COMPONENT CORE WITH SHAPED EDGES

Number of patents in Portfolio can not be more than 2000

United States of America

APP PUB NO 20200024963A1
SERIAL NO

16199825

Stats

ATTORNEY / AGENT: (SPONSORED)

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Abstract

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A gas turbine engine according to an example of the present disclosure includes, among other things, a plurality of blade outer air seals and a plurality of airfoils, at least one of seals and airfoils including at least one cooling passage. The cooling passage includes a first wall and an opposed second wall bounding the cooling passage, a surface contour of the first wall having a plurality of first surface features and a surface contour of the second wall having a plurality of second surface features. The first surface features and the second surface features are arranged such that a width of the cooling passage varies along a length of the cooling passage defined by the first surface features and the second surface features. The first surface features have a first profile, and the second surface features have a second, different profile. A casting core for forming cooling passages in an aircraft component is also disclosed.

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  • Owner owned or assignment not recorded

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Devore, Matthew A Cromwell, US 70 431
Gleiner, Matthew S Norwalk, US 30 264
Jenne, Douglas C Ashford, US 8 121

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