Thermoelectric generator on an aircraft bleed system
A device for producing electrical power has a thermoelectric device coupled to an aircraft bleed system for generating electrical power using temperature differentials between ram air and bleed air. A system control is coupled to the ram air and the bleed air to control a temperature of the bleed air and to control a temperature gradient of the thermoelectric device.
1. A device for producing electrical power in an aircraft comprising:
a bleed air system bleeding air from one of an engine or compressor;
a thermoelectric device coupled to said bleed air system for generating said electrical power using temperature differentials between ram air and bleed air;
the thermoelectric device including an air-to-air heat exchanger receiving said ram air and said bleed air;
a bypass line for routing bleed air around the thermoelectric device; and
a system control coupled to the ram air and the bleed air to control a temperature of the bleed air and to control a temperature gradient of the thermoelectric device by selectively bypassing bleed air around the thermoelectric device.
2. The device of claim 1 , wherein said bleed air system comprises:
an ozone converter for reducing ozone levels within said bleed air;
the air-to-air heat exchanger receiving said ram air and said bleed air from said ozone converter, wherein said ram air cools said bleed air; and
an air separator receiving said cooled bleed air, wherein said air separator separates said cooled bleed air into nitrogen and oxygen enriched fractions.
3. The device of claim 2 , further comprising a fuel tank for said nitrogen enriched fraction.
4. The device of claim 1 , wherein said bleed air provides a heat source and said ram air provides a cold source to create said temperature differentials.
5. The device of claim 1 , wherein said electrical power is generated from said thermoelectric device when said temperature differential is above a threshold value.
6. The device of claim 2 , further comprising a bypass flow valve coupled to the air separator to allow the bleed air to be passed through the air-to-air heat exchanger or bypass the air-to-air heat exchanger based on a temperature of the bleed air.
7. The device of claim 1 , wherein said system control displays a system status.
8. A method for generating power on an aircraft bleed system comprising:
receiving ram air;
receiving bleed air from one of an engine or compressor;
directing said ram air and said bleed air through a thermoelectric cell coupled to said aircraft bleed system for generating electrical energy, the thermoelectric cell including an air-to-air heat exchanger receiving said ram air and said bleed air;
a bypass line for routing bleed air around the thermoelectric cell; and
controlling a temperature of the bleed air and a temperature gradient of the thermoelectric device by selectively bypassing bleed air around the thermoelectric cell.
9. The method of claim 8 , further comprising cooling said bleed air by said thermoelectric cell reducing an amount of ram air used by said aircraft bleed system.
10. The method of claim 9 , wherein reducing an amount of ram air decreases air drag.
11. The method of claim 9 , wherein cooling said bleed air further comprises cooling said bleed air to about 230° C.
12. The method of claim 8 , further comprising coupling the thermoelectric cell to a nitrogen generation system.
13. A system for producing electrical power in an aircraft comprising:
a thermoelectric device with an air-to-air heat exchanger receiving bleed air from one of an engine or compressor, wherein said thermoelectric device produces electrical energy from a temperature difference between said bleed air and ram air while cooling said bleed air;
a bypass line for routing bleed air around the thermoelectric device; and
a system control coupled to the ram air and the bleed air to control a temperature of the bleed air and to control a temperature gradient of the thermoelectric device by selectively bypassing bleed air around the thermoelectric device.
14. The system of claim 13 , wherein said air-to-air heat exchanger cools said bleed air using said ram air.
15. The system of claim 13 , further comprising the system control controlling ram air flow and bleed air flow.
16. The system of claim 13 , further comprising a nitrogen generation system coupled to said thermoelectric device.
17. The system device of claim 16 , wherein said nitrogen generation system comprises:
an ozone converter for reducing ozone levels within said bleed air;
the air-to-air heat exchanger receiving said ram air and said bleed air from said ozone converter, wherein said ram air cools said bleed air; and
an air separator receiving said cooled bleed air, wherein said air separator separates said cooled bleed air into nitrogen and oxygen enriched fractions.