Turbomachine turbine blade comprising a cooling circuit with improved homogeneity
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United States of America Patent
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Jan 16, 2018
Grant Date -
Feb 9, 2017
app pub date -
Apr 23, 2015
filing date -
Apr 24, 2014
priority date (Note) -
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Abstract
The internal cooling of moving blades of turbines in aircraft turbomachines is limited in effectiveness because of inhomogeneities of this cooling on each of the pressure-side and suction-side walls. To address this problem, there is proposed a blade including a circuit for cooling the airfoil part thereof, in which circuit the cavities interconnected in series are such that the stream of air flows radially toward the outside along the pressure-side wall in pressure-side cavities, and radially toward the inside along the suction-side wall in a suction-side cavity that is separated from the pressure-side cavities by an internal wall of the airfoil part. In this way, the force of the Coriolis effect deflects the stream of air toward each of the pressure-side and suction-side walls thereby limiting the inhomogeneity.
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