Combustor of gas turbine
View Patent ↗A combustor 500 is composed of a plurality of premixed combustion burners 100 each comprising a fuel nozzle 110 provided in a burner tube 120 , the fuel nozzle 110 having a plurality of swirl vanes 130 on an outer peripheral surface thereof. Injection holes 133 a, 133 b are formed in each swirl vane 130 . Staging control is exercised such that when a gas turbine is in a full load state, a fuel is injected through the injection holes 133 a, 133 b of all the swirl vanes 130 , and when the gas turbine is under a partial load, the fuel is injected only through the injection holes 133 a, 133 b of a specific number of the swirl vanes 130 adjacent in a circumferential direction, and fuel injection through the injection holes 133 a, 133 b of the remaining swirl vanes 130 is stopped. By performing such staging control over fuel injection or its stoppage for the swirl vanes 130 , a fuel-air ratio can be increased locally, generation of CO and UHC can be suppressed, and high efficiency combustion can be achieved, even under the partial load.
1. A combustor of a gas turbine, the combustor having a combustion burner, comprising:
a fuel nozzle; and
swirl vanes which are arranged at a plurality of locations, along a circumferential direction, on an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, said swirl vanes are progressively curved from an upstream side toward a downstream side of a flow of air flowing along the axial direction of the fuel nozzle in order to swirl the air around the fuel nozzle,
wherein the combustor comprises:
injection holes, formed at a position on the upstream side of the flow of air on a vane ventral surface and a vane dorsal surface of each swirl vane, for injecting a fuel;
fuel passages for supplying the fuel individually to the injection holes formed in each swirl vane;
valves provided in the respective fuel passages; and
a control section for controlling the valves to open or close, and
the control section
brings all of the valves to an open state when the gas turbine is in a full load state, and
controls an opening of the valves, which are provided in the fuel passages for supplying the fuel to the injection holes formed in a specific number of the swirl vanes of the fuel nozzle arranged adjacently as a group in the circumferential direction, in accordance with a load, and closes valves of the remaining swirl vanes of the fuel nozzle, when the gas turbine is in a partial load state.
2. A combustor of a gas turbine, the combustor having a plurality of combustion burners each comprising:
a fuel nozzle; and
swirl vanes which are arranged at a plurality of locations, along a circumferential direction, on an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, said swirl vanes are progressively curved from an upstream side toward a downstream side of a flow of air flowing along the axial direction of the fuel nozzle in order to swirl the air around the fuel nozzle,
wherein the combustor comprises:
injection holes on an inner peripheral side and injection holes on an outer peripheral side, which are formed on an inner peripheral side and an outer peripheral side of each swirl vane at a position on the upstream side of the flow of air on a vane ventral surface and a vane dorsal surface of each swirl vane, for injecting a fuel;
fuel passages for supplying the fuel individually to the respective injection holes on the inner peripheral side and the respective injection holes on the outer peripheral side formed in each swirl vane;
valves provided in the respective fuel passages; and
a control section for controlling the valves to open or close, and
the control section exercises control over the plurality of the combustion burners in such a manner as to:
bring all of the valves to an open state when the gas turbine is in a full load state, and
control an opening of the valves, which are provided in the fuel passages for supplying the fuel to the injection holes on the inner peripheral side, in accordance with a load, and close the valves provided in the fuel passages for supplying the fuel to the injection holes on the outer peripheral side, when the gas turbine is in a partial load state.
3. A combustor of a gas turbine, the combustor having a plurality of combustion burners each comprising;
a fuel nozzle; and
swirl vanes which are arranged at a plurality of locations, along a circumferential direction, on an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, said swirl vanes are progressively curved from an upstream side toward a downstream side of a flow of air flowing along the axial direction of the fuel nozzle in order to swirl the air around the fuel nozzle,
wherein the combustor comprises:
injection holes formed in each swirl vane for injecting a fuel;
fuel passages for supplying the fuel individually to the injection holes formed in each swirl vane;
valves provided in the respective fuel passages; and
a control section for controlling the valves to open or close,
a plurality of the combustion burners being arranged side by side in a circumferential direction, and
the control section exercises control over the plurality of the combustion burners in such a manner as to
bring all of the valves to an open state when the gas turbine is in a full load state, and
control an opening of the valves, which are provided in the fuel passages for supplying the fuel to the injection holes formed in a specific number of the swirl vanes of the fuel nozzle arranged adjacently as a group in the circumferential direction, in accordance with a load, and close valves of the remaining swirl vanes of the fuel nozzle, when the gas turbine is in a partial load state.
controls an opening of the valves, which are provided in the fuel passages for supplying the fuel to the injection holes formed in a specific number of the swirl vanes of the fuel nozzle arranged adjacently as a group in the circumferential direction, in accordance with a load, and closes valves of the remaining swirl vanes of the fuel nozzle, when the gas turbine is in a partial load state.
4. The combustor of a gas turbine according to claim 3 , characterized in that
the swirl vanes arranged adjacently in the circumferential direction are arranged at portions where a swirl air flow wrapping up toward an inner peripheral side of the combustor flows.
5. A combustor of a gas turbine, the combustor having a plurality of combustion burners each comprising:
a fuel nozzle; and
swirl vanes which are arranged at a plurality of locations, along a circumferential direction, on an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, said swirl vanes are progressively curved from an upstream side toward a downstream side of a flow of air flowing along the axial direction of the fuel nozzle in order to swirl the air around the fuel nozzle,
wherein the combustor comprises:
injection holes on an inner peripheral side and injection holes on an outer peripheral side which are formed on an inner peripheral side and an outer peripheral side of each swirl vane for injecting a fuel;
fuel passages for supplying the fuel individually to the respective injection holes on the inner peripheral side and the respective injection holes on the outer peripheral side formed in each swirl vane;
valves provided in the respective fuel passages; and
a control section for controlling the valves to open or close,
a plurality of the combustion burners being arranged side by side in a circumferential direction, and
the control section exercises control over the plurality of the combustion burners in such a manner as to
bring all of the valves to an open state when the gas turbine is in a full load state, and
control an opening of the valves, which are provided in the fuel passages for supplying the fuel to the injection holes on the inner peripheral side, in accordance with a load, and close the valves provided in the fuel passages for supplying the fuel to the injection holes on the outer peripheral side, when the gas turbine is in a partial load state.
6. A combustor of a gas turbine, the combustor having a plurality of combustion burners each comprising:
a fuel nozzle; and
swirl vanes which are arranged at a plurality of locations, along a circumferential direction, on an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, said swirl vanes are progressively curved from an upstream side toward a downstream side of a flow of air flowing along the axial direction of the fuel nozzle in order to swirl the air around the fuel nozzle,
wherein the combustor comprises:
injection holes formed in each swirl vane for injecting a fuel, and injection holes formed in the fuel nozzle for injecting the fuel;
fuel passages for supplying the fuel individually to the respective injection holes formed in each swirl vane and the respective injection holes formed in the fuel nozzle;
valves provided in the respective fuel passages; and
a control section for controlling the valves to open or close,
a plurality of the combustion burners being arranged side by side in a circumferential direction, and
the control section exercises control over the plurality of the combustion burners in such a manner as to
bring all of the valves to an open state when the gas turbine is in a full load state, and
control an opening of the valves, which are provided in the fuel passages for supplying the fuel to the injection holes formed in the fuel nozzle, in accordance with a load, and close the valves provided in the fuel passages for supplying the fuel to the injection holes formed in the swirl vanes, when the gas turbine is in a partial load state.
7. The combustor of a gas turbine according to any one of claims 1 to 4 , characterized in that
an angle formed by a tangent to an average camber line of the swirl vane at a rear edge of the swirl vane and an axis line extending along the axial direction of the fuel nozzle is 0 to 10 degrees on an inner peripheral side of the rear edge of the swirl vane, and the angle is larger on an outer peripheral side of the rear edge of the swirl vane than the angle on the inner peripheral side of the rear edge of the swirl vane.
8. The combustor of a gas turbine according to any one of claims 1 to 4 , characterized in that
an angle formed by a tangent to an average camber line of the swirl vane at a rear edge of the swirl vane and an axis line extending along the axial direction of the fuel nozzle is 0 to 10 degrees on an inner peripheral side of the rear edge of the swirl vane, and is 25 to 35 degrees on an outer peripheral side of the rear edge of the swirl vane.