Electric centrifugal compressor of a turbine engine or aircraft
The invention relates to an electric centrifugal compressor, in particular for a turbine engine or aircraft, including an electric motor, the stator of which is supported by a casing and the rotor of which includes a shaft mounted inside the casing, driving a centrifugal compressor impeller, the casing having a double skin and including two substantially cylindrical, coaxial skins extending around the engine and defining between them an annular section suitable for the circulation of a first cooling air flow, one inlet of which is located at a first longitudinal end of the shaft and an outlet of which is connected to a second longitudinal end of the shaft, which supports the centrifugal compressor impeller, wherein it includes means (J) for collecting a second air flow at the outlet of the centrifugal compressor impeller, means for channelling the second air flow along the shaft up to the first end, and means for discharging the second air flow out of the casing in order to prevent same from mixing with the first air flow.
1. An electric centrifugal compressor comprising:
an electric motor, the stator of which is supported by a casing and the rotor of which includes a shaft mounted inside said casing, said shaft driving a centrifugal compressor impeller,
said casing having a double skin and comprising two substantially cylindrical, coaxial skins extending around said electric motor and defining between them an annular flow path for the circulation of a first cooling air flow, one inlet of which is located at a first longitudinal end of said shaft and an outlet of which is connected to a second longitudinal end of said shaft, which supports said centrifugal compressor impeller,
wherein said compressor includes means (J) for collecting a second air flow at the outlet of said centrifugal compressor impeller, means for channeling said second air flow along said shaft up to said first end, and means for discharging said second air flow out of said casing in order to prevent said second air flow from mixing with said first air flow.
2. The compressor according to claim 1 , in which the outlet of said annular flow path is connected to an air inlet of said centrifugal impeller.
3. The compressor according to claim 2 , in which said casing connects the outlet of said flow path to the air inlet of said centrifugal impeller.
4. The compressor according to claim 1 , in which said compressor includes bearings intersected by said shaft and secured to the casing, whereby said second air flow being intended to circulate between the bearings and said shaft.
5. The compressor according to claim 4 , in which said shaft includes a radial collar inserted between two radial walls of the bearings.
6. The electric centrifugal compressor according to claim 4 wherein the bearings comprise foil bearings.
7. The compressor according to claim 1 , in which said discharge means includes a nozzle configured to regulate the flow of said second air flow.
8. The compressor according to claim 7 , in which said casing includes or supports a deflector configured to disperse said second air flow.
9. The compressor according to claim 8 , in which a shielding is mounted and sealed on the casing, at the level of said first end of said shaft, and is configured to prevent said first air flow from mixing with said second airflow.
10. A turbine engine, including the electric centrifugal compressor according to claim 1 .
11. An aircraft, including the electric centrifugal compressor according to claim 1 .
12. The aircraft according to claim 11 wherein the electric centrifugal compressor powers a fuel cell.
13. The aircraft according to claim 11 wherein the electric centrifugal compressor pressurizes an enclosure.
14. The electric centrifugal compressor according to claim 1 for a turbine engine.
15. The electric centrifugal compressor according to claim 1 for an aircraft.
16. A turbine engine including the electric centrifugal compressor according to claim 1 , to power a fuel cell.
17. A turbine engine including the electric centrifugal compressor according to claim 1 , to pressurize an enclosure.
18. A turbine engine of an aircraft, including the electric centrifugal compressor according to claim 1 .