PURPOSE: To contrive to stabilize combustion, by a method wherein a combustion chamber is comprised of two combustion chambers which are parallel to each other and are connected to each other at their tail parts, and one of the combustion chambers is provided with holes for diluting air, in a gas turbine combustor using a gaseous fuel having a low calorific power.
CONSTITUTION: Residual air left after removing the amount of cooling air for a combustion liner and the amount of diluted air 23 is supplied to the first combustion chamber 2 and the second combustion chamber 3 and is caused to flow in through a rotating device 6 and air holes 14, 15 of the combustion chamber 2, and a rotating device 11 and air holes 16, 19 of the combustion chamber 3. At the time of starting, a valve 21 is closed, and a fuel is fed only into the first combustion chamber 2 through a fuel line 4 and is burned in the chamber 2. Then, the fuel is supplied into the second combustion chamber 3 and is burned in the chamber 3. Accordingly, a fuel having a low calorific power can be burned stably.
TSUKAHARA SATOSHI
SUGITA NARIHISA
