅片前端的半径和护罩后缘的半径的结构。

    Gas turbine combustor
    2.
    发明授权
    Gas turbine combustor 失效
    燃气轮机燃烧器

    公开(公告)号:US06732528B2

    公开(公告)日:2004-05-11

    申请号:US10114053

    申请日:2002-04-03

    IPC分类号: F23R306

    CPC分类号: F23R3/002 F23R3/04 Y02T50/675

    摘要: An internal cylinder which has the opening section from which combustion gas is blown out is inserted into the tail cylinder which becomes a flow path of the combustion gas, and is engaged with the tail cylinder, while securing a clearance between the edge of the opening section and the internal wall surface of the tail cylinder. Air compressed with a compressor is jetted from the clearance along the internal wall surface of the tail cylinder, and a film of cooling air is formed on the internal wall surface of the tail cylinder.

    摘要翻译: 具有吹出燃烧气体的开口部的内筒被插入作为燃烧气体的流路的尾筒中,并且与尾筒接合,同时确保开口部的边缘之间的间隙 和尾缸的内壁表面。 利用压缩机压缩的空气沿着尾筒的内壁表面从间隙喷射,并且在尾筒的内壁表面上形成冷却空气膜。