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