| 摘要 |
A gas turbine combustor arrangement comprises two combustion chambers 2, 4, separated by a necked down throat portion 3 with provision 5, 6, for fuel introduction into each of the chambers. Initially, fuel is introduced into the first chamber and ignited. Thereafter, fuel is introduced into the second chamber until the total fuel flow to the combustor is at the desired rate. Burning in the first chamber is then extinguished by shifting fuel flow to the second chamber and after burning termination, the fuel distribution is reversed until a low emission operation is realized. <IMAGE> |
