Gas turbine engine combustor with a set of dilution passages

A combustor for a gas turbine engine, the combustor defining a combustor centerline and comprising:

• a dome wall;
• an annular liner extending from the dome wall;
• a combustion chamber at least partially defined by the dome wall and the annular liner;
• at least one fuel cup having a fuel cup centerline;
• a set of dilution passages, with each dilution passage of the set of dilution passages having a passage centerline;
• a plurality of slots provided along the dome wall and being spaced about the at least one fuel cup, wherein:
• each slot of the plurality of slots defines a termination of at least one dilution passage of the set of dilution passages;
• each slot of the plurality of slots including a center point defined as a location where the passage centerline of the at least one dilution passage intersects the slot, each center points of the plurality of slots being located on a polar coordinate system having:
• a fuel cup reference line extending through the fuel cup centerline and defining a 0 degree to 180 degree reference line, with 0 degrees being radially closest to the combustor centerline;
• a transverse reference line defining a 90 degree to 270 degree reference line;
• and
• four quadrants split by the fuel cup reference line and the transverse reference line, the four quadrants including a first quadrant circumferentially adjacent to a second quadrant;
• a break defining a slot-free arc segment extending circumferentially about the at least one fuel cup that does not include the set of slots;
• and
• a slot-present arc segment extending circumferentially about the at least one fuel cup and defining an area of the dome wall that includes the set of slots, with the slot-present arc segment being provided circumferentially adjacent the break;
• wherein the plurality of slots include a subset of slots provided within at least the first quadrant and the second quadrant, the subset of slots including:
• a first slot defined as a slot within a first adjacent quadrant circumferentially farthest from the second quadrant, the first slot being provided a first radial distance from the fuel cup centerline, the first radial distance being a minimum radial distance of the plurality of slots;
• and
• a second slot defined as a slot within a second adjacent quadrant circumferentially farthest from the first quadrant, the second slot being provided a second radial distance from the fuel cup centerline, the second radial distance being a maximum radial distance of the plurality of slots.

A combustor for a gas turbine engine, the combustor defining a combustor centerline and comprising:

• a dome wall;
• an annular liner extending from the dome wall;
• a combustion chamber at least partially defined by the dome wall and the annular liner;
• at least one fuel cup having a fuel cup centerline;
• a set of dilution passages, with each dilution passage of the set of dilution passages having a passage centerline;
• a plurality of slots provided along the dome wall and being spaced about the at least one fuel cup, wherein:
• each slot of the plurality of slots defines a termination of at least one dilution passage of the set of dilution passages;
• each slot of the plurality of slots including a center point defined as a location where the passage centerline of the at least one dilution passage intersects the slot, each center points of the plurality of slots being located on a polar coordinate system having:
• a fuel cup reference line extending through the fuel cup centerline and defining a 0 degree to 180 degree reference line, with 0 degrees being radially closest to the combustor centerline;
• a transverse reference line defining a 90 degree to 270 degree reference line;
• and
• four quadrants split by the fuel cup reference line and the transverse reference line, the four quadrants including a first quadrant circumferentially adjacent to a second quadrant;
• a break defining a slot-free arc segment extending circumferentially about the fuel cup that does not include the set of slots, the slot-free arc segment extending a total distance that is less than or equal to a range of 75 degrees to −75 degrees from the transverse reference line;
• and
• a slot-present arc segment extending circumferentially about the at least one fuel cup and defining an area of the dome wall that includes the set of slots, with the slot-present arc segment being provided circumferentially adjacent the break;
• wherein the plurality of slots include a subset of slots provided within at least the first quadrant and the second quadrant, the subset of slots including:
• a first slot defined as a slot within a first adjacent quadrant circumferentially farthest from the second quadrant, the first slot having a first cross-sectional area along the dome wall;
• and
• a second slot defined as a slot within a second adjacent quadrant circumferentially farthest from the first quadrant, the second slot having second cross-sectional area along the dome wall;
• and
• wherein a remainder of the subset of slots interconnect the first slot and the second slot, with at least one slot of the remainder of the subset of slots having a third cross-sectional area non-equal to the first cross-sectional area and the second cross-sectional area.

A combustor for a gas turbine engine, the combustor defining a combustor centerline and comprising:

• a dome wall;
• an annular liner extending from the dome wall;
• a combustion chamber at least partially defined by the dome wall and the annular liner;
• at least one fuel cup having a fuel cup centerline;
• a set of dilution passages, with each dilution passage of the set of dilution passages having a passage centerline;
• a plurality of slots provided along the dome wall and being spaced about the at least one fuel cup, wherein:
• each slot of the plurality of slots defines a termination of at least one dilution passage of the set of dilution passages;
• each slot of the plurality of slots including a center point defined as a location where the passage centerline of the at least one dilution passage intersects the slot, each center points of the plurality of slots being located on a polar coordinate system having:
• a fuel cup reference line extending through the fuel cup centerline and defining a 0 degree to 180 degree reference line, with 0 degrees being radially closest to the combustor centerline;
• a transverse reference line defining a 90 degree to 270 degree reference line;
• a first quadrant extending between 0 degrees and 90 degrees;
• a second quadrant extending between 90 degrees and 180 degrees;
• a third quadrant extending between 180 degrees and 270 degrees;
• and
• a fourth quadrant extending between 270 degrees and 360 degrees;
• a break defining a slot-free arc segment extending circumferentially about the fuel cup that does not include the set of slots, the slot-free arc segment extending a total distance that is less than or equal to a range of 75 degrees to −75 degrees from the transverse reference line;
• and
• a slot-present arc segment extending circumferentially about the fuel cup and defining an area of the dome wall that includes the set of slots, with the slot-present arc segment being provided circumferentially adjacent the break;
• wherein a first subset of the plurality of slots follow a curved line, and a second subset of the slots follow a linear line extending from a circumferential end of the curved line.