Vibration damper for aircraft engine
AssigneeBrp-Rotax GmbH & Co. KG
InventorsThomas Koch, Johann Bayerl
Life of this patent
Estimating the term…
Abstract
An internal combustion engine for an aircraft is described. The internal combustion engine includes a crankshaft defining first and second ends, a propeller, and a transmission disposed between the first end of the crankshaft and the propeller, operatively connecting the propeller to the crankshaft. A torsion bar is disposed between the first end of the crankshaft and the transmission, operatively connecting the crankshaft to the transmission. A torsional vibration damper is operatively connected at one of the first and the second ends of the crankshaft.
Claims32
A drive unit, comprising:
- an air propeller;
- and
- an internal combustion engine comprising
- a crankshaft defining first and second ends,
- a transmission disposed between the first end of the crankshaft and the air propeller, operatively connecting the air propeller to the crankshaft, the transmission comprising a reduction gearing for reducing the speed of 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 or the second ends of the crankshaft.
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 or the second ends of the crankshaft,
- wherein the torsional vibration damper is a viscous damper.
An aircraft, comprising:
- a fuselage;
- at least one wing attached to the fuselage to provide a lifting force upon movement of the wing through, air;
- and
- at least one aircraft drive unit comprising
- an air propeller, and
- an internal combustion engine comprising
- a crankshaft defining first and second ends,
- a transmission disposed between the first end of the crankshaft and the air propeller, operatively connecting the air propeller to the crankshaft, the transmission comprising a reduction gearing for inducing the speed of 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 or the second ends of the crankshaft.
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 or the second ends of the crankshaft,
- wherein the torsional vibration damper is a viscous damper.
Dependencies are inferred from the claim text.