Combustor with staged, axially offset combustion
In some aspects, a gas turbine combustor assembly is arranged around a longitudinal axis. The gas turbine combustor comprises a first fuel/air mixer assembly, the mixer assembly comprising a first fuel injector and a plurality of first mixer elements, each mixer element defining an air flow passage therethrough having an outlet in a first plane. A second fuel/air mixer assembly comprises a second fuel injector and a plurality of second mixer elements, and each second mixer element defines an air flow passage therethrough having an outlet in a second plane, longitudinally offset from the first plane.
1. A gas turbine combustor dome assembly arranged around a longitudinal axis, the gas turbine combustor dome assembly comprising:
a first fuel/air mixer assembly, the first fuel/air mixer assembly comprising a fuel first injector and a plurality of first fuel/air mixer elements, each first mixer element defining an air flow passage therethrough having an outlet in a first plane; and
a second fuel/air mixer assembly, the second fuel/air mixer assembly comprising a second fuel injector and a plurality of second fuel/air mixer elements, each second mixer element defining an air flow passage therethrough having an outlet in a second plane, longitudinally offset from the first plane.
2. The gas turbine combustor of claim 1 , where the first fuel injector is changeable between supplying fuel and supplying no fuel, independent of whether the second fuel injector is supplying fuel.
3. The gas turbine combustor of claim 1 , comprising a plurality of first fuel/air mixer assemblies and a plurality of second fuel/air mixer assemblies nested in a ring with the first fuel/air mixer assemblies, the ring centered about the longitudinal axis.
4. The gas turbine combustor of claim 3 , where the first and second fuel/air mixer assemblies are arranged in alternating order around the ring.
5. The gas turbine combustor of claim 3 , where the second fuel/air mixer elements produce a flame in the longitudinal direction at operating conditions, and
where the second plane is longitudinally offset from the first plane a distance substantially equal to the length of the flame.
6. The gas turbine combustor of claim 5 , where the second fuel/air mixer elements are longitudinally recessed behind the first fuel/air mixer elements along the longitudinal axis.
7. The gas turbine combustor of claim 3 , where the plurality of first fuel/air mixer elements are arranged around a center location on the longitudinal axis and where the first fuel injector resides at the center location.
8. The gas turbine combustor of claim 7 , where a center of each first fuel/air mixer elements is equidistant from the center location.
9. The gas turbine combustor of claim 7 , where the plurality of first fuel/air mixer elements is symmetrically arranged around the center location.
10. The gas turbine combustor of claim 3 , where the first fuel/air mixers have a different number of first fuel/air mixer elements than the number of second fuel/air mixer element of the second fuel/air mixers.
11. The gas turbine combustor of claim 1 , where the air flow passage comprises a Venturi.
12. A device, comprising:
a plurality of gas turbine fuel/air mixer assemblies arranged in a ring centered about a longitudinal axis, each of the plurality of fuel/air mixer assemblies comprising a plurality of fuel/air mixer elements,
a subset of the fuel/air mixer assemblies being recessed along the longitudinal axis from the remainder of the fuel/air mixer assemblies.
13. The device of claim 12 , where the remainder of the fuel/air mixer assemblies comprise fuel injectors that are changeable between supplying fuel and supplying no fuel to the fuel/air mixer, independent of whether fuel injectors of the subset of fuel/air mixer assemblies are supplying fuel.
14. The device of claim 12 , where the subset of fuel/air mixer assemblies have a different number of fuel/air mixer elements than the remainder of the fuel/air mixer assemblies have.