Hybrid propulsion drive train system for tiltrotor aircraft

Patent metadata

Field	Value
Publication number	US-11731772-B2
Application number	US-201815896383-A
Country	US
Kind code	B2
Filing date	Feb 14, 2018
Priority date	Mar 2, 2017
Publication date	Aug 22, 2023
Grant date	Aug 22, 2023

Abstract

The present invention includes a hybrid propulsion system for an aircraft comprising: one or more turboshaft engines that provide shaft power and are capable of providing thrust; at least one of: one or more electrical generators or one or more hydraulic pumps connected to a shaft of the one or more turboshaft engines; and at least two rotatable nacelles, each nacelle housing at least one of: one or more electric motors or one or more hydraulic motors each connected to a proprotor, wherein the electric motor is electrically connected to the electric generator, or the hydraulic motor is connected to the hydraulic pump, respectively, wherein the proprotors provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.

First claim

What is claimed is:

1. A hybrid propulsion system for a tiltrotor craft comprising:
one or more engines disposed within a fuselage of the tiltrotor craft;
two or more electrical generators, disposed within the fuselage and connected to the one or more engines;
two rotatable nacelles, each rotatable nacelle comprising a stop-fold proprotor at a forward end of the rotatable nacelle, and each rotatable nacelle housing two or more electric motors connected to the stop-fold proprotor;
wherein each electrical generator is connected to one of the two or more electric motors in each rotatable nacelle;
wherein the stop-fold proprotors provide lift for vertical takeoff and landing and for stationary flight in a helicopter mode and thrust for forward flight in a first airplane mode, and are in a folded position during a second airplane mode; one or more ducted fans disposed within the fuselage and each connected to two or more additional electric motors disposed within the fuselage, each additional electric motor connected to one of the two or more electric generators, wherein the one or more ducted fans are powered and provide thrust for forward flight during the second airplane mode;
wherein the first airplane mode is converted to the second airplane mode by increasing power to the one or more ducted fans while decreasing power to the stop-fold proprotors to zero, and folding the stop-fold proprotors; and
wherein the second airplane mode is converted to the first airplane mode by unfolding the stop-fold proprotors, and decreasing power to the one or more ducted fans while increasing power to the stop-fold proprotors.

2. The system of claim 1 , wherein the one or more engines provide direct thrust, distributed thrust, or both.

3. The system of claim 1 , further comprising a reduction gearbox positioned between the one or more engines and the two or more electrical generators.

4. The system of claim 1 , further comprising a proprotor reduction gearbox positioned between the two or more electrical motors, and the stop-fold proprotor.

5. The system of claim 1 , wherein the stop-fold proprotors are driven directly by the two or more electrical motors.

6. The system of claim 1 , wherein the one or more engines are defined further as one or more turboshaft engines, or one or more distributed engines that are not mechanically connected to one or more ducted fans, wherein the one or more engines or the one or more distributed engines provide additional thrust during the forward flight.

7. The system of claim 1 , further comprising an electric slip ring that electrically connects the two or more electrical generators to the two or more electrical motors in each of the rotatable nacelles.

8. The system of claim 1 , wherein the two or more electrical generators comprise two or more electric redundant generators and the two or more electric motors in each rotatable nacelle comprise two or more redundant electric motors.

9. The system of claim 1 , wherein the one or more ducted fans are not powered during the helicopter mode or the first airplane mode.

10. The system of claim 1 , wherein the power to the one or more ducted fans is decreased to zero during the conversion from the second airplane mode to the first airplane mode.

11. The system of claim 1 , wherein the one or more ducted fans are positioned at least one of upstream, adjacent to, or downstream from, the one or more engines.

12. The system of claim 1 , wherein the two or more additional electric motors comprise two or more additional redundant electric motors.

13. A method of providing propulsion to a tiltrotor craft comprising:
providing one or more engines disposed within a fuselage of the tiltrotor craft;
providing one or more ducted fans disposed within the fuselage and each connected to two or more additional electric motors disposed within the fuselage, and provide a first thrust for forward flight;
providing two or more electrical generators disposed within the fuselage, each electrical generator connected to an engine of the one or more engines and one of the two or more additional electric motors;
providing two rotatable nacelles, each rotatable nacelle comprising a stop-fold proprotor at a forward end of the rotatable nacelle, wherein the stop-fold proprotors are distinct from the one or more ducted fans, and two or more electric motors connected to the stop-fold proprotor, wherein each electric motor is electrically connected to one of the two or more electric generators;
operating the tiltrotor craft in a helicopter mode or a first airplane mode by:
generating an electrical power from the two or more electrical generators;
transmitting the electrical power to the two or more electric motors in the rotatable nacelles, and
rotating the stop-fold proprotors using the two or more electrical motors in each rotatable nacelle to provide lift for vertical takeoff and landing and stationary flight in the helicopter mode, and to provide thrust for forward flight in the first airplane mode;

operating the tiltrotor craft in a second airplane mode by powering the one or more ducted fans to provide thrust for forward flight, and the stop-fold proprotors are in a folded position;
converting the tiltrotor craft from the first airplane mode to the second airplane mode by increasing power to the one or more ducted fans while decreasing power to the stop-fold proprotors to zero, and folding the stop-fold proprotors; and
converting the tiltrotor craft from the second airplane mode to the first airplane mode by unfolding the stop-fold proprotors, and decreasing power to the one or more ducted fans while increasing power to the stop-fold proprotors.

14. The method of claim 13 , wherein the one or more engines provide direct thrust, distributed thrust, or both.

15. The method of claim 13 , wherein the one or more engines comprise a turboshaft engine.

16. The method of claim 13 , further comprising positioning a reduction gearbox between the one or more engines and the two or more electrical generators.

17. The method of claim 13 , further comprising positioning a proprotor reduction gearbox between the two or more electrical motors and the stop-fold proprotor.

18. The method of claim 13 , further comprising directly driving each of the stop-fold proprotors with the two or more electrical motors.

19. The method of claim 13 , further comprising positioning an electric slip ring to electrically connect the two or more electrical generators to the two or more electrical motors in the rotatable nacelles.

20. The method of claim 13 , wherein the two or more electrical generators comprise two or more redundant electric generators and the two or more redundant electric motors in each rotatable nacelle comprise two or more redundant electrical motors.

21. The method of claim 13 , further comprising not powering the one or more ducted fans during the helicopter mode or the first airplane mode.

22. The method of claim 13 , wherein decreasing the power to the one or more ducted fans is decreased comprises decreasing the power to the one or more ducted fans to zero.

23. The method of claim 13 , wherein the two or more additional electric motors comprise two or more additional redundant electric motors.

24. A hybrid propulsion system for an aircraft comprising:
a turboshaft engine disposed within a fuselage of the aircraft that provides shaft power and distributed thrust; two or more electrical generators, di

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Fenny Carlos Alexander
• Wittmaak Jr John Robert
• Ryan Mike John
• Drennan Joseph Scott

Classifications

• B64D27/24 Primary

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D35/024

  of series type · CPC title

• B64D35/023

  of series-parallel type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title