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US 10,894,605 B2Granted
Efficient low-noise aircraft propulsion system
AssigneeU.S. Aeronautics, Inc.
InventorJames Paul Hines
Life of this patent
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Abstract
An aircraft propulsion system comprising a reciprocating liquid cooled engine housed within the fuselage driving twin fuselage mounted ducted-fans is disclosed. The propulsion system may be liquid cooled with a liquid cooled exhaust and at least one turbocharger. The ducted-fans may run fan blade tip speeds of up to 97% Mach driven by a near constant RPM engine through a continuously variable transmission. The propulsion system may be low noise and may meet environmental standards typical in the automotive industry.
Claims15
A propulsion system for an aircraft, comprising:
- a reciprocating engine;
- a continuously variable transmission,
- wherein the reciprocating engine and the continuously variable transmission are housed within a fuselage of the aircraft;
- a liquid cooled exhaust system;
- and
- a ducted fan assembly configured to be powered by the reciprocating engine via a drive shaft connected to the continuously variable transmission,
- wherein the ducted fan assembly is configured to be mounted to the exterior of the fuselage,
- wherein the ducted fan assembly comprises at least three blades and one stator,
- wherein the drive shaft is configured to be at least partially housed within the one stator.
6 more elements
A propulsion system for an aircraft, comprising:
- a reciprocating engine;
- a continuously variable transmission,
- wherein the reciprocating engine and the continuously variable transmission are housed within a fuselage of the aircraft;
- a liquid cooled exhaust system;
- and
- a ducted fan assembly powered by the reciprocating engine via a drive shaft connected to the continuously variable transmission,
- wherein the ducted fan assembly is configured to be mounted to the exterior of the fuselage,
- wherein the ducted fan assembly comprises at least three blades and one stator,
- wherein the drive shaft is configured to be at least partially housed within the one stator,
- wherein a turbocharger is configured to compress engine inlet air to maintain a constant temperature and pressure during at least one flight phase;
- and
- an intercooler configured to cool exhaust air prior to the exhaust air entering a catalytic converter.
9 more elements
Dependencies are inferred from the claim text.