发明名称 |
APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES |
摘要 |
A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends from a connection at the root to the approximate radial height of the platform, wherein, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein a pressure side of the platform comprises a topside extending circumferentially from the airfoil to a pressure side slashface. The platform cooling arrangement may include: a platform cavity formed within the pressure side of the platform, a high-pressure connector that connects the platform cavity to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the platform cavity to the low-pressure coolant region of the interior cooling passage; and a pin bank formed within the platform cavity that includes radial pins.
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申请公布号 |
US2012107134(A1) |
申请公布日期 |
2012.05.03 |
申请号 |
US20100915477 |
申请日期 |
2010.10.29 |
申请人 |
HARRIS, JR. JOHN WESLEY;BIELEK CRAIG ALLEN;ELLIS SCOTT EDMOND;FU XIAOYONG;GENERAL ELECTRIC COMPANY |
发明人 |
HARRIS, JR. JOHN WESLEY;BIELEK CRAIG ALLEN;ELLIS SCOTT EDMOND;FU XIAOYONG |
分类号 |
F01D5/18;B23P15/02 |
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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