Industrial turbine blade with platform cooling
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United States of America Patent
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Feb 4, 2014
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N/A
app pub date -
Jan 25, 2011
filing date -
Jan 25, 2011
priority date (Note) -
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Abstract
A turbine rotor blade with a platform hot spot cooling circuit that includes a bracket occupying a space below the platform on the pressure side of the blade neck and forming a cooling air supply hole connected to the blade cooling air supply channel and opening into an impingement cavity located below a hot spot location on the pressure side platform surface. A number of film cooling holes are connected to the impingement cavity and open onto the platform surface to cool the hot spot location.
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