Combustor liner panel with micro-circuit core cooling

A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area, wherein the combustor comprises:

• a shell having an inner surface and an outer surface opposite the inner surface;
• a heat shield panel having a first surface and a second surface opposite the first surface of the heat shield panel, the inner surface of the shell and the second surface of the heat shield panel being in a facing spaced relationship defining a cavity therebetween;
• and
• a cooling circuit formed in the heat shield panel, the cooling circuit comprising an inlet at the second surface of the heat shield panel, an outlet at the first surface of the heat shield panel, an inward surface, and an outward surface, the inward surface and the outward surface being in a facing spaced relationship extending from the inlet to the outlet defining an airflow passageway therebetween,
• wherein the airflow passageway includes a parallel portion that is oriented about parallel to at least one of the first surface of the heat shield panel and the second surface of the heat shield panel.

A heat shield panel for use in a gas turbine engine, the heat shield panel comprising:

• a first surface;
• a second surface opposite the first surface of the heat shield panel;
• and
• a cooling circuit formed in the heat shield panel, the cooling circuit comprising an inlet at the second surface of the heat shield panel, an outlet at the first surface of the heat shield panel, an inward surface, and an outward surface, the inward surface and the outward surface being in a facing spaced relationship extending from the inlet to the outlet defining an airflow passageway therebetween,
• wherein the airflow passageway includes a parallel portion that is oriented about parallel to at least one of the first surface of the heat shield panel and the second surface of the heat shield panel.