发明名称 |
Inlet film cooling of turbine end wall of a gas turbine engine |
摘要 |
The disclosure provides a gas turbine engine having a plurality of nozzle vanes extending between an inner shroud wall and an outer shroud wall of the engine. Each of the vanes includes a leading edge and at least one cooling protrusion extending upstream from a center of the leading edge. A cooling system is provided that is operable to inject cooling air upstream from the vanes. The disclosure also provides a method of cooling a gas turbine engine. The method includes the steps of supplying cooling air to an engine nozzle upstream of a gas directing vane, and adjusting the flow of the cooling air with a cooling protrusion extending forward from a leading edge center of the vane.
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申请公布号 |
US2006032233(A1) |
申请公布日期 |
2006.02.16 |
申请号 |
US20040915658 |
申请日期 |
2004.08.10 |
申请人 |
ZHANG LUZENG J;MOON HEE K |
发明人 |
ZHANG LUZENG J.;MOON HEE K. |
分类号 |
F02C6/08 |
主分类号 |
F02C6/08 |
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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