Gas turbine combustor including burner having plural gaseous fuel manifolds

1. A gas turbine combustor that mixes and combusts combustion air introduced from a compressor and gaseous fuel, and supplies produced combustion gas to a gas turbine,

the gas turbine combustor comprising:

an inner tube to produce combustion gas by combusting the combustion air and the gaseous fuel;

an outer tube enclosing the inner tube;

an end cover located upstream of the outer tube; and

a burner secured to the end cover and installed in the inner tube,

the burner including:

a plurality of gaseous fuel nozzles to inject gaseous fuel;

a first manifold to distribute gaseous fuel to the plurality of gaseous fuel nozzles;

a burner flange to secure the burner to the end cover; and

a burner body to connect the first manifold and the burner flange,

wherein gaseous fuel passages are provided to flow gaseous fuel through the end cover, the burner flange, and the burner body, the gaseous fuel passages including a first gaseous fuel passage provided in the burner body, a second fuel passage provided in the burner flange, and a third fuel passage provided in the end cover, an inlet of the first gaseous fuel passage communicating with an outlet of the second fuel passage, an inlet of the second fuel passage communicating with an outlet of the third fuel passage, an outlet of the first gaseous fuel passage communicating with the first manifold,

an annular second manifold is provided in the burner flange,

the annular second manifold having a single inlet for fuel inflow and a single outlet for fuel outflow,

the second fuel passage includes an inlet side second fuel passage and an outlet side second fuel passage, the inlet side second fuel passage providing fluid communication between the outlet of the third fuel passage and the single inlet for fuel inflow of the annular second manifold, the outlet side second fuel passage providing fluid communication between the single outlet for fuel outflow of the annular second manifold and the inlet of the first gaseous fuel passage, and

the single inlet for fuel inflow of the second manifold and the single outlet for fuel outflow of the second manifold are disposed at opposite circumferential positions within the burner.

2. The gas turbine combustor according to claim 1 ,

wherein a liquid fuel nozzle is located upstream of an axial center of the gas turbine combustor, secured to the burner via the end cover, and injects liquid fuel into the inner tube.

3. The gas turbine combustor according to claim 1 ,

wherein a sealing component is provided between the end cover and the burner flange to prevent fuel from leaking.

4. A gas turbine combustor that mixes and combusts combustion air introduced from a compressor and gaseous fuel, and supplies produced combustion gas to a gas turbine,

the gas turbine combustor comprising:

an inner tube to produce combustion gas by combusting the combustion air and the gaseous fuel;

an outer tube enclosing the inner tube;

an end cover located upstream of the outer tube; and

a burner secured to the end cover and installed in the inner tube,

the burner including:

a plurality of gaseous fuel nozzles to inject gaseous fuel;

a first manifold to distribute gaseous fuel to the plurality of gaseous fuel nozzles;

a burner flange to secure the burner to the end cover;

a burner body to connect the first manifold and the burner flange,

an annular second manifold provided in the burner flange, the annular second manifold having a single inlet for fuel inflow and a single outlet for fuel outflow, and

an annular third manifold provided in the end cover, the annular third manifold having a single inlet for fuel inflow and a single outlet for fuel outflow,

wherein gaseous fuel passages are provided to flow gaseous fuel through the end cover, the burner flange, and the burner body, the gaseous fuel passages including a first gaseous fuel passage provided in the burner body, a second fuel passage provided in the burner flange and a third fuel passage provided in the end cover, an inlet of the first gaseous fuel passage communicating with an outlet of the second fuel passage, an inlet of the second fuel passage communicating with an outlet of the third fuel passage, an outlet of the first gaseous fuel passage communicating with the first manifold,

the second fuel passage includes an inlet side second fuel passage and an outlet side second fuel passage,

the third fuel passage includes an inlet side third fuel passage and an outlet side third fuel passage,

the inlet side second fuel passage provides fluid communication between an outlet of the outlet side third fuel passage and the single inlet for fuel inflow of the annular second manifold,

the outlet side second fuel passage provides fluid communication between the single outlet for fuel outflow of the annular second manifold and the inlet of the first gaseous fuel passage,

an outlet of the inlet side third fuel passage communicates with the single inlet for fuel inflow of the annular third manifold,

the outlet side third fuel passage provides fluid communication between the single outlet for fuel outflow of the annular third manifold and an inlet of the inlet side second fuel passage, and

at least one of the second manifold and the third manifold is configured so that the single inlet for fuel inflow of the at least one of the second manifold and the third manifold and the single outlet for fuel outflow are disposed at opposite circumferential positions within the burner.

5. The gas turbine combustor according to claim 4 ,

wherein a sealing component is provided between the end cover and the burner flange to prevent fuel from leaking.

6. The gas turbine combustor according to claim 4 ,

wherein a liquid fuel nozzle is located upstream of an axial center of the gas turbine combustor, secured to the burner via the end cover, and injects liquid fuel into the inner tube.