Turbine engine combustor with a dilution passage

A combustor for a turbine engine comprising:

• a dome wall;
• a combustor liner extending from the dome wall;
• a combustion chamber at least partially defined by the dome wall and the combustor liner;
• a set of fuel cups circumferentially spaced along the dome wall relative to a combustor centerline, with each fuel cup having a fuel cup centerline, and wherein each fuel cup of the set of fuel cups includes a swirler;
• and
• a set of dilution passages extending through the dome wall or the combustor liner to direct air into the combustion chamber, wherein at least one dilution passage of the set of dilution passages comprises:
• a radiused inlet fluidly coupled to a compressed air source, wherein the radiused inlet is defined by a spherical inlet;
• an outlet downstream of the radiused inlet and fluidly coupled to the combustion chamber;
• and
• a passageway fluidly coupling the radiused inlet to the outlet;
• wherein a first part of a compressed air is fed to the fuel cup as a swirled airflow via the swirler, and a second part of the compressed air is fed to the set of dilution passages which provides a dilution airflow to the combustion chamber to direct and shape a flame.

A combustor for a turbine engine comprising:

• a dome wall;
• a combustor liner extending from the dome wall;
• a combustion chamber at least partially defined by the dome wall and the combustor liner;
• a set of fuel cups circumferentially spaced along the dome wall relative to a combustor centerline, with each fuel cup having a fuel cup centerline;
• and
• a set of dilution passages extending through the dome wall or the combustor liner to direct air into the combustion chamber, wherein at least one dilution passage of the set of dilution passages comprises:
• a radiused inlet fluidly coupled to a compressed air source;
• an outlet downstream of the radiused inlet and fluidly coupled to the combustion chamber;
• a passageway fluidly coupling the radiused inlet to the outlet;
• and
• a channel having a radiused sidewall forming the radiused inlet, wherein the channel is a curved groove recessed into the dome wall, wherein the radiused sidewall is defined by a portion of the dome wall;
• wherein at least a portion of a compressed air flow from the compressed air source is provided to the set of dilution passages which defines a dilution airflow to the combustion chamber to direct and shape a flame.

A combustor for a turbine engine comprising:

• a dome wall;
• a combustor liner extending from the dome wall;
• a combustion chamber at least partially defined by the dome wall and the combustor liner;
• a set of fuel cups circumferentially spaced along the dome wall relative to a combustor centerline, with each fuel cup having a fuel cup centerline;
• and
• a set of dilution passages extending through the dome wall or the combustor liner to direct air into the combustion chamber, wherein at least one dilution passage of the set of dilution passages comprises:
• a radiused inlet fluidly coupled to a compressed air source, wherein the radiused inlet has a radiused inlet diameter at least twice a radius of curvature of the radiused inlet or a radiused sidewall;
• an outlet downstream of the radiused inlet and fluidly coupled to the combustion chamber;
• and
• a passageway fluidly coupling the radiused inlet to the outlet;
• wherein at least a portion of a compressed air flow from the compressed air source is provided to the set of dilution passages which defines a dilution airflow to the combustion chamber to direct and shape a flame.