Claims
- 1. An internal combustion engine for an aircraft, comprising:
a crankshaft defining first and second ends; a propeller; a transmission disposed between the first end of the crankshaft and the propeller, operatively connecting the propeller to the crankshaft; a torsion bar disposed between the first end of the crankshaft and the transmission, operatively connecting the crankshaft to the transmission; and a torsional vibration damper operatively connected at one of the first and the second ends of the crankshaft.
- 2. The internal combustion engine of claim 1, wherein the torsional vibration damper is disposed at the second end of the crankshaft.
- 3. The internal combustion engine of claim 1, wherein the torsional vibration damper is disposed at the first end of the crankshaft.
- 4. The internal combustion engine of claim 1, wherein the torsional vibration damper is a viscous damper.
- 5. The internal combustion engine of claim 4, wherein the torsional vibration damper comprises:
a flywheel; a housing disposed at a peripheral portion of the flywheel; an annular body disposed within the housing such that a gap exists between the annular body and the housing; and a viscous fluid disposed within the gap.
- 6. The internal combustion engine of claim 5, wherein the housing is integrated within the flywheel.
- 7. The internal combustion engine of claim 5, wherein the viscous fluid comprises silicon oil.
- 8. The internal combustion engine of claim 5, wherein the torsional vibration damper further comprises:
first and second rings disposed between the annular body and the housing at diagonally-opposed regions of the annular body to position the annular body within the housing such that the gap is maintained between the annular body and the housing.
- 9. The internal combustion engine of claim 8, wherein the first and second rings comprise plastic.
- 10. The internal combustion engine of claim 6, wherein the flywheel comprises:
a starter gear being disposed at an outer periphery thereof.
- 11. The internal combustion engine of claim 10, wherein the starter gear is integrally formed on the outer periphery of the flywheel.
- 12. The internal combustion engine of claim 5, wherein the flywheel further comprises:
a tubular extension connected to the flywheel at one side thereof.
- 13. The internal combustion engine of claim 12, wherein the tubular extension is integrally formed as a part of the flywheel.
- 14. The internal combustion engine of claim 12, wherein the tubular extension comprises:
at least one pulse-generator wheel affixed to a peripheral surface thereof, wherein the pulse-generator wheel operates in connection with at least one sensor to establish a rotational position of the crankshaft.
- 15. The internal combustion engine of claim 12, wherein the tubular extension comprises:
a rotor of an alternator affixed to a peripheral surface thereof.
- 16. The internal combustion engine of claim 1, further comprising:
a replaceable sleeve disposed between the crankshaft and the torsion bar, operatively connecting the crankshaft to the torsion bar.
- 17. An aircraft, comprising:
a fuselage; and at least one wing attached to the fuselage to provide a lifting force upon movement of the wing through air, wherein the fuselage is powered by an internal combustion engine comprising
a crankshaft defining first and second ends; a propeller; a transmission disposed between the first end of the crankshaft and the propeller, operatively connecting the propeller to the crankshaft; a torsion bar disposed between the first end of the crankshaft and the transmission, operatively connecting the crankshaft to the transmission; and a torsional vibration damper operatively connected at one of the first and the second ends of the crankshaft.
- 18. The aircraft of claim 17, wherein the torsional vibration damper is disposed at the second end of the crankshaft.
- 19. The aircraft of claim 17, wherein the torsional vibration damper is disposed at the first end of the crankshaft.
- 20. The aircraft of claim 17, wherein the torsional vibration damper is a viscous damper.
- 21. The aircraft of claim 20, wherein the torsional vibration damper comprises:
a flywheel; a housing disposed at a peripheral portion of the flywheel; an annular body disposed within the housing such that a gap exists between the annular body and the housing; and a viscous fluid disposed within the gap.
- 22. The aircraft of claim 21, wherein the housing is integrated within the flywheel.
- 23. The aircraft of claim 21, wherein the viscous fluid comprises silicon oil.
- 24. The aircraft of claim 21, wherein the torsional vibration damper further comprises:
first and second rings disposed between the annular body and the housing at diagonally-opposed regions of the annular body to position the annular body within the housing such that the gap is maintained between the annular body and the housing.
- 25. The aircraft of claim 24, wherein the first and second rings comprise plastic.
- 26. The aircraft of claim 22, wherein the flywheel comprises:
a starter gear being disposed at an outer periphery thereof.
- 27. The aircraft of claim 26, wherein the starter gear is integrally formed on the outer periphery of the flywheel.
- 28. The aircraft of claim 21, wherein the flywheel further comprises:
a tubular extension connected to the flywheel at one side thereof.
- 29. The aircraft of claim 28, wherein the tubular extension is integrally formed as a part of the flywheel.
- 30. The aircraft of claim 28, wherein the tubular extension comprises:
at least one pulse-generator wheel affixed to a peripheral surface thereof, wherein the pulse-generator wheel operates in connection with at least one sensor to establish a rotational position of the crankshaft.
- 31. The aircraft of claim 28, wherein the tubular extension comprises:
a rotor of an alternator affixed to a peripheral surface thereof.
- 32. The aircraft of claim 17, further comprising:
a replaceable sleeve disposed between the crankshaft and the torsion bar, operatively connecting the crankshaft to the torsion bar.
Parent Case Info
[0001] This non-provisional application claims priority from U.S. Provisional Patent Application Serial No. 60/331,380 filed on Nov. 14, 2001, and U.S. Provisional Patent Application Serial No. 60/341,874 filed on Dec. 21, 2001, the contents of both provisional applications are incorporated herein by reference.
Provisional Applications (2)
|
Number |
Date |
Country |
|
60331380 |
Nov 2001 |
US |
|
60341874 |
Dec 2001 |
US |