Multifuel gas turbine combustor
To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner ( 12 ) for supplying to and combusting a premixed gas (M), containing a first fuel (F 1 ), within a first combustion region (S 1 ) of a combustion chamber ( 10 ), and a supplemental burner ( 20 ) for supplying to and combusting a second fuel (F 2 ) of a composition different from that of the first fuel (F 1 ) within a second combustion region (S 2 ) defined downstream of the first combustion region (S 1 ) within the combustion chamber ( 10 ). The first fuel (F 1 ) is of a hydrocarbon system and the second fuel (F 2 ) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.
1. A gas turbine combustor which comprises:
a main burner to supply a first premixed gas, containing a first fuel, to a first combustion region within a combustion chamber and then to combust the first premixed gas; and
a supplemental burner to supply a second premixed gas, containing a second fuel of a composition different from that of the first fuel, to a second combustion region at a location downstream of the first combustion region within the combustion chamber and then to combust the second premixed gas;
in which the first fuel is of a hydrocarbon system and the second fuel is a gas containing hydrogen in concentration exceeding a stable combustion limiting concentration of the hydrogen,
in which the supplemental burner is a premixing burner operable to premix both of the first fuel and the second fuel with an air so as to provide the second premixed gas and to supply the second premixed gas to the second combustion region,
in which the supplemental burner comprises a premixing chamber to which the air is introduced, a first nozzle to inject the first fuel into the premixing chamber, a second nozzle to inject the second fuel into the premixing chamber, a first fuel chamber to reserve the first fuel, and a second fuel chamber to reserve the second fuel, and
in which the first nozzle is in the form of a plurality of small perforations, which open in the first fuel chamber, and the second nozzle is in the form of a plurality of small perforations which open in the second fuel chamber.
2. The gas turbine combustor as claimed in claim 1 , further comprising:
a main fuel supply passage to supply the first fuel to the main burner;
a first fuel control valve provided in the main fuel supply passage; and
a first reheating fuel supply passage to supply the first fuel to the supplemental burner, the first reheating fuel supply passage being branched off from an upstream side of the first fuel control valve in the main fuel supply passage.
3. The gas turbine combustor as claimed in claim 1 , further comprising:
a pilot burner to inject the first fuel into the first combustion region and then to accomplish a diffusion combustion thereof;
a pilot fuel supply passage to supply the first fuel to the pilot burner; and
a pilot sub passage to supply the second fuel into the pilot fuel supply passage during activation of the main burner.
4. The gas turbine combustor as claimed in claim 1 , wherein:
the supplemental burner includes a fuel introducing block and a collared mixture injecting barrel interconnected by a plurality of guide pieces, the fuel introducing block being provided with the first fuel chamber and the second fuel chamber;
an air inflow opening is formed between a collar of the mixture injecting barrel and a bottom wall of the fuel introducing block, the air inflow opening being provided with the guide pieces; and
the premixing chamber is defined by an inner peripheral surface of the mixture injecting barrel and an outer surface of the bottom wall, and the air inflow opening is communicated with the premixing chamber.