Electric propulsion unit of an aircraft comprising a cooling system incorporating at least one front air inlet and aircraft comprising at least one such electric propulsion unit

Patent metadata

Field	Value
Publication number	US-11952134-B2
Application number	US-202217737134-A
Country	US
Kind code	B2
Filing date	May 5, 2022
Priority date	May 7, 2021
Publication date	Apr 9, 2024
Grant date	Apr 9, 2024

Abstract

An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

First claim

The invention claimed is:

1. An electric propulsion unit of an aircraft comprising:
at least one electric power system,
at least one electric motor powered by the electric power system and comprising an output shaft,
a propeller driven in rotation by the electric motor,
a cooling system for the electric power system comprising a main cooling circuit which comprises:
a main air inlet,
at least one intake duct,
at least one main heat exchanger thermally connected to the electric power system,
at least an exhaust duct,
a main air outlet,

a nacelle housing the electric power system and the electric motor and comprising:
a central fairing,
a front fairing which extends from the central fairing to a front end, and
a rear fairing which extends from the central fairing to a rear end,

wherein the front fairing comprises a protrude positioned in a lower part of the front fairing, said protrude having a front face located in a transverse plane perpendicular to the output shaft, the main air inlet being positioned on the front face,
wherein the main cooling circuit is sized for the cooling needs of the electric power system during a cruise flight, and
wherein the cooling system comprises at least one secondary cooling circuit which comprises:
a secondary air inlet on a side face of the central fairing,
at least one intake duct,
at least one secondary heat exchanger,
at least one exhaust duct, and
a secondary air outlet aft of the main air outlet,

said at least one secondary cooling circuit being sized to increase a cooling capacity of the cooling system.

2. The electric propulsion unit according to claim 1 , wherein the front face is located in the same transverse plane as the front end of the front fairing.

3. The electric propulsion unit according to claim 1 , wherein the main air inlet occupies the entire front face.

4. The electric propulsion unit according to claim 1 , wherein the main air outlet is positioned on the rear fairing and configured to eject an air flow generating an additional thrust.

5. The electric propulsion unit according to claim 1 , wherein the main air outlet comprises at least one main flap which is adjustable in order to adjust an air mass flow in the main cooling circuit.

6. The electric propulsion unit according to claim 1 , wherein the main heat exchanger comprises an inlet face connected to the intake duct and an outlet face substantially parallel to the inlet face, connected to the exhaust duct, wherein the inlet and outlet faces of the main heat exchanger are inclined with respect to a transverse plane.

7. The electric propulsion unit according to claim 1 ,
wherein the central fairing comprises two side faces, and
wherein the secondary air inlet is positioned on one of the side faces of the central fairing, said secondary air inlet being of flush type.

8. The electric propulsion unit according to claim 1 , wherein the secondary air inlet comprises a secondary flap movable between a closed position in which the secondary flap completely closes the secondary air inlet and an at least partially open position in which the secondary flap at least partially clears the secondary air inlet.

9. The electric propulsion unit according to claim 1 , wherein the secondary cooling circuit comprises a fan to regulate an air mass flow in the secondary cooling circuit.

10. The electric propulsion unit according to claim 1 , wherein the secondary air outlet is positioned at a lower part of the rear fairing, between the main air outlet and the rear end of the rear fairing and configured to eject an air flow generating an additional thrust.

11. An aircraft comprising at least one electric propulsion unit according to claim 1 .

Assignees

• Airbus Sas
• Airbus Operations Sas
• Airbus Operations Gmbh
• Airbus Operations Sl

Inventors

• Carretero Benignos Jorge
• Bammer Benedikt
• Verseux Olivier
• Juanas Fernandez Maria Del Sagrario
• Molano Rembiasz Jorge
• Scherer Thomas
• Solntsev Alexander

Classifications

• B64D27/34

  All-electric aircraft · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D29/00 Primary

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D27/24 Primary

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• B64D33/08

  of power plant cooling systems · CPC title