Parallel hybrid-electric aircraft engine

Abstract

A parallel hybrid-electric aircraft engine that provides power for takeoff and climb by combining the output power of an electric motor with that an internal combustion engine and then converting the electric motor to a generator once the additional power of the electric motor is no longer needed.

Claims

1. A parallel hybrid aircraft engine system, comprising; a variable pitch propeller having a propeller shaft; an out-runner electric motor, receiving the propeller shaft and enabled to transmit rotary power to the propeller shaft; a gasoline or diesel internal combustion engine having an engine output shaft and enabled to transmit power to the propeller shaft; an over-running sprag clutch receiving the engine output shaft; and a flexible belt providing a connection between the sprag clutch and the electric motor providing translation of power from the engine output shaft to the electric motor and thereby to the propeller shaft via the sprag clutch and flexible belt; wherein the electric motor is positioned between the propeller shaft and the sprag clutch, the engine output shaft is positioned between the sprag clutch and the internal combustion engine and both the electric motor and the internal combustion engine transmit power to the propeller shaft in parallel via the connection between the sprag clutch and the electric motor via the belt, providing power for takeoff and climb.

2. The system of claim 1, wherein the sprag clutch disengages from the engine output shaft in an event of a failure of the internal combustion engine.

3. The system of claim 1, wherein the electric motor is enabled to switch to a generator to provide power for accessories and to recharge the batteries.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) A complete understanding of the present invention may be obtained by reference to the accompanying drawings, when considered in conjunction with the subsequent, detailed description, in which:

(2) FIG. 1 is a front perspective view of a parallel hybrid-electric aircraft engine;

(3) FIG. 2 is a lower perspective view of a parallel hybrid-electric aircraft engine;

(4) FIG. 3 is a left view of a parallel hybrid-electric aircraft engine;

(5) FIG. 4 is a front view of a parallel hybrid-electric aircraft engine;

(6) FIG. 5 is a top view of a parallel hybrid-electric aircraft engine; and

(7) FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine.

(8) For purposes of clarity and brevity, like elements and components will bear the same designations and numbering throughout the Figures.

DESCRIPTION OF THE PREFERRED EMBODIMENT

(9) FIG. 1 is a perspective view of a hybrid-electric aircraft engine consisting of an internal combustion engine 10, sprag clutch 30, flexible belt 40, electric motor 50 and propeller 20. FIG. 2 is a lower perspective view of parallel hybrid electric engine showing the internal combustion engine 10, sprag clutch 30, flexible belt 40, electric motor 50 and propeller 20. FIG. 3 is a left side view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, flexible belt 40, electric motor 50 and propeller 20. FIG. 4 is a front view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, sprag clutch 30, flexible belt 40, electric motor 50, engine output shaft 60 and propeller 20. FIG. 5 is a top view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, flexible belt 40, electric motor 50 and propeller 20. FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, flexible belt 40, electric motor 50 and propeller 20.

(10) Since other modifications and changes varied to fit particular operating requirements and environments will be apparent to those skilled in the art, the invention is not considered limited to the example chosen for purposes of disclosure, and covers all changes and modifications which do not constitute departures from the true spirit and scope of this invention.

(11) Having thus described the invention, what is desired to be protected by Letters Patent is presented in the subsequently appended claims.