US Patent Application 18202731. AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE simplified abstract

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AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE

Organization Name

Raytheon Technologies Corporation

Inventor(s)

Paul R. Hanrahan of Sedona AZ (US)

Michael G. Mccaffrey of Windsor CT (US)

AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE - A simplified explanation of the abstract

This abstract first appeared for US patent application 18202731 titled 'AIRCRAFT PROPULSION SYSTEM WITH VARIABLE SPEED ROTATING STRUCTURE

Simplified Explanation

The patent application describes a propulsion system that includes two propulsor rotors and a gas turbine engine core.

  • The first propulsor rotor generates propulsive thrust, while the second propulsor rotor generates propulsive lift.
  • The gas turbine engine core consists of a compressor section, a combustor section, a turbine section, and a rotating structure.
  • The rotating structure includes a turbine rotor within the turbine section.
  • In the first mode, the gas turbine engine core rotates the rotating structure at a first speed to drive the first propulsor rotor and generate propulsive thrust.
  • In the second mode, the gas turbine engine core rotates the rotating structure at a second speed to drive the second propulsor rotor and generate propulsive lift.
  • The second rotational speed is less than eighty percent of the first rotational speed.


Original Abstract Submitted

A propulsion system includes a first propulsor rotor, a second propulsor rotor and a gas turbine engine core. The first propulsor rotor is configured to generate propulsive thrust. The second propulsor rotor is configured to generate propulsive lift. 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 gas turbine engine core is configured to rotate the rotating structure at a first rotational speed during a first mode to drive the first propulsor rotor to generate the propulsive thrust. The gas turbine engine core is configured to rotate the rotating structure at a second rotational speed during a second mode to drive the second propulsor rotor to generate the propulsive lift. The second rotational speed may be less than eighty percent of the first rotational speed.

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