Electric propulsion system of an aircraft
A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.
1. A propulsion system of an aircraft, comprising:
a system for producing electricity comprising a set of fuel cells;
at least one electric motor supplied with electricity by at least some of the fuel cells;
a propeller mechanically coupled to the at least one electric motor and driven only by the at least one electric motor; and
a nacelle housing at least the system for producing electricity and the at least one electric motor, said nacelle comprising an air circulation channel provided to allow the system for producing electricity to be cooled,
wherein the propeller is external to the nacelle,
wherein the air circulation channel extends inside the nacelle from a first end of said air circulation channel, that is situated at a first longitudinal end of the nacelle, to a second end of the air circulation channel located between the first longitudinal end of the nacelle and a second longitudinal end of the nacelle, the air circulation channel having an opening in a lateral wall of the nacelle between the first longitudinal end of the nacelle and the second longitudinal end of the nacelle, such that an entirety of the flow of air within said air circulation channel flows through the opening in the lateral wall of the nacelle and through the first longitudinal end of the nacelle;
wherein at least a part of the air circulation channel that is contiguous with the first end of the air circulation channel is delimited by an outer surface of cylindrical shape that surrounds a longitudinal axis of the nacelle;
wherein the air circulation channel receives a heat exchanger provided to allow the system for producing electricity to be cooled; and
wherein the propeller is situated near the first longitudinal end of the nacelle.
2. The propulsion system according to claim 1 , wherein in at least a part of the nacelle, considered along a length of the nacelle, there is only one air circulation channel, which is of circular section centered on the longitudinal axis of the nacelle and houses a fan provided to promote a circulation of air in the air circulation channel.
3. The propulsion system according to claim 2 , wherein the fan is housed in the air circulation channel, between the first end of the air circulation channel and the heat exchanger.
4. The propulsion system according to claim 1 , wherein the propeller is mounted to be able to rotate about the nacelle.
5. The propulsion system according to claim 1 , further comprising a device to adjust an air flow rate, which is associated with the first end of the air circulation channel.
6. The propulsion system according to claim 1 , wherein the propeller is mounted secured to a drive shaft of which a longitudinal axis corresponds to the longitudinal axis of the nacelle.
7. The propulsion system according to claim 1 , wherein the heat exchanger is installed in a part of the air circulation channel in which a section of the air circulation channel on a plane perpendicular to the longitudinal axis of the nacelle is shaped as a ring.
8. The propulsion system according to claim 1 , wherein the heat exchanger is installed in a part of the air circulation channel in which the air circulation channel is of circular section.
9. The propulsion system according to claim 8 , wherein the air circulation channel is of cylindrical shape and extends along a length of the nacelle, between the first end of the air circulation channel and a second end of the air circulation channel that opens near a second longitudinal end of the nacelle, which is opposite the first longitudinal end of the nacelle.
10. The propulsion system according to claim 1 , wherein the second end of the air circulation channel opens through the lateral wall of the nacelle, between the first longitudinal end of the nacelle and the second longitudinal end of the nacelle, which is opposite the first longitudinal end of the nacelle.
11. The propulsion system according to claim 10 , further comprising a hydrogen reservoir housed in the nacelle between the second end of the air circulation channel and the second longitudinal end of the nacelle.
12. The propulsion system according to claim 1 , further comprising a device for adjusting an air flow rate, which is associated with a second end of the air circulation channel.
13. The propulsion system according to claim 1 , wherein the first longitudinal end of the nacelle corresponds to a front longitudinal end of the nacelle.
14. The propulsion system according to claim 1 , wherein the first longitudinal end of the nacelle corresponds to a rear longitudinal end of the nacelle.
15. An aircraft comprising a propulsion system according to claim 1 .