Multi-stage axial combustion system
View Patent ↗A gas turbine combustion system is provided comprising a combustion chamber ( 16 ) having a central axis ( 44 ), a primary combustion stage ( 28 ) located at a front end ( 32 ) of the combustion chamber ( 16 ) for injecting fuel, air, or mixtures thereof substantially along the central axis ( 44 ), a plurality of secondary combustion stages ( 30 A-D) spaced apart in flow series along a length of the combustion chamber ( 16 ), wherein each of the plurality of secondary combustion stages ( 30 A-D) comprises a plurality of circumferentially-spaced secondary injectors ( 48 ) for injecting fuel, air, or mixtures thereof, toward the central axis ( 44 ), and wherein an internal diameter of the combustion chamber ( 16 ) decreases from at least a first one of the plurality of secondary combustion stages ( 30 AD) to at least a second one of the plurality of secondary combustion stages ( 30 A-D).
1. A gas turbine combustion system, comprising:
a combustion chamber having a central axis;
a pilot flame located within a primary combustion stage at a front end of the combustion chamber for combusting a first amount of injected fuel;
a plurality of secondary combustion stages spaced apart in flow series along a length of the combustion chamber, wherein each of the plurality of secondary combustion stages comprises a plurality of circumferentially-spaced secondary injectors for injecting a second amount of fuel, air, or mixtures thereof, toward the central axis;
wherein a minimum internal diameter of a first one of the plurality of secondary combustion stages is greater than a minimum internal diameter of at least a second downstream one of the plurality of secondary combustion stages.
2. The apparatus of claim 1 , wherein the plurality of secondary combustion stages form a substantially cone-shaped secondary combustion zone in the combustion chamber.
3. The apparatus of claim 1 , wherein the primary combustion stage comprises:
at least one fuel supply line and a first air supply line; and
a mixer for mixing fuel and air provided by the at least one fuel supply line and the first air supply line.
4. The apparatus of claim 1 , wherein each of the plurality of secondary injectors in at least one of the plurality of secondary stages is aligned to inject material at substantially the same angle toward the central axis.
5. The apparatus of claim 1 , wherein at least one of the plurality of secondary injectors of at least one of the plurality of secondary stages is aligned to inject material at an angle different from another one of the plurality of secondary injectors in that one secondary stage toward the central axis.
6. The apparatus of claim 1 , wherein each of the plurality of secondary combustion stages comprises:
at least one secondary fuel supply line and a secondary air supply; and
a second mixer for mixing fuel and air supplied by the at least one secondary fuel supply line and the secondary air supply, the mixer being disposed within each of the plurality of secondary injectors.
7. The gas turbine combustion system of claim 1 , wherein a velocity of the combusted air and fuel along the central axis of the combustion chamber increases from a first one of the plurality of secondary combustion stages to at least a second one of the plurality of secondary combustion stages.
8. A gas turbine combustion system, comprising:
(a) a combustion chamber having a central axis;
(b) a primary combustion stage located at a front end of the combustion chamber, wherein the primary combustion stage comprises:
at least one fuel supply line and an air supply line;
a mixer for mixing fuel and air supplied by the at least one fuel supply line and the air supply line and for providing a fuel-air mixture;
a substantially cone-shaped portion disposed downstream from the first mixing means; and
a pilot flame within the substantially cone-shaped portion for combusting the fuel-air mixture mixed along a central axis of the combustion chamber; and
(c) a plurality of secondary combustion stages spaced apart in flow series along a length of the combustion chamber, wherein each of the plurality of secondary combustion stages comprises plurality of secondary injectors spaced circumferentially around a perimeter of each of the plurality of secondary combustion stages, and wherein a minimum internal diameter of a first one of the plurality of secondary combustion stages is greater than a minimum internal diameter of to at least a second downstream one of the plurality of secondary combustion stages.
9. The apparatus of claim 8 , wherein the plurality of secondary combustion stages form a substantially cone-shaped second combustion zone of the combustion chamber.
10. The apparatus of claim 8 , wherein a velocity of the combusted air and fuel along the central axis of the combustion chamber increases from a first one of the plurality of secondary combustion stages to at least a second one of the plurality of secondary combustion stages.