Heat Shield for a Fuel Nozzle of a Turbine Engine

A heat shield for a fuel nozzle of a turbine engine, the heat shield comprising:

• an aft wall extending at an aft end of the heat shield along a radial direction that extends perpendicular to a heat shield centerline axis defined by the heat shield;
• a forward wall extending along the radial direction and disposed between the aft wall and a cooling flow passage partially defined by the forward wall;
• an outer wall extending from the forward wall to the aft wall such that an annular outer rim is defined along an outer surface of the outer wall between the forward wall and the outer wall;
• an inner wall extending from the forward wall to the aft wall;
• and
• an internal cooling cavity defined and enclosed by the aft wall, the forward wall, the outer wall, and the inner wall, each of the aft wall, the forward wall, the outer wall, and the inner wall being annular such that the internal cooling cavity is annular,
• wherein a plurality of first exhaust apertures opens into the cooling flow passage and extends through the forward wall into the internal cooling cavity, a plurality of second exhaust apertures opens into the internal cooling cavity and extends through the aft wall, and a plurality of third exhaust apertures opens into the cooling flow passage and extends through the forward wall to the outer surface of the outer wall adjacent to the outer rim, and
• wherein, during operation of the turbine engine, the plurality of first exhaust apertures and the plurality of second exhaust apertures direct flow of air from the cooling flow passage and through the internal cooling cavity to cool the heat shield from heat of combustion.