Patent ID: 6931853
Filing Date: 2005-08-23
Classification: F23R

Abstract:
1. A combustor for a gas turbine engine, the combustor comprising: a plurality of main fuel supply pre-mix burners, each burner comprising a fuel injection region and a mixing region downstream of the fuel injection region; a single combustion chamber region disposed downstream of the plurality of burners for receiving and combusting fuel/air mixtures received from all of the burners with no flow restriction there between; a first main fuel stage in fluid communication with a first grouping of the burners, each burner of the first grouping comprising a mixing region having a first geometry; a second main fuel stage in fluid communication with a second grouping of the burners, each burner of the second grouping comprising a mixing region having a second geometry aerodynamically different than the first geometry; wherein the first main fuel stage and the second main fuel stage cooperate with the respective first geometry and second geometry to provide a supplemental degree of control over dynamic pressure response in the combustion chamber when a split of a fixed total fuel flow between the first and second stages is varied so that first combustion conditions exist in the combustion chamber with a first split of the total fuel flow between the first and second stages, and second combustion conditions different from the first combustion conditions exist in the combustion chamber with a second split of the total fuel flow between the first and second stapes.