| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide a mechanism capable of reducing an amount of CO generated through combustion of a gas turbine. <P>SOLUTION: A combustor (10) for the gas turbine includes a plurality of radially outer nozzles (26) arranged in an annular array, each of the radially outer nozzles having an outlet end located to supply fuel and/or air to a first combustion chamber (32). A center nozzle (28) has an outlet end located axially upstream of the outlet ends of the radially outer nozzles (26), and is configured and arranged to supply fuel and air to a second combustion chamber (36) axially upstream of the first combustion chamber (32). The second combustion chamber (36) opens into the first combustion chamber (32) and has a length sufficient to maintain a center nozzle flame confined to the second combustion chamber (36). <P>COPYRIGHT: (C)2011,JPO&INPIT</p> |
