发明名称 |
Film cooling of jet engine components |
摘要 |
A jet engine component, such as an aircraft gas turbine engine rotor blade or a scramjet engine fuel injector. The component has a wall portion including a first surface exposable to a cooler, higher static pressure fluid and a second surface exposable to a hotter, lower static pressure gas flow flowing across the second surface. The component further includes a generally straight film coolant passageway having an inlet on the first surface and an outlet on the second surface. The second surface has a seamless groove which is open substantially entirely along its longitudinal dimension extending from the outlet along the lower static pressure gas flow for improved film cooling of the second surface.
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申请公布号 |
US5653110(A) |
申请公布日期 |
1997.08.05 |
申请号 |
US19910733892 |
申请日期 |
1991.07.22 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
LEE, CHING-PANG;ABUAF, NESIM;WILSON, PAUL STUART |
分类号 |
F01D5/18;(IPC1-7):F02C1/00;B63H1/14 |
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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