US Patent Application 18202733. AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR simplified abstract

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AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR

Organization Name

Raytheon Technologies Corporation

Inventor(s)

Paul R. Hanrahan of Sedona AZ (US)

AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR - A simplified explanation of the abstract

This abstract first appeared for US patent application 18202733 titled 'AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR

Simplified Explanation

The patent application describes a propulsion system for an aircraft, consisting of a gas turbine engine core, a first propulsor rotor, and a second propulsor rotor.

  • Gas turbine engine core includes compressor, combustor, turbine sections, and a rotating structure with a turbine rotor.
  • The first propulsor rotor is driven by the rotating structure in two modes.
  • The first propulsor rotor has variable pitch blades, including a blade that can pivot between a thrust position and an idle position.
  • The first blade is in the thrust position during the first mode and in the idle position during the second mode.
  • The second propulsor rotor is driven by the rotating structure only during the second mode.


Original Abstract Submitted

A propulsion system is provided for an aircraft. This aircraft propulsion system includes a gas turbine engine core, a first propulsor rotor and a second propulsor rotor. The gas turbine engine core includes a compressor section, a combustor section, a turbine section and a rotating structure. The rotating structure includes a turbine rotor within the turbine section. The first propulsor rotor is rotatably driven by the rotating structure during a first mode and a second mode. The first propulsor rotor includes a plurality of variable pitch blades. The variable pitch blades include a first blade configured to pivot between a thrust position and an idle position. The first blade is in the thrust position during the first mode. The first blade is in the idle position during the second mode. The second propulsor rotor is rotatably driven by the rotating structure during the second mode.

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