US Patent Application 18202727. SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract

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SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM

Organization Name

Raytheon Technologies Corporation

Inventor(s)

Paul R. Hanrahan of Sedona AZ (US)

SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM - A simplified explanation of the abstract

This abstract first appeared for US patent application 18202727 titled 'SELECTIVE POWER DISTRIBUTION FOR AN AIRCRAFT PROPULSION SYSTEM

Simplified Explanation

The patent application describes an assembly for an aircraft propulsion system.

  • The 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 can rotate around a centerline axis.
  • The ring gear surrounds the sun gear and can also rotate around the centerline axis.
  • The intermediate gears are positioned around the centerline axis and are meshed between the sun gear and the ring gear.
  • The carrier can rotate around the centerline axis and each intermediate gear is mounted to the carrier.
  • The first brake is designed to slow down or stop the rotation of the ring gear around the centerline axis.
  • The second brake is designed to slow down or stop the rotation of the carrier around the centerline axis.


Original Abstract Submitted

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.

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