Aircraft energy harvesting system
An energy harvesting system is provided and a corresponding method for harvesting energy from an aircraft cabin pressurization system utilizing the same. According to one aspect, an energy harvesting system includes an aircraft cabin enclosing a high-pressure environment of pressurized air. An air input receives incoming air from a low-pressure environment and an air output expels outgoing air from the high-pressure environment. A turbine receives the pressurized air expelled from the aircraft cabin and utilizes the pressurized air to produce rotational motion on a turbine shaft. An energy harvesting mechanism is coupled to the turbine shaft and utilizes the rotational motion from the turbine shaft to compress the incoming air or to create electrical energy.
1. An energy harvesting system, comprising:
an aircraft cabin enclosing a high-pressure environment comprising an interior aircraft cabin air at a first air pressure, the aircraft cabin defining a low-pressure environment exterior of the aircraft cabin comprising an exterior aircraft cabin air at a second air pressure lower than the first air pressure, wherein the aircraft cabin includes an air input, fluidly communicating between the low pressure environment and the aircraft cabin, and an air output, fluidly communicating between the aircraft cabin and the low pressure environment;
a turbine in fluid communication with the air output, the turbine comprising:
an expansion chamber configured to receive the interior aircraft cabin air and expand the received air from the first air pressure to the second air pressure; and
an exit chamber configured to direct the expanded air to the low-pressure environment via the air output;
wherein the turbine is configured to produce rotational motion of a turbine shaft in response to the received interior aircraft cabin air expanding; and
an energy harvesting mechanism comprising:
an entrance chamber in fluid communication with the air input and configured to receive the exterior aircraft cabin air; and
a compressor coupled to the turbine shaft and configured to compress the exterior aircraft cabin air and direct the compressed air into the aircraft cabin at the first air pressure, wherein the compressor defines a compression chamber configured to warm the compressed air; and
wherein the exit chamber of the turbine is thermally coupled to the entrance chamber of the energy harvesting mechanism such that heat from the exit chamber is transferred to the entrance chamber.
2. The energy harvesting system of claim 1 , wherein:
the energy harvesting mechanism further comprises an electrical generator coupled to the turbine shaft and configured to convert the rotational motion into electrical energy; and
the compressor is operably coupled to the generator so that the electrical energy drives the compressor.
3. The energy harvesting system of claim 2 , wherein the energy harvesting mechanism further comprises an electrical output configured to electrically couple the electrical generator to an electrical load for providing the electrical energy to the electrical load.
4. The energy harvesting system of claim 3 , wherein the electrical load comprises a heating device.
5. The energy harvesting system of claim 3 , wherein the electrical load comprises at least one of an electric motor, an electrical energy storage device, a sensor, and a lighting device.
6. The energy harvesting system of claim 3 , wherein the compressor is configured to receive the exterior aircraft cabin air at the second air pressure.
7. The energy harvesting system of claim 1 , wherein:
the compressor is mechanically coupled to the turbine shaft, the compressor configured to receive the exterior aircraft cabin air at the second air pressure; and
the energy harvesting system further comprises:
an electrical generator coupled to the turbine shaft and configured to convert the rotational motion into electrical energy; and
an electrical output configured to electrically couple the electrical generator to an electrical load for providing the electrical energy to the electrical load.
8. The energy harvesting system of claim 1 , wherein the energy harvesting system is one of an environmental control system (ECS) and a ventilation system.
9. The energy harvesting system of claim 1 , wherein the compression chamber of the compressor is thermally coupled to the expansion chamber of the turbine.
10. An energy harvesting system, comprising:
an aircraft cabin enclosing a high-pressure environment comprising an interior aircraft cabin air at a first air pressure, the aircraft cabin defining a low-pressure environment exterior of the aircraft cabin comprising an exterior aircraft cabin air at a second air pressure lower than the first air pressure, wherein the aircraft cabin includes an air input, fluidly communicating between the low pressure environment and the aircraft cabin, and an air output, fluidly communicating between the aircraft cabin and the low pressure environment;
a turbine in fluid communication with the air output, the turbine comprising an expansion chamber configured to receive the interior aircraft cabin air and expand the received air from the first air pressure to the second air pressure, wherein the turbine is configured to produce rotational motion of a turbine shaft in response to the received interior aircraft cabin air expanding; and
an energy harvesting mechanism comprising:
an entrance chamber in fluid communication with the air input and configured to receive the exterior aircraft cabin air; and
a compressor coupled to the turbine shaft and configured to compress the exterior aircraft cabin air and direct the compressed air into the aircraft cabin at the first air pressure, wherein the compressor defines a compression chamber configured to warm the compressed air, and wherein the compression chamber is thermally coupled to the entrance chamber such that heat from the compression chamber is transferred to the entrance chamber.
11. The energy harvesting system of claim 10 , wherein:
the energy harvesting mechanism further comprises an electrical generator coupled to the turbine shaft and configured to convert the rotational motion into electrical energy; and
the compressor is operably coupled to the generator so that the electrical energy drives the compressor.
12. The energy harvesting system of claim 11 , wherein the energy harvesting mechanism further comprises an electrical output configured to electrically couple the electrical generator to an electrical load for providing the electrical energy to the electrical load.
13. The energy harvesting system of claim 11 , wherein the electrical load comprises a heating device.
14. The energy harvesting system of claim 11 , wherein the electrical load comprises at least one of an electric motor, an electrical energy storage device, a sensor, and a lighting device.
15. The energy harvesting system of claim 10 , wherein:
the compressor is mechanically coupled to the turbine shaft, the compressor configured to receive the exterior aircraft cabin air at the second air pressure; and
the energy harvesting system further comprises:
an electrical generator coupled to the turbine shaft and configured to convert the rotational motion into electrical energy; and
an electrical output configured to electrically couple the electrical generator to an electrical load for providing the electrical energy to the electrical load.
16. The energy harvesting system of claim 10 , wherein the energy harvesting system is one of an environmental control system (ECS) and a ventilation system.
17. The energy harvesting system of claim 10 , wherein the compression chamber of the compressor is thermally coupled to the expansion chamber of the turbine.
18. The energy harvesting system of claim 10 , wherein a heat sink material is disposed between the compression chamber and the entrance chamber.
19. An energy harvesting system, comprising:
an aircraft cabin enclosing a high-pressure environment comprising an interior aircraft cabin air at a first air pressure, the aircraft cabin defining a low-pressure environment exterior of the aircraft cabin comprising an exterior aircraft cabin air at a second air pressure lower than the first air pressure, wherein the aircraft cabin includes an air input, fluidly communicating between the low pressure environment and the aircraft cabin, and an air output, fluidly communicating between the aircraft cabin and the low pressure environment;
an energy harvesting mechanism comprising:
a compressor in fluid communication with the air input and configured to compress the exterior aircraft cabin air and direct the compressed air into the aircraft cabin at the first air pressure, wherein the compressor defines a compression chamber configured to warm the compressed air and an entrance chamber for receiving the exterior aircraft cabin air; and
a thermal mechanism operably coupled to the compressor and configured to receive heat energy from the compression chamber and transfer the heat energy from the compression chamber to the entrance chamber, wherein the thermal mechanism is thermally coupled to at least one of the air input or the air output.