Combustor and heat shield configurations for a gas turbine engine

A combustor of a gas turbine engine, the combustor comprising:

• a combustor structure including a combustor cavity;
• and
• one or more panels lining the combustor shell structure, wherein each panel is configured to include
• a panel structure having a surface configured to face the combustor cavity, the surface of the panel structure configured to receive cooling airflow,
• a dilution hole in the surface of the panel structure, the dilution hole to provide airflow for the combustor cavity;
• and
• one or more effusion holes downstream of the dilution hole, wherein the one or more effusion holes are configured to restore cooling airflow to the surface of the panel structure downstream from dilution hole.