Gas turbine combustor

F - Mech Eng,Light,Heat,Weapons – 23 – R

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F23R 3/00 (2006.01) F23C 6/04 (2006.01) F23C 7/00 (2006.01) F23C 9/00 (2006.01) F23R 3/02 (2006.01) F23R 3/12 (2006.01)

Patent

CA 1179156

ABSTRACT A combustor capable of reducing the noxious emissions such as fuel bound and thermal nitrogen oxide products, during combustion of high nitrogen bearing and high aromatic content fuels is disclosed. The combustor includes a plurality of substantially concentric pipes defining annular passages with annular divergent nozzles. The divergent nozzles may be formed by rings having a venturi shaped axial section to facilitate fast mixing of axially supplied air between adjacent annular passages. The longitudinal spacing between at least two adjacent nozzles defines first and second divergent cavities. A fuel rich toroidal vortex is formed in proximity to a central fuel jet in the first cavity and advan- tageously converts fuel bound nitrogen to N2. A fuel lean toroidal vortex formed in the second cavity mixes hot combustion products with additional gaseous reactant to complete the combustion while avoiding locally high temperatures, and thus thermal NOx formation. A ring of jet nozzles radially injects relatively small amounts of high pressure gaseous reactant or steam to form a throat to separate and stabilize the vortices. Alternatively, the pipe extending between the two cavities can include a convergent and divergent portion forming the throat between the cavities for separating and reinforcing the toroidal vortices. Guide vanes may be positioned in the annular passages to swirl the gaseous reactant entering the cavities to assist in the formation of the toroidal vortices.

396692

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