17835280. AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE simplified abstract (General Electric Company)

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AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE

Organization Name

General Electric Company

Inventor(s)

Keith Edward James Blodgett of Milford OH (US)

William J. Bowden of Cleves OH (US)

Egbert Geertsema of Cincinnati OH (US)

AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE - A simplified explanation of the abstract

This abstract first appeared for US patent application 17835280 titled 'AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE

Simplified Explanation

The abstract describes an aircraft with a fuselage and an unducted turbine engine. The fuselage has a divot with an upstream edge and a downstream edge, defined by a straight reference line with a length (L) and a maximum depth (h) relative to the reference line. The unducted turbine engine consists of an engine core, a nacelle, and a set of blades. The first flow ratio (FR1) is calculated as h/L.

  • The aircraft has a unique design with a divot in the fuselage.
  • The divot is defined by a straight reference line and has a specific length and depth.
  • The unducted turbine engine is a key component of the aircraft.
  • The first flow ratio is calculated based on the divot dimensions.

Potential applications of this technology:

  • This aircraft design could be used in commercial aviation, military aircraft, or private jets.
  • It may be suitable for both short-haul and long-haul flights.
  • The unique design could offer improved aerodynamics and fuel efficiency.

Problems solved by this technology:

  • The divot in the fuselage may help reduce drag and improve overall aircraft performance.
  • The specific dimensions of the divot could optimize airflow around the aircraft.

Benefits of this technology:

  • Improved aerodynamics could result in reduced fuel consumption and lower operating costs.
  • The unique design may enhance the aircraft's speed and maneuverability.
  • The divot could potentially contribute to a quieter flight experience for passengers.


Original Abstract Submitted

An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h/L.

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