Turbine blade for gas turbine engine and method of cooling same
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Jul 9, 2002
Grant Date -
N/A
app pub date -
Nov 3, 2000
filing date -
Nov 3, 2000
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A turbine blade includes a platform and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough to cool the airfoil. At least one supply passage is provided to direct some of the coolant that has passed at least partially through the internal cooling circuit onto the platform for cooling the platform.
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