Aircraft propulsion system geartrain

Patent metadata

Field	Value
Publication number	US-12378000-B2
Application number	US-202318233620-A
Country	US
Kind code	B2
Filing date	Aug 14, 2023
Priority date	Aug 12, 2022
Publication date	Aug 5, 2025
Grant date	Aug 5, 2025

Abstract

An assembly is provided for an aircraft. This assembly includes a geartrain, a first propulsor rotor and a rotating structure. The geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The ring gear circumscribes the sun gear and is rotatable about an axis. Each of the intermediate gears is between and meshed with the sun gear and the ring gear. Each of the intermediate gears is rotatably mounted to the carrier. The carrier is rotatable about the axis. The first propulsor rotor is coupled to the carrier. The rotating structure is coupled to the ring gear. The rotating structure includes a turbine rotor. The rotating structure is configured to drive rotation of the first propulsor rotor through the geartrain.

First claim

What is claimed is:

1. An assembly for an aircraft, comprising:
a geartrain comprising a sun gear, a ring gear, a plurality of intermediate gears and a carrier, the ring gear circumscribing the sun gear and rotatable about an axis, each of the plurality of intermediate gears between and meshed with the sun gear and the ring gear, each of the plurality of intermediate gears rotatably mounted to the carrier, and the carrier rotatable about the axis;
a first propulsor rotor coupled to the carrier;
a second propulsor rotor coupled to the sun gear; and
a rotating structure coupled to the ring gear, the rotating structure comprising a turbine rotor, the rotating structure configured to drive rotation of the first propulsor rotor through the geartrain, and the rotating structure configured to drive rotation of the second propulsor rotor through the geartrain;
wherein the sun gear is rotatable about the axis.

2. The assembly of claim 1 , further comprising a lock device configured to lock rotation of the carrier about the axis.

3. The assembly of claim 2 , wherein the lock device comprises a splined coupling.

4. The assembly of claim 1 , further comprising a brake configured to brake rotation of the carrier about the axis.

5. The assembly of claim 4 , wherein the brake comprises a disk brake.

6. The assembly of claim 1 , further comprising a lock device configured to lock rotation of the sun gear about the axis.

7. The assembly of claim 6 , wherein the lock device comprises a splined coupling.

8. The assembly of claim 1 , further comprising a brake configured to brake rotation of the sun gear about the axis.

9. The assembly of claim 8 , wherein the brake comprises a disk brake.

10. The assembly of claim 1 , wherein
the first propulsor rotor is rotatable about a first rotor axis; and
the second propulsor rotor is rotatable about a second rotor axis that is angularly offset from the first rotor axis.

11. The assembly of claim 10 , wherein the first rotor axis is coaxial with the axis.

12. The assembly of claim 1 , wherein
the first propulsor rotor is configured to generate propulsive force in a first direction; and
the second propulsor rotor is configured to generate propulsive force in a second direction that is different than the first direction.

13. The assembly of claim 1 , wherein at least one of
the first propulsor rotor comprises a ducted rotor; or
the second propulsor rotor comprises an open rotor.

14. The assembly of claim 1 , further comprising:
a gas turbine engine core including a compressor section, a combustor section, a turbine section and the rotating structure; and
the turbine rotor within the turbine section.

15. The assembly of claim 1 , wherein the second propulsor rotor comprises an open rotor.

16. The assembly of claim 1 , wherein the first propulsor rotor comprises a ducted rotor and the second propulsor rotor comprises an open rotor.

17. An assembly for an aircraft, comprising:
a geartrain comprising a sun gear, a ring gear, a plurality of intermediate gears and a carrier, the sun gear rotatable about an axis, the ring gear circumscribing the sun gear and rotatable about the axis, each of the plurality of intermediate gears between and meshed with the sun gear and the ring gear, each of the plurality of intermediate gears rotatably mounted to the carrier, and the carrier rotatable about the axis;
a first propulsor rotor coupled to the carrier;
a second propulsor rotor coupled to the sun gear;
a power output coupled to the carrier or the sun gear; and
a power input coupled to the ring gear, the power input configured to drive rotation of the power output through the geartrain.

18. The assembly of claim 17 , wherein the first propulsor rotor comprises a ducted rotor and the second propulsor rotor comprises an open rotor.

Assignees

• Rtx Corp

Inventors

• Hanrahan Paul R
• Mylrea Benjamin T
• Stachowiak David A

Classifications

• F05D2260/902

  using frictional mechanical forces · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• B64D35/04

  characterised by the transmission driving a plurality of propellers or rotors · CPC title