COMBUSTOR AND HEAT SHIELD CONFIGURATIONS FOR A GAS TURBINE ENGINE
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United States of America Patent
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Issued Date -
Sep 8, 2016
app pub date -
Mar 5, 2015
filing date -
Mar 5, 2015
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Abstract
The present disclosure relates to combustor and heat shield configurations for gas turbine engines. A heat shield for a gas turbine engine can include one or more effusion holes downstream of a dilution hole to restore a cooling film applied to the heat shield in the combustor. Effusion holes may be clustered in one or more configurations and rows following each dilution hole and/or on a trailing edge of each heat shield panel structure. One or more embodiments are directed to effusion holes positioned along a trailing edge of a heat shield panel.
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