Providing oxidation to a gas turbine engine
View Patent ↗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.
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; and
a 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; and
a 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.