发明名称 |
Gas turbine engine components with blade tip cooling |
摘要 |
A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit. |
申请公布号 |
EP2713011(A1) |
申请公布日期 |
2014.04.02 |
申请号 |
EP20130184439 |
申请日期 |
2013.09.13 |
申请人 |
HONEYWELL INTERNATIONAL INC. |
发明人 |
CRITES, DANIEL CREGG;HALFMANN, STEVE;MORRIS, MARK C.;RIAHI, ARDESHIR |
分类号 |
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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