Gas turbine combustor and operating method thereof
View Patent ↗A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets.
1. A combustor comprising:
a combustion chamber supplied with fuel and air;
a plurality of fuel nozzles each injecting fuel from an upstream side to a downstream side of said combustion chamber; and
a member facing said combustion chamber and having a plurality of holes formed therein, peripheral walls of said plurality of holes defining a plurality of premixing flow passages, respectively; and
wherein downstream ends of said plurality of nozzles are positioned substantially adjacent inlets of said plurality of holes, respectively,
said member allows all or almost all of combustion air to flow into said combustion chamber substantially in parallel with fuel jet flows injected from said plurality of fuel nozzles, and
said plurality of fuel nozzles are positioned with respect to said plurality of premixing flow passages respectively so that the combustion air flows so as to envelop the fuel jet flows from said plurality of fuel nozzles.
2. A combustor according to claim 1 , wherein said combustion air is air that remains to be supplied into said combustion chamber without flowing into an inside of a combustion liner defining said combustion chamber from a peripheral side of said combustion liner.
3. A combustor according to claim 2 , wherein said combustion air is the air that remains and is present at the upstream side of said combustion chamber, and flows into said combustion chamber through said premixing flow passages of said member.
4. A gas turbine comprising:
a combustion chamber supplied with fuel and air;
a plurality of fuel nozzles each injecting fuel from an upstream side to a downstream side of said combustion chamber;
a member facing said combustion chamber and having a plurality of holes formed therein, peripheral walls of said plurality of holes defining a plurality of premixing flow passages, respectively; and
a turbine supplied with the combusted gas from said combustion chamber; and
wherein downstream ends of said plurality of nozzles are positioned substantially adjacent inlets of said plurality of holes, respectively,
said member allows all or almost all of combustion air to flow into said combustion chamber substantially in parallel with fuel jet flows injected from said plurality of fuel nozzles, and
said plurality of fuel nozzles are positioned with respect to said plurality of premixing flow passages respectively so that the combustion air flows so as to envelop the fuel jet flows from said plurality of fuel nozzles.
5. A gas turbine according to claim 4 , wherein said combustion air is air that remains to be supplied into said combustion chamber without flowing into an inside of a combustion liner defining said combustion chamber from a peripheral side of said combustion liner.
6. A gas turbine according to claim 5 , wherein said combustion air is the air that remains and is present at the upstream side of said combustion chamber, and flows into said combustion chamber through said premixing flow passages of said member.