A gas turbine engine includes a compressor for compressing air from an environment; a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel; a turbine coupled with the compressor for receiving exhaust gas from the combustion and
A gas turbine engine includes a compressor for compressing air from an environment; a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel; a turbine coupled with the compressor for receiving exhaust gas from the combustion and powering the compressor; and an injector coupled with a source of oxidizer for injecting the oxidizer into the combustor. A method for operating a gas turbine engine includes compressing air from an environment; receiving the compressed air at a combustor; mixing the compressed air with fuel; injecting oxidizer into the combustor in addition to the air from the environment; combusting the fuel with the compressed air and the oxidizer; receiving exhaust gas from the combusted fuel; and powering the compression of the air from the environment using the exhaust gas.
대표청구항▼
1. A gas turbine engine comprising: a compressor for compressing air from an environment;a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel;a turbine coupled with the compressor for receiving exhaust gas from the combustion
1. A gas turbine engine comprising: a compressor for compressing air from an environment;a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel;a turbine coupled with the compressor for receiving exhaust gas from the combustion and powering the compressor;an injector coupled with a source of oxidizer for injecting an oxidizer into the combustor; anda swirler having the injector for spraying the oxidizer into the combustor, wherein the oxidizer is mixed with the fuel in at least one of a fuel line or a fuel spray nozzle for supplying the fuel to the combustor. 2. The gas turbine engine as recited in claim 1, wherein the source of oxidizer comprises at least one of oxygen, pressurized oxygen, liquid oxygen, or gasified liquid oxygen. 3. The gas turbine engine as recited in claim 1, wherein the source of oxidizer is coupled with a heat exchanger, and the heat exchanger is coupled with a controller for controlling a gasification rate of the oxidizer. 4. The gas turbine engine as recited in claim 1, wherein the swirler is positioned within a core entrance of a flame tube of the combustor. 5. The gas turbine engine as recited in claim 1, further comprising at least one of a cooling hole, a dilution hole, a pore, or a micro-pore for injecting the oxidizer into a flame tube of the combustor. 6. The gas turbine engine as recited in claim 1, further comprising a variable flow diffuser for adjusting the pressure in the combustor. 7. A gas turbine engine comprising: a compressor for compressing air from an environment;a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel;a turbine coupled with the compressor for receiving exhaust gas from the combustion and powering the compressor;an injector coupled with a source of oxidizer for injecting the oxidizer into the combustor, the injector positioned within a core entrance of the combustor for spraying the oxidizer into the combustor, wherein the oxidizer is mixed with the fuel in at least one of a fuel line or a fuel spray nozzle for supplying the fuel to the combustor. 8. The gas turbine engine as recited in claim 7, further comprising a variable flow diffuser for adjusting the pressure in the combustor. 9. The gas turbine engine as recited in claim 1, further comprising a fuel injector for injecting the fuel into the combustor, wherein the fuel injector and the injector are positioned within a flame tube of the combustor. 10. The gas turbine engine as recited in claim 1, wherein the oxidizer is injected within a flame tube of the combustor. 11. The gas turbine engine as recited in claim 7, wherein a variable flow diffuser is automatically controlled for adjusting the pressure in the combustor. 12. The gas turbine engine as recited in claim 7, wherein the injection of the oxidizer into the combustor is automatically controlled. 13. The gas turbine engine as recited in claim 7, wherein the oxidizer is supplied from a source of oxidizer coupled with a heat exchanger, and the heat exchanger is coupled with a controller for controlling a gasification rate of the oxidizer. 14. The gas turbine engine as recited in claim 7, wherein the injector is positioned between the core entrance of the combustor and a primary combustion zone within the combustor. 15. The gas turbine engine as recited in claim 7, wherein the source of oxidizer comprises at least one of oxygen, pressurized oxygen, liquid oxygen, or gasified liquid oxygen. 16. The gas turbine engine as recited in claim 7, wherein the oxidizer is injected within a flame tube of the combustor. 17. The gas turbine engine as recited in claim 7, further comprising at least one of a cooling hole, a dilution hole, a pore, or a micro-pore for injecting the oxidizer into a flame tube of the combustor. 18. A gas turbine engine comprising: a compressor for compressing air from an environment;a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel;a turbine coupled with the compressor for receiving exhaust gas from the combustion and powering the compressor;an injector coupled with a source of oxidizer for injecting an oxidizer into the combustor; anda swirler having the injector for spraying the oxidizer into the combustor, wherein the swirler is positioned within a core entrance of a flame tube of the combustor.
Erlendur Steinthorsson ; Michael A. Benjamin ; David R. Barnhart, Fuel atomization method for turbine combustion engines having aerodynamic turning vanes.
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