Combustor with an air mixer and an air swirler each having slots
An air mixer includes an annular body defining a center axis. A plurality of slots are defined in the annular body circumferentially spaced apart from one another. Each slot defines a respective center injection axis extending from an outer surface of the annular body to an inner surface of the annular body. Each respective center injection axis is parallel to a respective plane bisecting the annular body. At least one of the slots is intersected by the respective bisecting plane parallel to its respective center injection axis.
1. A combustor system comprising:
a combustor case;
a combustor within the combustor case, a combustion chamber defined within the combustor;
a fuel manifold operatively connected to the combustor case;
an annular fuel distributor downstream from and fluidly, connected to the fuel manifold, wherein the annular fuel distributor is configured to provide fuel into the combustion chamber, wherein the annular fuel distributor defines a portion of the combustion chamber;
at least one air swirler upstream from the fuel distributor, wherein the at least one air swirler defines a portion of the combustion chamber, wherein the at least one air swirler is configured to impart swirl to air going from between the combustor case and the combustor into the combustion chamber, wherein the at least one air swirler includes:
a first annular body defining a first center axis; and
a first plurality of slots defined in the first annular body, the first plurality of slots circumferentially spaced apart from one another, wherein each slot of the first plurality of slots defines a respective center injection axis parallel to a respective plane bisecting the first annular body; and
an air mixer downstream from the annular fuel distributor and the at least one air swirler, wherein the air mixer defines a portion of the combustion chamber, wherein the air mixer is configured to impart swirl to air going from between the combustor case and the combustor into the combustion chamber wherein the air mixer includes:
a second annular body defining a second center axis; and
a second plurality of slots defined in the second annular body, the second plurality of slots circumferentially spaced apart from one another, wherein each slot of the second plurality of slots defines a respective center injection axis extending between an outer surface of the second annular body and an inner surface of the second annular body, wherein each respective center injection axis is parallel to a respective plane bisecting the second annular body, wherein at least one slot of the second plurality of slots is intersected by the respective plane bisecting the second annular body,
wherein a first offset defines a distance between the respective plane corresponding with the at least one slot of the second plurality of slots and the respective center injection axis of the at least one slot of the second plurality of slots, wherein the first offset distance is measured perpendicular to the respective plane corresponding with the at least one slot of the second plurality of slots,
wherein the first offset is smaller than a second offset,
wherein the second offset defines a distance between the respective plane corresponding with a first slot of the first plurality of slots and the respective center injection axis of the first slot of the first plurality of slots, wherein the second offset distance is measured perpendicular to the respective plane corresponding with the first slot of the first plurality of slots.
2. The combustor system as recited in claim 1 , wherein a plane bisecting the second annular body is parallel to two of the center injection axes of the second plurality of slots.
3. The combustor system as recited in claim 1 , wherein each slot of the second plurality of slots defines a respective longitudinal axis.
4. The combustor system as recited in claim 1 , wherein each slot of the second plurality of slots defines a respective longitudinal axis, wherein at least One of the longitudinal axes is angled with respect to the second center axis.
5. The combustor system as recited in claim 1 , wherein at least one of the center injection axes of the second plurality of slots is at an oblique angle relative to the second center axis.
6. The combustor system as recited in claim 1 , wherein a distance between an upstream side of a given one of the plurality of second slots and the respective plane corresponding with the given one of the plurality of second slots in a direction perpendicular to the respective plane corresponding with the given one of the plurality of second slots is different from a distance between a downstream side of the given of the plurality of second slots and the respective plane corresponding with the given one of the plurality of second slots in a direction perpendicular to the respective plane corresponding with the given one of the plurality of second slots.