发明名称 |
Turbine cooling vane of gas turbine engine |
摘要 |
A cooled blade of a small gas turbine engine can enhance cooling performance without increasing the amount of cooling air in a simple configuration. A cooled turbine blade is provided with a cooling passageway 12 formed inside thereof, making the cooling air flow therein. Film-cooling holes 13 penetrate from an inner wall surface 111 to an external wall surface 112 and form a cooling film. An impingement cooling member 2 has a multiple number of small holes 21 ejecting the cooling air. A gap t made by the inner wall surface 111 and the impingement cooling member 2 has a sealing portion 14 mounted thereon which divides the gap in a blade chord direction.
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申请公布号 |
US7300251(B2) |
申请公布日期 |
2007.11.27 |
申请号 |
US20050544844 |
申请日期 |
2005.08.08 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
KITAMURA TSUYOSHI;TAKEISHI KENICHIRO;MATSUURA MASAAKI;NOGAMI RYOMA |
分类号 |
F01D5/18;F01D9/02 |
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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