Gas turbine engine component with upstream-directed cooling film holes

An apparatus for a gas turbine engine, the apparatus comprising:

• a combustion section comprising a heat shield;
• the heat shield comprising a surface with one or more upstream-directed cooling film holes therethrough;
• the combustion section further comprising a support shell and a cavity formed radially between the support shell and the heat shield;
• the support shell configured with a plurality of impingement apertures fluidly coupled with the cavity;
• the heat shield attached to the support shell;
• and
• the one or more upstream-directed cooing film holes fluidly coupled with the cavity.