Turbine abradable layer with asymmetric ridges or grooves
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United States of America Patent
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Feb 2, 2016
Grant Date -
Aug 27, 2015
app pub date -
Feb 25, 2014
filing date -
Feb 25, 2014
priority date (Note) -
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Abstract
Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting asymmetric non-parallel walls or trapezoidal cross section ridges that reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. In some embodiments at least one angularly oriented first groove formed in the ridge plateau is adapted for angular orientation upstream a turbine blade rotation direction to resist blade tip airflow leakage and the ridges are separated by second grooves that are skewed relative to the respective ridge plateaus and the substrate that are also adapted for orientation upstream the turbine blade rotation direction to resist blade tip airflow leakage.
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