Multiple wall impingement plate for sequential impingement cooling of a turbine hot part
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United States of America Patent
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Jun 20, 2017
Grant Date -
N/A
app pub date -
Dec 5, 2014
filing date -
Nov 18, 2013
priority date (Note) -
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Abstract
An air hot part of a gas turbine engine, the hot part having an isogrid formed on a cool surface opposite to a hot surface, where an impingement plate bonded over multiple impingement cooling surfaces of the airfoil, where the impingement plate forms a series of double or triple impingement cooling for separate surfaces of the airfoil. The impingement plate can be shaped and sized to fit over an airfoil surface that requires multiple impingement cooling.
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