Gas turbine combustor and fuel supply method for same
View Patent ↗A gas turbine combustor for mixing fuel into combustion air introduced from a compressor, burning an air-fuel mixture, and supplying produced combustion gas to a gas turbine. The combustor has a liquid fuel nozzle for jetting out liquid fuel and a pre-mixture chamber wall having a hollow conical shape gradually spreading in the direction in which the fuel is jetted out from the liquid fuel nozzle, and defining a pre-mixture chamber therein. A plurality of gaseous fuel nozzles are disposed around the pre-mixture chamber wall in an opposing relation respectively to a plurality of air inlet holes bored through the pre-mixture chamber wall and jet out gaseous fuel substantially coaxially with the axes of the air inlet holes.
1. A gas turbine combustor for mixing fuel into combustion air introduced from a compressor, burning an air-fuel mixture, and supplying produced combustion gas to a gas turbine, the combustor comprising:
a first fuel nozzle for jetting out fuel;
a pre-mixture chamber having a single wall defining said pre-mixture chamber therein downstream of the first fuel nozzle;
air holes bored in a circumferential direction through said pre-mixture chamber wall in plural stages in the direction of an axis of the pre-mixture chamber wall; and
second fuel nozzles disposed in plural stages in the direction of the axis around an exterior of said pre-mixture chamber wall in an opposing relationship and alignment respectively with said air holes;
said air holes and said second fuel nozzles being configured to generate swirling flows in said pre-mixture chamber, and
the length of each of the air holes effective for mixing being determined by the thickness of the pre-mixture chamber wall.
2. A gas turbine combustor according to claim 1 :
wherein said first fuel nozzle and said air holes are configured such that an axis of the first fuel nozzle does not intersect axes of the air holes.
3. A gas turbine combustor according to claim 2 , wherein the axes of said air holes coincides with axes of said second fuel nozzles.
4. A gas turbine combustor according to claim 1 :
wherein said first fuel nozzle and said second fuel nozzles are configured such that an axis of the first fuel nozzle does not intersect axes of the second fuel nozzles.
5. A gas turbine combustor according to claim 1 , wherein said air holes and said second fuel nozzles are configured so that fuel introduced through said second fuel nozzles and the combustion air are roughly mixed as a roughly mixed gas in said air holes, and part of said swirling flows is generated upon the jetting out of the roughly mixed gas from said air holes into said pre-mixture chamber.
6. A gas turbine combustor according to claim 1 , wherein said air holes and said second fuel nozzles are configured so that fuel introduced through said second fuel nozzles and the combustion air are roughly mixed as a roughly mixed gas in said air holes and jetted out from said air holes into said pre-mixture chamber, and part of said swirling flows is a circumferential flow in said pre-mixture chamber.
7. A gas turbine combustor for mixing fuel into combustion air introduced from a compressor, burning an air-fuel mixture, and supplying produced combustion gas to a gas turbine, the combustor comprising:
a first fuel nozzle for jetting out fuel;
a pre-mixture chamber having a single wall defining said pre-mixture chamber being provided with said first fuel nozzle at a center thereof, and having a shape gradually spreading in the direction in which the fuel is jetted out from said first fuel nozzle;
air holes bored in a circumferential direction through said pre-mixture chamber wall in plural stages in the direction of an axis of the pre-mixture chamber wall; and
second fuel nozzles disposed in plural stages in the direction of the axis around an exterior of said pre-mixture chamber wall in an opposing relationship and alignment respectively with said air holes;
said air holes and said second fuel nozzles being configured to generate swirling flows in said pre-mixture chamber,
said air holes being configured to roughly mix therein fuel supplied from said second fuel nozzles and air and then jet out therefrom the fuel and air in a roughly mixed gas state.
8. A gas turbine combustor according to claim 7 , wherein said air holes and said second fuel nozzles are configured with the roughly mixed gas jetted out from said air holes into said pre-mixture chamber, so that part of said swirling flows generated is a circumferential flow in said pre-mixture chamber.
9. A fuel supply method for a gas turbine combustor for mixing combustion air introduced from a compressor and fuel in a pre-mixture chamber defined by a single pre-mixture chamber wall, the method comprising the steps of:
jetting first fuel into said pre-mixture chamber from the upstream side in said pre-mixture chamber; jetting a second fuel from a plurality of fuel nozzle positions outside of said pre-mixture chamber and opposing to air holes aligned with the plurality of fuel nozzle positions, the air holes bored in a circumferential direction through said pre-mixture chamber in plural stages in the direction of an axis of the pre-mixture chamber wall; and
introducing said second fuel and said combustion air as a roughly mixed gas from said air holes into said pre-mixture chamber so as to generate swirling flows in said pre-mixture chamber.
10. A fuel supply method for a gas turbine combustor according to claim 9 , wherein part of said swirling flows generated from said jetting of said roughly mixed gas through said air holes into said pre-mixture chamber is a circumferential flow in said pre-mixture chamber.