General Electric Company
Liner of a gas turbine engine combustor including dilution holes with airflow features

Abstract:

A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.