AIRFOIL OF GAS TURBINE ENGINE
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United States of America Patent
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Issued Date -
Jun 18, 2015
app pub date -
Dec 27, 2013
filing date -
Dec 17, 2013
priority date (Note) -
Abandoned
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Abstract
An airfoil of gas turbine engine is provided, which can improve cooling efficiency at a leading edge of the airfoil even when a location of combustion gas stagnation changes, without having to increase cooling air flowrate. The airfoil of gas turbine engine includes a cooling passage formed inside the airfoil to guide cooling air, and one or more cooling slots in elongated form, extending through the leading edge of the airfoil to a direction of the cooling passage and across a lengthwise direction of the leading edge.
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