Microcircuit cooling for gas turbine engine combustor

A combustor component of a gas turbine engine comprising:

• a heat shield panel defining a microcircuit flow path within a thickness of said heat shield panel and provided with an inlet and an outlet;
• and
• a flow swirler received in a dilution hole defined by said heat shield panel, said flow swirler downstream of and in communication with a microcircuit flow from said microcircuit flow path and with a diffusion flow from said dilution hole, wherein said diffusion flow is communicated from an annular passageway between a combustor case and said heat shield and wherein said flow swirler is configured to eject flow from said outlet in a tangential direction with respect to an axial flow path and to a combustion chamber defined by the heat shield panel.