COMBUSTOR AND HEAT SHIELD CONFIGURATIONS FOR A GAS TURBINE ENGINE

摘要

The present disclosure relates to combustor (105; 400) and heat shield (200) configurations for gas turbine engines (100). A heat shield for a gas turbine engine can include one or more effusion holes (226; 227; 235; 245; 330; 335; 340; 420) downstream of a dilution hole (220; 230; 255; 311; 316; 405) 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 (211; 213) 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.