IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0344697
(2012-01-06)
|
등록번호 |
US-8464511
(2013-06-18)
|
발명자
/ 주소 |
- Ribarov, Lubomir A.
- Gieras, Jacek F.
|
출원인 / 주소 |
- Hamilton Sundstrand Corporation
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
9 |
초록
▼
A turbomachine comprises a turbine shaft, first and second rotors, first and second propulsion stages, and a magnetic stator. The first rotor is rotationally coupled to the turbine shaft, and coaxially arranged along an axis. The first propulsion stage is rotationally coupled to the first rotor, opp
A turbomachine comprises a turbine shaft, first and second rotors, first and second propulsion stages, and a magnetic stator. The first rotor is rotationally coupled to the turbine shaft, and coaxially arranged along an axis. The first propulsion stage is rotationally coupled to the first rotor, opposite the turbine shaft. The second rotor is coaxially arranged about the first rotor, and the second propulsion stage is rotationally coupled to second rotor, opposite the turbine shaft and adjacent the first propulsion stage. The magnetic stator is coaxially arranged between the first rotor and the second rotor, forming a magnetic coupling between the and second rotors to drive the second propulsion stage in contra-rotation with respect to the first propulsion stage.
대표청구항
▼
1. A turbomachine comprising: a turbine shaft rotationally mounted along an axis;a first rotor rotationally coupled to the turbine shaft and coaxially arranged about the axis;a first propulsion stage rotationally coupled to the first rotor, opposite the turbine shaft;a second rotor coaxially arrange
1. A turbomachine comprising: a turbine shaft rotationally mounted along an axis;a first rotor rotationally coupled to the turbine shaft and coaxially arranged about the axis;a first propulsion stage rotationally coupled to the first rotor, opposite the turbine shaft;a second rotor coaxially arranged about the first rotor;a second propulsion stage rotationally coupled to second rotor, opposite the turbine shaft and adjacent the first propulsion stage;a magnetic stator coaxially arranged between the first rotor and the second rotor and forming a magnetic coupling between the first rotor and the second rotor to drive the second propulsion stage in contra-rotation with respect to the first propulsion stage. 2. The turbomachine of claim 1, wherein the first and second rotors comprise permanent magnetic elements to form the magnetic coupling. 3. The turbomachine of claim 1, wherein the first and second rotors comprise cage windings to form the magnetic coupling. 4. The turbomachine of claim 1, wherein the stator coil comprises first and second windings to form the magnetic coupling. 5. The turbomachine of claim 4, wherein the first and second windings are switchable to drive the first and second propulsion stages in co-rotation about the axis. 6. The turbomachine of claim 1, wherein the magnetic stator comprises a coil having a number of poles selected to drive the first and second propulsion stages at different rotational speeds. 7. The turbomachine of claim 1, further comprising an engine core coupled to the turbine shaft opposite the first rotor, the engine core comprising a compressor, a combustor and a turbine arranged in flow series along the axis. 8. A turboprop engine comprising the turbomachine of claim 7, wherein the first and second propulsion stages comprise contra-rotating propellers. 9. The turboprop engine of claim 8, further comprising a clutch mechanism coupled to the first rotor, wherein the clutch mechanism is operable to rotationally decouple the contra-rotating propellers from the turbine shaft. 10. A turbofan engine comprising the turbomachine of claim 7, wherein the first and second propulsion stages comprise contra-rotating fan rotors. 11. A turboshaft engine comprising the turbomachine of claim 7, wherein the first and second propulsion stages comprise contra-rotating lift rotors. 12. A propulsion engine comprising: an engine core comprising a compressor, a combustor and a turbine arranged in flow series along an axis;a primary magnetic rotor rotationally coupled to the engine core along the axis;a primary propulsion rotor coaxially coupled to the primary magnetic rotor, opposite the engine core along the axis;a secondary magnetic rotor coaxially arranged about the primary magnetic rotor;a secondary propulsion rotor coaxially coupled to the secondary magnetic rotor, opposite the engine core along the axis and adjacent the primary propulsion rotor; anda magnetic stator coaxially arranged between the primary magnetic rotor and the secondary magnetic rotor, the magnetic stator forming a magnetic coupling between the primary and secondary magnetic rotors to drive the primary and secondary propulsion stages in contra-rotation about the axis. 13. The propulsion engine of claim 12, wherein the primary and secondary magnetic rotors comprise permanent magnet elements to form the magnetic coupling. 14. The propulsion engine of claim 12, wherein the primary and secondary magnetic rotors comprise cage windings or solid conductive cylinders to form the magnetic coupling. 15. The propulsion engine of claim 12, wherein the magnetic stator comprises a two windings distributed in inner and outer slots switchable to drive the primary and secondary propulsion rotors in co-rotation about the axis. 16. The propulsion engine of claim 12, wherein the magnetic stator comprises a coil having a selected number of poles to drive the primary and secondary propulsion rotors at different rotational speeds. 17. A turboprop engine comprising the propulsion engine of claim 12, wherein the primary and secondary propulsion rotors comprise contra-rotating propellers. 18. The turboprop engine of claim 17, further comprising a clutch mechanism to decouple the contra-rotating propellers from the engine core. 19. The turboprop engine of claim 17, wherein the contra-rotating propellers have different numbers of blades. 20. A turbofan engine comprising the propulsion engine of claim 12, wherein the primary and secondary propulsion rotors comprise contra-rotating fan stages.
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