20240035419. Geared Turbine Engine with Relatively Lightweight Propulsor Module simplified abstract (RAYTHEON TECHNOLOGIES CORPORATION)

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Geared Turbine Engine with Relatively Lightweight Propulsor Module

Organization Name

RAYTHEON TECHNOLOGIES CORPORATION

Inventor(s)

Frederick M. Schwarz of Glastonbury CT (US)

Gabriel L. Suciu of Glastonbury CT (US)

Geared Turbine Engine with Relatively Lightweight Propulsor Module - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240035419 titled 'Geared Turbine Engine with Relatively Lightweight Propulsor Module

Simplified Explanation

The abstract describes a gas turbine engine with a propulsor assembly and an epicyclic gear train that provides a gear reduction ratio of greater than 2.3. The weight of the propulsor assembly is less than 40 percent of the total weight of the engine, excluding the nacelle. The engine has a first spool with a first shaft that connects a first compressor and the first turbine. The first shaft drives the propulsor through the gear train at a lower speed than the first spool. The engine also has a second spool with a second shaft connecting a second compressor and a second turbine. The weight of the propulsor is greater than the weight of the first turbine.

  • The gas turbine engine includes a propulsor assembly and an epicyclic gear train.
  • The propulsor assembly has a weight that is less than 40 percent of the total weight of the engine.
  • The gear train provides a gear reduction ratio of greater than 2.3.
  • The first spool connects a first compressor and the first turbine.
  • The first shaft of the first spool drives the propulsor through the gear train at a lower speed.
  • The second spool connects a second compressor and a second turbine.
  • The weight of the propulsor is greater than the weight of the first turbine.

Potential applications of this technology:

  • Aircraft engines
  • Power generation systems
  • Marine propulsion systems

Problems solved by this technology:

  • Improved efficiency of gas turbine engines
  • Reduction in weight of the propulsor assembly
  • Increased power output

Benefits of this technology:

  • Higher fuel efficiency
  • Reduced emissions
  • Increased power-to-weight ratio


Original Abstract Submitted

an example gas turbine engine includes a propulsor assembly consisting of a propulsor and a first turbine. an epicyclic gear train defines a gear reduction ratio of greater than 2.3. a weight of the propulsor assembly is less than 40 percent of a total weight of the gas turbine engine, excluding any nacelle. a first spool includes a first shaft that connects a first compressor and the first turbine. the first shaft drives the propulsor through the gear train to drive the propulsor at a lower speed than the first spool. a second spool includes a second shaft connecting a second compressor and a second turbine. a weight of the propulsor is greater than a weight of the first turbine.

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