Mechanically-distributed propulsion drivetrain and architecture

Patent metadata

Field	Value
Publication number	US-11142330-B2
Application number	US-201816117305-A
Country	US
Kind code	B2
Filing date	Aug 30, 2018
Priority date	Aug 30, 2018
Publication date	Oct 12, 2021
Grant date	Oct 12, 2021

Abstract

An aircraft with an integrated boundary layer ingesting propulsion having a mechanically-distributed propulsion system. The mechanically-distributed propulsion system may include an engine to generate a mechanical drive power, a drive shaft, a direction-reversing transmission, and a propulsor fan. The drive shaft may be operatively coupled to the engine to receive the mechanical drive power. The direction-reversing transmission may have a first rotating shaft and a second rotating shaft, the first rotating shaft operatively coupled to the drive shaft to receive the mechanical drive power, which is configured to redirect the mechanical drive power received at the first rotating shaft from a first direction to face a second direction at the second rotating shaft. The propulsor fan may be coupled to the second rotating shaft to convert the mechanical drive power into thrust.

First claim

What is claimed is:

1. A mechanically-distributed propulsion system for use in an aircraft, the mechanically-distributed propulsion system comprising:
an engine to generate a mechanical drive power wherein the engine is configured to expel exhaust forward;
a drive shaft operatively coupled to the engine to receive the mechanical drive power;
a direction-reversing transmission having a first rotating shaft and a second rotating shaft, the first rotating shaft operatively coupled to the drive shaft to receive the mechanical drive power,
wherein the direction-reversing transmission is configured to redirect the mechanical drive power received at the first rotating shaft from a first direction to face a second direction at the second rotating shaft; and
a propulsor fan coupled to the second rotating shaft to convert the mechanical drive power into thrust.

2. The mechanically-distributed propulsion system of claim 1 , wherein the direction-reversing transmission comprises a first angled drive assembly to turn a path of the mechanical drive power by a first angle, and a second angled drive assembly to turn the path of the mechanical drive power by a second angle.

3. The mechanically-distributed propulsion system of claim 2 , wherein each of the first angle and the second angle are equal.

4. The mechanically-distributed propulsion system of claim 2 , wherein the first angled drive assembly and the second angled drive assembly are mechanically coupled to one another via a linear drive shaft assembly.

5. The mechanically-distributed propulsion system of claim 2 , wherein the first angled drive assembly comprises the first rotating shaft having a first axis of rotation and a third rotating shaft having a third axis of rotation, the first rotating shaft and the third rotating shaft being mechanically coupled to one another via a first set of bevel gears, wherein the first axis of rotation and the third axis of rotation are positioned relative to one another at the first angle.

6. The mechanically-distributed propulsion system of claim 5 , wherein the second angled drive assembly comprises the second rotating shaft having a second axis of rotation and a fourth rotating shaft having a fourth axis of rotation, the second rotating shaft and the fourth rotating shaft being mechanically coupled to one another via a second set of bevel gears, wherein the second axis of rotation and the fourth axis of rotation are positioned relative to one another at the second angle.

7. The mechanically-distributed propulsion system of claim 6 , wherein the third rotating shaft and the fourth rotating shaft are mechanically coupled to one another via a sliding spline coupling.

8. The mechanically-distributed propulsion system of claim 1 , wherein the direction-reversing transmission includes a conduit manifold and a plurality of fluid conduits to supply lubricant to the direction-reversing transmission.

9. The mechanically-distributed propulsion system of claim 1 , wherein the engine is coupled to a rear-facing engine exhaust duct to redirect the exhaust aft.

10. An aerial vehicle comprising:
a fuselage having a forward end and an aft end;
a wing set operatively coupled to said fuselage;
an empennage at the aft end of said fuselage, the empennage having a plurality of flight control surfaces;
a propulsor fan integrated at the aft end of said fuselage, the aft end of said fuselage being shaped with a geometry to direct a boundary layer flowing over the fuselage to the propulsor fan;
an engine positioned within the fuselage to generate a mechanical drive power wherein the engine is configured to expel exhaust toward the forward end; and
a direction-reversing transmission to receive the mechanical drive power from the engine and to redirect the mechanical drive power from a first direction to face a second direction.

11. The aerial vehicle of claim 10 , wherein the propulsor fan is positioned to ingest a boundary layer flowing over the fuselage.

12. The aerial vehicle of claim 11 , wherein the propulsor fan is blended with the fuselage.

13. The aerial vehicle of claim 11 , wherein the propulsor fan is blended with the fuselage via a set of integral nacelle cowling diffusers defined by the fuselage.

14. The aerial vehicle of claim 11 , wherein the propulsor fan is integrated with an aft-fuselage subassembly of the fuselage.

15. The aerial vehicle of claim 11 , wherein the fuselage includes a center fuselage subassembly having a double-bubble cross-section.

16. The aerial vehicle of claim 14 , wherein the aft-fuselage subassembly is fabricated as a semi-monocoque structure having a plurality of fuselage-skin pieces fastened to an internal structure.

17. The aerial vehicle of claim 10 , wherein the first direction is from the forward end and the second direction is toward the forward end.

18. The aerial vehicle of claim 10 , wherein the fuselage includes a center fuselage subassembly having a double-bubble cross-section.

19. The aerial vehicle of claim 10 , further comprising a rear-facing engine exhaust duct to redirect the exhaust from the engine toward the aft end.

20. A method of operating an aircraft having a mechanically-distributed propulsion system, the method comprising:
generating a mechanical drive power using an engine, wherein the engine is configured to expel exhaust toward a forward end of the aircraft;
receiving the mechanical drive power from the engine via a drive shaft;
receiving the mechanical drive power from the drive shaft via a direction-reversing transmission, wherein the direction-reversing transmission comprises a first rotating shaft and a second rotating shaft, the first rotating shaft being operatively coupled to the drive shaft;
redirecting the exhaust toward an aft end of the aircraft using a rear-facing engine exhaust;
redirecting the mechanical drive power received at the first rotating shaft from a first direction to face a second direction at the second rotating shaft; and
rotating a propulsor fan to convert the mechanical drive power into thrust, wherein the propulsor fan is operatively coupled to the second rotating shaft.

Assignees

• Aurora Flight Sciences Corp

Inventors

• Papas Gary Richard
• Titchener Neil
• Yutko Brian M
• Church Clint
• Tian Jian Long

Classifications

• Y02T50/10

  Drag reduction · CPC title

• B64D27/14 Primary

  within, or attached to, fuselages · CPC title

• F05D2250/313

  the axes being perpendicular to each other · CPC title

• B64D27/20

  within, or attached to, fuselages · CPC title

• F05D2260/532

  of the bevelled or angled type · CPC title