Refractory metal core cooling technologies for curved...

Details Refractory metal core cooling technologies for curved... Refractory metal core cooling technologies for curved...

2007-12-04

2007-12-04

Edgar, Richard A. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

With fluid passage in working member communicating with...

Air and watercraft propellers

C416S09700R, C029S889721

Reexamination Certificate

active

11286942

ABSTRACT:
A turbine engine component has an airfoil portion with a leading edge portion. The leading edge portion includes a plurality of staggered holes for causing fluid to flow over a surface of the airfoil portion. A method for forming the leading edge portion using refractory metal core technology is described.

REFERENCES:
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patent: 5637239 (1997-06-01), Adamski et al.
patent: 2003/0143075 (2003-07-01), Fleck
patent: 0614917 (1995-03-01), None
patent: 1013877 (2000-06-01), None
patent: 1467064 (2004-10-01), None

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