Selective power distribution for an aircraft propulsion system

Patent metadata

Field	Value
Publication number	US-12092040-B2
Application number	US-202318202727-A
Country	US
Kind code	B2
Filing date	May 26, 2023
Priority date	May 26, 2022
Publication date	Sep 17, 2024
Grant date	Sep 17, 2024

Abstract

An assembly is provided for an aircraft propulsion system. This assembly includes a sun gear, a ring gear, a plurality of intermediate gears, a carrier, a first brake and a second brake. The sun gear is rotatable about a centerline axis. The ring gear circumscribes the sun gear and is rotatable about the centerline axis. The intermediate gears are arranged circumferentially about the centerline axis. Each of the intermediate gears is meshed between the sun gear and the ring gear. The carrier is rotatable about the centerline axis. Each of the intermediate gears is rotatably mounted to the carrier. The first brake is configured to slow and/or stop rotation of the ring gear about the centerline axis. The second brake is configured to slow and/or stop rotation of the carrier about the centerline axis.

First claim

What is claimed is:

1. An assembly for an aircraft propulsion system, comprising:
a geartrain including a sun gear, a ring gear, a plurality of intermediate gears and a carrier, the sun gear rotatable about a centerline axis, the a ring gear circumscribing the sun gear and rotatable about the centerline axis, the plurality of intermediate gears arranged circumferentially about the centerline axis, each of the plurality of intermediate gears meshed between the sun gear and the ring gear, the carrier rotatable about the centerline axis, and each of the plurality of intermediate gears rotatably mounted to the carrier;
a first brake configured to at least one of slow or stop rotation of the ring gear about the centerline axis;
a second brake configured to at least one of slow or stop rotation of the carrier about the centerline axis;
a first propulsor rotor coupled to the geartrain by the ring gear, the first propulsor rotor rotatable about a first axis;
a second propulsor rotor coupled to the geartrain by the carrier, the second propulsor rotor rotatable about a second axis that is angularly offset from the first axis; and
a gas turbine engine core including a compressor section, a combustor section, a turbine section and a rotating structure, the rotating structure comprising a turbine rotor within the turbine section, the rotating structure configured to drive rotation of the first propulsor rotor through the geartrain and using the ring gear, and the rotating structure configured to drive rotation of the second propulsor rotor through the geartrain and using the carrier.

2. The assembly of claim 1 , wherein during a star system mode
the second brake is configured to stop rotation of the carrier about the centerline axis;
the sun gear is configured to rotate about the centerline axis; and
the ring gear is configured to rotate about the centerline axis.

3. The assembly of claim 2 , wherein the first brake is disengaged during the star system mode.

4. The assembly of claim 1 , wherein during a planetary system mode
the first brake is configured to stop rotation of the ring gear about the centerline axis;
the sun gear is configured to rotate about the centerline axis; and
the carrier is configured to rotate about the centerline axis.

5. The assembly of claim 4 , wherein the second brake is disengaged during the planetary system mode.

6. The assembly of claim 1 , wherein during an open system mode
the first brake and the second brake are disengaged;
the sun gear is configured to rotate about the centerline axis;
the ring gear is configured to rotate about the centerline axis; and
the carrier is configured to rotate about the centerline axis.

7. 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.

8. The assembly of claim 1 , wherein
the gas turbine engine core further includes a second rotating structure; and
the second rotating structure includes a compressor rotor within the compressor section and a second turbine rotor within the turbine section.

9. An assembly for an aircraft propulsion system, comprising:
a geartrain including a sun gear, a ring gear, a plurality of intermediate gears and a carrier, the sun gear rotatable about a centerline axis, the a ring gear circumscribing the sun gear and rotatable about the centerline axis, the plurality of intermediate gears arranged circumferentially about the centerline axis, each of the plurality of intermediate gears meshed between the sun gear and the ring gear, the carrier rotatable about the centerline axis, and each of the plurality of intermediate gears rotatably mounted to the carrier;
a first brake configured to at least one of slow or stop rotation of the ring gear about the centerline axis;
a second brake configured to at least one of slow or stop rotation of the carrier about the centerline axis;
a propulsor rotor coupled to the geartrain by the ring gear; and
a gas turbine engine core including a compressor section, a combustor section, a turbine section and a rotating structure, the rotating structure comprising a turbine rotor within the turbine section, the rotating structure configured to drive rotation of the propulsor rotor through the geartrain and using the ring gear.

10. The assembly of claim 9 , wherein the propulsor rotor comprises a ducted rotor.

11. The assembly of claim 1 , further comprising a propulsor rotor coupled to and configured to be rotatably driven by the carrier.

12. The assembly of claim 11 , wherein the propulsor rotor comprises an open rotor.

13. An assembly for an aircraft propulsion system, comprising:
a powertrain comprising an epicyclic geartrain, an input, a first output and a second output;
the epicyclic geartrain operable as a star geartrain in a star system mode of operation, and the epicyclic geartrain operable as a planetary geartrain in a planetary system mode of operation;
the epicyclic geartrain configured to transfer power from the input to the first output during the star system mode of operation, wherein the epicyclic geartrain does not transfer power from the input to the second output during the star system mode of operation; and
the epicyclic geartrain configured to transfer power from the input to the second output during the planetary system mode of operation, wherein the epicyclic geartrain does not transfer power from the input to the first output during the planetary system mode of operation.

14. The assembly of claim 13 , wherein the epicyclic geartrain includes
a sun gear rotatable about a centerline axis, the sun gear coupled to the input;
a ring gear circumscribing the sun gear and rotatable about the centerline axis, the ring gear coupled to the first output;
a plurality of intermediate gears arranged circumferentially about the centerline axis, each of the plurality of intermediate gears meshed between the sun gear and the ring gear; and
a carrier rotatable about the centerline axis, each of the plurality of intermediate gears rotatably mounted to the carrier, and the carrier coupled to the second output.

15. The assembly of claim 13 , further comprising:
a first brake configured to stop rotation of the first output during the planetary system mode of operation; and
a second brake configured to stop rotation of the second output during the star system mode of operation.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Hanrahan Paul R

Classifications

• F05D2260/90

  Braking · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• B64D35/00

  Transmitting power from power plants to propellers or rotors; Arrangements of transmissions · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• B64C27/32

  Rotors · CPC title