Wavy annular dilution slots for lower emissions
A combustor liner for a combustor of a gas turbine includes an outer liner having a plurality of outer liner segments, and an inner liner having a plurality of inner liner segments. Each segment of the inner liner and the outer liner includes at least one slotted dilution opening therethrough extending in a circumferential direction, and each slotted dilution opening includes a deflector wall extending radially from the respective liner into a dilution zone of a combustion chamber between the outer liner and the inner liner. The at least one slotted dilution opening may be a curved slot (either concave or convex) dilution opening, and the curved slot dilution openings for each segment of the outer liner and the inner liner may be connected so as to provide a wavy slotted dilution opening extending annularly through the outer liner and the inner liner.
1 . A combustor liner for a combustor of a gas turbine, the combustor liner defining an axial direction along a combustor centerline, a radial direction extending from the combustor centerline, and a circumferential direction extending circumferentially about the combustor centerline, the combustor liner comprising:
a liner segment defining a flow direction extending in the axial direction from an upstream end of the liner segment to a downstream end of the liner segment, a dilution zone being defined between the upstream end of the liner segment and the downstream end of the liner segment, the liner segment having a cold surface side and a hot surface side and including a curved slot dilution opening arranged in the dilution zone and having, with respect to the flow direction, a concave curved slot dilution opening portion and a convex curved slot dilution opening portion arranged adjacent to one another in the circumferential direction, and including a liner deflector wall adjacent to a downstream side of the curved slot dilution opening and extending radially inward from the hot surface side of the liner segment,
wherein the liner deflector wall includes a convex deflector wall portion arranged at a downstream side of the convex curved slot dilution opening portion, and a concave deflector wall portion arranged at a downstream side of the concave curved slot dilution opening portion.
2 . The combustor liner according to claim 1 , wherein the liner segment further defines a liner segment centerline extending from the upstream end of the liner segment to the downstream end of the liner segment, and the concave curved slot dilution opening portion is arranged on a first circumferential side of the liner segment centerline and the convex curved slot dilution opening portion is arranged on a second circumferential side of the liner segment centerline.
3 . The combustor liner according to claim 2 , wherein the liner segment further defines a first liner segment boundary on a first circumferential side of the liner segment, and a second liner segment boundary on a second circumferential side of the liner segment.
4 . The combustor liner according to claim 3 , wherein a first end of the convex curved slot dilution opening portion is arranged adjacent to the first liner segment boundary and a second end of the convex curved slot dilution opening portion is arranged adjacent to the liner segment centerline, and a first end of the concave curved slot dilution opening portion is arranged adjacent to the liner segment centerline and a second end of the concave curved slot dilution opening portion is arranged adjacent to the second liner segment boundary.
5 . The combustor liner according to claim 4 , wherein the liner deflector wall extends continuously along from the first end of the convex curved slot dilution opening portion to the second end of the concave curved slot dilution opening portion.
6 . The combustor liner according to claim 1 , wherein the combustor liner includes a plurality of liner segments connected together annularly about the combustor centerline to define an annular combustor liner.
7 . The combustor liner according to claim 6 , wherein the combustor liner includes a first annular combustor liner defining an outer combustor liner, and a second annular combustor liner defining an inner combustor liner, the outer combustor liner being arranged radially outward of the inner combustor liner with respect to the combustor centerline.
8 . A combustor for a gas turbine engine, the combustor defining a combustor centerline axis, an axial direction extending along the combustor centerline axis, a radial direction extending from the combustor centerline axis, and a circumferential direction extending circumferentially about the combustor centerline axis, the combustor comprising:
an outer liner;
an outer casing arranged radially outward of the outer liner, an outer flow passage being defined between the outer liner and the outer casing;
an inner liner;
an inner casing arranged radially inward of the inner liner, an inner flow passage being defined between the inner liner and the inner casing;
a dome structure connecting the outer liner and the inner liner, a combustion chamber being defined between the outer liner, the inner liner, and the dome structure; and
a plurality of swirler assemblies connected to the dome structure,
wherein at least one of the outer liner or the inner liner comprises a plurality of liner segments connected together so as to extend annularly about the combustor centerline axis, at least one liner segment of the plurality of liner segments defining a flow direction extending in the axial direction from an upstream end of the at least one liner segment to a downstream end of the at least one liner segment, a dilution zone being defined between the upstream end of the at least one liner segment and the downstream end of the at least one liner segment, the at least one liner segment having a cold surface side and a hot surface side adjacent to the combustion chamber, and including a curved slot dilution opening arranged in the dilution zone, the curved slot dilution opening having, with respect to the flow direction, a concave curved slot dilution opening portion and a convex curved slot dilution opening portion arranged adjacent to one another in the circumferential direction, and including a liner deflector wall adjacent to a downstream side of the curved slot dilution opening and extending radially inward from the hot surface side of the at least one liner segment, and
wherein the liner deflector wall includes a convex deflector wall portion arranged at a downstream side of the convex curved slot dilution opening portion, and a concave deflector wall portion arranged at a downstream side of the concave curved slot dilution opening portion.
9 . The combustor according to claim 8 , wherein each liner segment of the plurality of liner segments further defines a liner segment centerline extending from the upstream end of the at least one liner segment to the downstream end of the at least one liner segment, and the concave curved slot dilution opening portion is arranged on a first circumferential side of the liner segment centerline and the convex curved slot dilution opening portion is arranged on a second circumferential side of the liner segment centerline.
10 . The combustor according to claim 9 , wherein the at least one liner segment further defines a first liner segment boundary on a first circumferential side of the at least one liner segment, and a second liner segment boundary on a second circumferential side of the at least one liner segment.
11 . The combustor according to claim 10 , wherein a first end of the convex curved slot dilution opening portion is arranged adjacent to the first liner segment boundary and a second end of the convex curved slot dilution opening portion is arranged adjacent to the liner segment centerline, and a first end of the concave curved slot dilution opening portion is arranged adjacent to the liner segment centerline and a second end of the concave curved slot dilution opening portion is arranged adjacent to the second liner segment boundary.
12 . The combustor according to claim 11 , wherein the liner deflector wall extends continuously along from the first end of the convex curved slot dilution opening portion to the second end of the concave curved slot dilution opening portion.
13 . The combustor according to claim 9 , wherein the liner segment centerline is circumferentially aligned with a center of one of the plurality of swirler assemblies.
14 . The combustor according to claim 9 , wherein the outer liner comprises the plurality of liner segments and includes the at least one liner segment.
15 . The combustor according to claim 14 , wherein each segment of the plurality of liner segments of the outer liner includes the at least one liner segment.
16 . The combustor according to claim 14 , wherein, in operation of the combustor, a flow of dilution air is provided through the curved slot dilution opening from the outer flow passage into the combustion chamber.
17 . The combustor according to claim 9 , wherein the inner liner comprises the plurality of liner segments and includes the at least one liner segment.
18 . The combustor according to claim 17 , wherein, in operation of the combustor, a flow of dilution air is provided through the curved slot dilution opening from the inner flow passage into the combustion chamber.