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 neede

Claims

1. A method for takeoff and climb in an aircraft comprising: powering a first mechanical-rotary shaft using a first internal combustion engine; powering a first electrical-rotary shaft using electrical power stored in the electricity storage device or via connection to the first mechanical-rotary shaft; applying to the takeoff and climb a portion of a thrust generated by the first mechanical-rotor; selectively applying to the takeoff and climb, in parallel with the first mechanical rotary shaft, at least a portion of a thrust generated by the first electrical-rotary shaft.

2. The method of claim 1, wherein the selective applying of thrust of the first electrical-rotary shaft is accomplished via a connection between the first mechanical-rotary shaft and the first electrical-rotary shaft via a clutch and belt.

3. The method of claim 2, wherein generation of electrical power using the first internal combustion engine is accomplished via the connection and the electrical power generated is stored in a battery.

4. The method of claim 3, wherein the electrical power generated is used to power accessories in an aircraft.

5. The method of claim 2 comprising a further step of removing power from either the first mechanical-rotary shaft or the first electrical-rotary shaft via the clutch.

6. The method of claim 5, wherein the clutch is a sprag clutch.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0013] 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:

[0014] FIG. 1 is a front perspective view of a parallel hybrid-electric aircraft engine;

[0015] FIG. 2 is a lower perspective view of a parallel hybrid-electric aircraft engine;

[0016] FIG. 3 is a left view of a parallel hybrid-electric aircraft engine;

[0017] FIG. 4 is a front view of a parallel hybrid-electric aircraft engine;

[0018] FIG. 5 is a top view of a parallel hybrid-electric aircraft engine; and

[0019] FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine.

[0020] 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

[0021] 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.

[0022] 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.

[0023] Having thus described the invention, what is desired to be protected by Letters Patent is presented in the subsequently appended claims.