发明名称 |
Air-cooled gas turbine blade |
摘要 |
A turbine blade for a gas turbine engine has internal passages which are opened at their roots to supply pressure so that there is a constant flow of cooling air inside the blade in use. The blade has an airfoil surface and a number of internal passages inside the walls of the blade, some being formed adjacent the mid-chord section and extend from the root section to the tip section to define feed channels open at the blade root section. A number of radially spaced film cooling holes in the airfoil surface communicate with each feed channel to flow a film of cooling air adjacent the airfoil surface. A number of replenishment holes are radially spaced in the wall to flow air from the mid-chord section to the feed channel(s) to replenish the cooling air in the feed channel(s) that is otherwise lost in supplying air to the film cooling holes. A device communicates cooling air from the root section via the feed channels to discharge from orifices in the airfoil surface at the tip section. |
申请公布号 |
SE470599(B) |
申请公布日期 |
1998.09.14 |
申请号 |
SE19900000112 |
申请日期 |
1990.01.12 |
申请人 |
UNITED TECHNOLOGIES CORP |
发明人 |
KENNETH B *HALL;ROBERT J *MCCLELLAND;THOMAS A *AUXIER |
分类号 |
F01D5/18;(IPC1-7):F01D5/18 |
主分类号 |
F01D5/18 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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