Gas turbine having alloy castings with craze-free cooling passages
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United States of America Patent
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Mar 1, 2005
Grant Date -
N/A
app pub date -
Dec 30, 2002
filing date -
Dec 30, 2002
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
An airfoil for an internal combustion engine, such as a gas turbine, formed by use of a preform. The airfoil includes: an outer surface forming the foil shape; and a plurality of craze-free cooling passages extending through the airfoil. In the preferred embodiment, a root on the airfoil joins the airfoil to the hub of a gas turbine vane assembly. Also, in the preferred embodiment, the gas turbine vane assembly is adapted to receive replaceable airfoils.
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