20240017839. AIRCRAFT FLUID ICE PROTECTION SYSTEM simplified abstract (The Boeing Company)

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AIRCRAFT FLUID ICE PROTECTION SYSTEM

Organization Name

The Boeing Company

Inventor(s)

Charles William Rust of Seattle WA (US)

AIRCRAFT FLUID ICE PROTECTION SYSTEM - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240017839 titled 'AIRCRAFT FLUID ICE PROTECTION SYSTEM

Simplified Explanation

The abstract describes a fluid ice protection system for an aircraft. Here is a simplified explanation of the patent application:

  • The system includes a plenum back wall and a fluid delivery network.
  • The plenum back wall is attached to the interior surface of an inlet cowl of the aircraft's nacelle.
  • This creates a plenum between the interior surface and the front surface of the plenum back wall.
  • The nacelle surrounds the rotor assembly of the aircraft's propulsion system.
  • The inlet cowl has perforations throughout its thickness.
  • These perforations are connected to the plenum, allowing fluid to flow through.
  • The fluid delivery network is connected to the plenum back wall and is designed to supply an anti-ice liquid into the plenum.
  • The purpose of the anti-ice liquid is to penetrate through the perforations and onto the exterior surface of the inlet cowl's leading edge section.

Potential applications of this technology:

  • Aircraft ice protection systems
  • Improving safety and performance of aircraft in icy conditions

Problems solved by this technology:

  • Preventing ice formation on the leading edge section of the inlet cowl
  • Ensuring proper functioning of the aircraft's propulsion system in icy conditions

Benefits of this technology:

  • Enhanced safety by reducing the risk of ice accumulation on critical aircraft components
  • Improved performance and efficiency of the aircraft's propulsion system in icy conditions


Original Abstract Submitted

a fluid ice protection system for an aircraft includes a plenum back wall and a fluid delivery network. the plenum back wall is affixed to an interior surface of an inlet cowl of a nacelle of the aircraft to define a plenum between the interior surface and a front surface of the plenum back wall. the nacelle surrounds a rotor assembly of an aircraft propulsion system. the inlet cowl defines a plurality of perforations through a thickness of the inlet cowl. the perforations are fluidly connected to the plenum. the fluid delivery network is coupled to the plenum back wall and configured to supply an anti-ice liquid into the plenum for the anti-ice liquid to penetrate through the perforations onto an exterior surface of the inlet cowl along a leading edge section of the inlet cowl.

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