A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel
A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injection slots (62,64,76,98) spaced apart transversely to the direction of flow through the fuel and air mixing ducts (54,70,92). The air injection slots (62,64,76,98) extend in the direction of flow through the fuel and air mixing ducts (54,70,92) to the reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).
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A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel
A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injection slots (62,64,76,98) spaced apart transversely to the direction of flow through the fuel and air mixing ducts (54,70,92). The air injection slots (62,64,76,98) extend in the direction of flow through the fuel and air mixing ducts (54,70,92) to the reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28). ounted therein. The inflow tube may have a bend at an end.
Toon, Ian J.; O'Dell, Stephen J.; Currin, John H.; Willis, Jeffrey D., Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection.
Rogers, Thomas J. C.; Twardochleb, Christopher Z.; Blust, James W.; Abreu, Mario E.; Cramb, Donald J., Acoustically tuned combustion for a gas turbine engine.
Rogers, Thomas J. C.; Twardochleb, Christopher Z.; Blust, James W.; Abreu, Mario E.; Cramb, Donald J., Acoustically tuned combustion for a gas turbine engine.
Modi, Roberto; Bonciani, Luciano; Ceccherini, Gianni, Combination of a premixing chamber and a combustion chamber, with low emission of pollutants, for gas turbines running on liquid and/or gas fuel.
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