Selective power distribution for an aircraft propulsion system

Patent metadata

Field	Value
Publication number	US-2023383700-A1
Application number	US-202318202727-A
Country	US
Kind code	A1
Filing date	May 26, 2023
Priority date	May 26, 2022
Publication date	Nov 30, 2023
Grant date	—

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 sun gear rotatable about a centerline axis; a ring gear circumscribing the sun gear and rotatable about the centerline axis; 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; a carrier rotatable about the centerline axis, 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; and a second brake configured to at least one of slow or stop rotation of the carrier about the centerline axis.

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 , further comprising:
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; and the rotating structure coupled to and configured to rotatably drive the sun gear about the centerline axis.

8 . The assembly of claim 7 , further comprising:
a first propulsor rotor coupled to and configured to be rotatably driven by the ring gear; and a second propulsor rotor coupled to and configured to be rotatably driven by the carrier.

9 . The assembly of claim 8 , wherein
the first propulsor rotor is rotatable about a first axis; and the second propulsor rotor is rotatable about a second axis that is angularly offset from the first axis.

10 . The assembly of claim 8 , 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.

11 . The assembly of claim 7 , 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.

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

13 . The assembly of claim 12 , wherein the propulsor rotor comprises a ducted rotor.

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

15 . The assembly of claim 14 , wherein the propulsor rotor comprises an open rotor.

16 . 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 in a star system mode and a planetary system mode; the epicyclic geartrain configured to transfer power from the input to the first output during the star system mode; and the epicyclic geartrain configured to transfer power from the input to the second output during the planetary system mode.

17 . The assembly of claim 16 , wherein at least one of
the epicyclic geartrain does not transfer power from the input to the second output during the star system mode; or the epicyclic geartrain does not transfer power from the input to the first output during the planetary system mode.

18 . The assembly of claim 16 , 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.

19 . The assembly of claim 16 , further comprising:
a first brake configured to stop rotation of the first output during the planetary system mode; and a second brake configured to stop rotation of the second output during the star system mode.

20 . An assembly for an aircraft propulsion system, comprising:
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; a first propulsor rotor; a second propulsor rotor; a powertrain configured to transfer power from the rotating structure to the first propulsor rotor during a first mode, and the powertrain configured to transfer power from the rotating structure to the second propulsor rotor during a second mode; a first brake engaged during the second mode and disengaged during the first mode; and a second brake engaged during the first mode and disengaged during the second mode.

Assignees

• Raytheon Tech Corp

Inventors

• Hanrahan Paul R

Classifications

• F02C7/36 Primary

  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

• B64D27/10

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

• B64C27/32

  Rotors · CPC title

• B64D35/00

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

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title