CRYOGENIC AIR SEPARATION ENHANCED GAS TURBINE
A turbine engine assembly includes a compressor section where an inlet airflow is compressed, a cryogenic fuel system for generating flow of cryogenic fuel, an air separation system where an airflow is placed in thermal communication with a portion of the flow of cryogenic fuel for generating an enhanced oxygen flow. In a combustor section, the compressed inlet airflow and a portion of the enhanced oxygen flow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path to a turbine section where expansion of the exhaust gas flow is utilized to generate a mechanical power output. Water is extracted from the exhaust gas flow in condenser transformed into a steam flow for injection into the core flow path in an evaporator system.
1 . A turbine engine assembly comprising:
a compressor section where an inlet airflow is compressed to generate a pressurized airflow;
a cryogenic fuel system for generating flow of cryogenic fuel;
an air separation system where a portion of the pressurized airflow from the compressor section is placed in thermal communication with a portion of the flow of cryogenic fuel for generating a pressurized enhanced oxygen flow;
a combustor section where the compressed inlet airflow and the pressurized enhanced oxygen flow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path;
a turbine section where expansion of the exhaust gas flow is utilized to generate a mechanical power output;
a condenser where water is extracted from the exhaust gas flow; and
an evaporator system where thermal energy from the exhaust gas flow is utilized to transform water extracted from the exhaust gas flow into a steam flow for injection into the core flow path.
2 - 3 . (canceled)
4 . The turbine engine assembly as recited in claim 1 , wherein the air separation system generates a nitrogen enriched flow that is communicated away from the core flow path through the turbine section.
5 . The turbine engine assembly as recited in claim 4 , wherein the nitrogen enriched flow is directed to cool a portion of the compressor section.
6 . (canceled)
7 . The turbine engine assembly as recited in claim 1 , wherein the air separator system comprises a first heat exchanger disposed outside of a core flow path, the heat exchanger configured to communicate the flow of cryogenic fuel with a flow of air.
8 - 10 . (canceled)
11 . An aircraft propulsion system comprising:
a core engine configured to generate an exhaust gas flow, the core engine including a core flow path through a compressor section, a combustor section and a turbine section, wherein the compressor section generates a pressurized airflow that is communicated to the combustor section;
a cryogenic fuel system configured to generate flow of cryogenic fuel;
an air separation system where a portion of the pressurized airflow from the compressor section is placed in thermal communication with a portion of the flow cryogenic fuel for liquifying a portion of oxygen from the pressurized airflow to generate an enhanced oxygen flow, wherein a portion of the enhanced oxygen flow is injected into the combustor section;
a condenser where water is extracted from the exhaust gas flow; and
an evaporator system where thermal energy from the exhaust gas flow is utilized to transform water extracted from the exhaust gas flow into a steam flow for injection into the core flow path.
12 - 15 . (canceled)
16 . The aircraft propulsion system as recited in claim 11 , wherein the air separation system generates a nitrogen enriched flow that is communicated away from the core flow path through the turbine section.
17 . A method of operating a gas turbine engine, the method comprising:
generating a flow of cryogenic fuel;
separating oxygen from a pressurized airflow from a compressor section of the gas turbine engine by liquifying oxygen through cooling with the flow cryogenic fuel to generate an enhanced oxygen flow;
generating an exhaust gas flow in a combustor with a portion of the cryogenic fuel flow and the enhanced oxygen flow;
expanding the gas flow through a turbine section and generating a mechanical power output;
extracting water from the exhaust gas flow in a condenser;
transforming the water flow to a steam flow with heat from the exhaust gas flow in an evaporator system and injecting a portion of the steam flow into the combustor; and
controlling generation of the oxygen enhanced flow by adjusting a ratio of a flow of cryogenic fuel relative to the airflow communicated to an air separator.
18 . The method as recited in claim 17 , further comprising separating a nitrogen enriched gas flow from the airflow and routing the nitrogen enriched gas flow away from a core flow path.
19 - 20 . (canceled)
21 . The turbine engine as recited in claim 1 , wherein the generation of the pressurize enhanced oxygen flow is controlled by adjusting a ratio of a flow of cryogenic fuel relative to pressurized airflow communicated to the air separator.
22 . The turbine engine as recited in claim 1 , wherein the compressor section includes a low pressure compressor and a high pressure compressor and the pressurized inlet airflow is drawn from a location between the low pressure compressor and the high pressure compressor.
23 . The aircraft propulsion system as recited in claim 11 , wherein the generation of the pressurize enhanced oxygen flow is controlled by adjusting a ratio of a flow of cryogenic fuel relative to pressurized airflow communicated to the air separator.
24 . The aircraft propulsion system as recited in claim 11 , wherein the compressor section includes a low pressure compressor and a high pressure compressor and the pressurized inlet airflow is drawn from a location between the low pressure compressor and the high pressure compressor.
25 . The method as recited in claim 17 , wherein the compressor section includes a low pressure compressor and a high pressure compressor and further comprising drawing the pressurized airflow from a location between the low pressure compressor and the high pressure compressor.