IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0305711
(2005-12-16)
|
등록번호 |
US-7575192
(2009-08-31)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
7 인용 특허 :
24 |
초록
▼
A transmission system for use with a microturbine engine that includes an input shaft operably coupled to the output shaft of the microturbine engine. The output shaft of the microturbine engine and the input shaft of the transmission system operate at a rotational speed in a range between 50,000 an
A transmission system for use with a microturbine engine that includes an input shaft operably coupled to the output shaft of the microturbine engine. The output shaft of the microturbine engine and the input shaft of the transmission system operate at a rotational speed in a range between 50,000 and 250,000 RPM with an output power between 200 and 5 HP. The transmission system includes a gear train having a first gear that interfaces to a second gear, the first and second gears employing teeth with opposite handed helix-angled surfaces that apply axial forces to the input shaft during both normal operation and start-up operations, which pushes the input shaft toward the output shaft of the microturbine engine. Preferably, the helix-angled surfaces on respective normal drive sides of the teeth produce an axial force during normal operation that will not be overcome with the axial force produced by the mass time acceleration of the first gear. The gear train interfaces to a starter-generator preferably through the second gear. The gear train preferably provides a reduction ratio having a value greater than 24.
대표청구항
▼
What is claimed is: 1. A transmission system for use with a microturbine engine having an output shaft, the transmission system comprising: an input shaft operably coupled to the output shaft of the microturbine engine; and a gear train including a first gear and a second gear that interface to one
What is claimed is: 1. A transmission system for use with a microturbine engine having an output shaft, the transmission system comprising: an input shaft operably coupled to the output shaft of the microturbine engine; and a gear train including a first gear and a second gear that interface to one another, the first gear fixed relative to said input shaft and rotating in the same direction as the input shaft, the second gear fixed relative to a counter-rotating shaft and rotating in the opposite direction of said input shaft, wherein the first and second gears employ teeth with first-type and second-type opposite handed helix-angled surfaces, the first-type opposite handed helix-angled surfaces applying axial forces to said input shaft during a normal operation mode where the microturbine engine drives the transmission system and the second-type opposite handed helix-angled surfaces applying axial forces to said input shaft during a start up operation mode where a generator drives the transmission system and microturbine engine, said first-type and second-type opposite handed helix-angled surfaces on respective normal drive sides and normal coast sides of the teeth, and said axial forces pushing the input shaft toward the output shaft of the microturbine engine. 2. A transmission system according to claim 1, wherein: said axial forces applied to said input shaft during normal operation by the first-type helix-angled surfaces on respective normal drive sides of the teeth of the first and second gears are greater than the axial force produced by the mass times acceleration of the first gear. 3. A transmission system according to claim 1, further comprising: a starter-generator operably coupled to the gear train. 4. A transmission system according to claim 3, wherein: said starter-generator is operably coupled to the second gear of the gear train. 5. A transmission system according to claim 4, wherein: the gear train includes an idler gear that operably couples said starter generator to the second gear, the idler gear interfacing to the second gear. 6. A transmission system according to claim 5, wherein: the gear train includes a pinion gear that is operably coupled to the output of said starter-generator, the pinion gear interfacing to the idler gear. 7. A transmission system according to claim 5, wherein: the idler gear and the second gear have opposite handed helical teeth. 8. A transmission system according to claim 1, wherein: the input shaft of the transmission system is coupled to the output shaft of the microturbine engine by a coupling that permits axial movement of the input shaft relative to the output shaft. 9. A transmission system according to claim 8, wherein: the coupling between the input shaft and the output shaft of the microturbine engine comprises a piloted spline coupler. 10. A transmission system according to claim 9, wherein: the coupling between the input shaft and the output shaft of the microturbine engine comprises a polygonal spline coupler. 11. A transmission system according to claim 1, wherein: said gear train provides a reduction ratio having a value greater than 24. 12. A transmission system according to claim 1, wherein: output of said gear train is operably coupled to a rotating element for propelling an aircraft body. 13. A transmission system according to claim 12, wherein: said aircraft body comprises a fixed-wing aircraft body, and said rotating element comprises a propeller. 14. A transmission system according to claim 12, wherein: said aircraft body comprises a vertical-lift aircraft body, and said rotating element comprises a rotor. 15. A transmission system according to claim 1, wherein: the gear train comprises at least two speed reduction stages. 16. A transmission system according to claim 15, wherein: the at least two speed reduction stages comprise an offset compound idler configuration. 17. A transmission system according to claim 1, wherein: the gear train comprises a self-equilibrating input stage. 18. A transmission system according to claim 17, wherein: the input shaft is bearingless. 19. A transmission system according to claim 1, wherein: the input shaft operates at a maximum rotational speed that is greater than 100,000 RPM with an output power between 200 HP and 5 HP. 20. A transmission system according to claim 1, wherein: the input shaft operates at a maximum rotational speed that is greater than 200,000 RPM with an output power between 200 HP and 5 HP. 21. A transmission system according to claim 1, wherein: the input shaft operates at a rotational speed in a range between 50,000 RPM and 250,000 RPM with an output power between 200 HP and 5 HP. 22. A propulsion system for an aircraft comprising: a microturbine engine having an output shaft; and a transmission system having an input shaft operably coupled to the output shaft of the microturbine engine and a gear train; wherein the gear train includes a first gear and a second gear that interface to one another, the first gear fixed relative to said input shaft and rotating in the same direction as the input shaft, the second gear fixed relative to a counter-rotating shaft and rotating in the opposite direction of said input shaft, wherein the first and second gears employ teeth with first-type and second-type opposite handed helix-angled surfaces, the first-type opposite handed helix-angled surfaces applying axial forces to said input shaft during a normal operation mode where the microturbine engine drives the transmission system and the second-type opposite handed helix-angled surfaces applying axial forces to said input shaft during a start up operation mode where a generator drives the transmission system and microturbine engine, said first-type and second-type opposite handed helix-angled surfaces on respective normal drive sides and normal coast sides of the teeth, and said axial forces pushing the input shaft toward the output shaft of the microturbine engine. 23. A propulsion system according to claim 22, wherein: output of said gear train is operably coupled to a rotating element for propelling an aircraft body. 24. A propulsion system according to claim 23, wherein: said aircraft body comprises a fixed-wing aircraft body, and said rotating element comprises a propeller. 25. A propulsion system according to claim 23, wherein: said aircraft body comprises a vertical-lift aircraft body, and said rotating element comprises a rotor. 26. An aircraft comprising: an aircraft body; a propulsion system including a microturbine engine having an output shaft and a transmission system having an input shaft operably coupled to the output shaft of the microturbine engine and a gear train, wherein the gear train includes a first gear and a second gear that interface to one another, the first gear fixed relative to said input shaft and rotating in the same direction as the input shaft, the second gear fixed relative to a counter-rotating shaft and rotating in the opposite direction of said input shaft, wherein the first and second gears employ teeth with first-type and second-type opposite handed helix-angled surfaces, the first-type opposite handed helix-angled surfaces applying axial forces to said input shaft during a normal operation mode where the microturbine engine drives the transmission system and the second-type opposite handed helix-angled surfaces applying axial forces to said input shaft during a start up operation mode where a generator drives the transmission system and microturbine engine, said first-type and second-type opposite handed helix-angled surfaces on respective normal drive sides and normal coast sides of the teeth, and said axial forces pushing the input shaft toward the output shaft of the microturbine engine; and a rotating element, operably coupled to said propulsion system for propelling said aircraft body. 27. An aircraft according to claim 26, wherein: said aircraft body comprises a vertical-lift aircraft body, and said rotating element comprises a rotor. 28. An aircraft according to claim 26, wherein: said aircraft body comprises a fixed-wing aircraft body, and said rotating element comprises a propeller.
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