INTERNAL COOLING SYSTEM WITH CORRUGATED INSERT FORMING NEARWALL COOLING CHANNELS FOR AIRFOIL USABLE IN A GAS TURBINE ENGINE
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United States of America Patent
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Issued Date -
Jul 16, 2015
app pub date -
Jan 15, 2014
filing date -
Jan 15, 2014
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Abstract
An airfoil for a gas turbine engine in which the airfoil includes an internal cooling system formed from one or more midchord cooling channels with a corrugated insert positioned therein and creating nearwall leading edge, pressure side and suction side nearwall cooling channels. The corrugated insert may be formed from a wall that oscillates in a repeating pattern between peaks and valleys, such that the peaks are closer to an inner surface of the outer wall forming the generally elongated hollow airfoil The corrugated insert may work in concert with the rows of partition walls to create periodic impingement on the inner surface of the outer wall Such cooling system provides adequate cooling for use in environments in which few, if any, cooling holes are desired, such as in crude oil engine applications
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