20240018902. SUPERSONIC AIR INLET OF AN AIRCRAFT PROPELLING ASSEMBLY COMPRISING A SUPPORT ARM DE-ICING DEVICE AND DE-ICING METHOD simplified abstract (SAFRAN NACELLES)

SUPERSONIC AIR INLET OF AN AIRCRAFT PROPELLING ASSEMBLY COMPRISING A SUPPORT ARM DE-ICING DEVICE AND DE-ICING METHOD

Organization Name

SAFRAN NACELLES

Inventor(s)

Jean-Philippe Joret of Moissy-Cramayel (FR)

Hazem Kioua of Moissy-Cramayel (FR)

Emmanuel Lesteven of Moissy-Cramayel (FR)

SUPERSONIC AIR INLET OF AN AIRCRAFT PROPELLING ASSEMBLY COMPRISING A SUPPORT ARM DE-ICING DEVICE AND DE-ICING METHOD - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240018902 titled 'SUPERSONIC AIR INLET OF AN AIRCRAFT PROPELLING ASSEMBLY COMPRISING A SUPPORT ARM DE-ICING DEVICE AND DE-ICING METHOD

Simplified Explanation

The abstract describes a supersonic air intake for an aircraft propulsion assembly. Here is a simplified explanation of the patent application:

• The supersonic air intake consists of a pipe that guides the flow of air into the turbine engine of an aircraft.
• Inside the pipe, there is a speed reducer fixedly mounted along the longitudinal axis.
• At least one support arm links the speed reducer to the pipe, creating a cavity between the upstream and downstream outer walls of the arm.
• An inner wall of a de-icing device is mounted in the cavity opposite the upstream outer wall, creating a calibrated de-icing space.
• The supersonic air intake also includes a member for supplying and a member for discharging a de-icing air flow into the de-icing space.

Potential applications of this technology:

• This supersonic air intake design can be used in aircraft propulsion systems to improve the efficiency and performance of the turbine engine.
• It can be applied to both military and commercial aircraft to enhance their overall capabilities.

Problems solved by this technology:

• The supersonic air intake helps prevent ice formation on the outer walls of the support arm, which could disrupt the airflow and potentially damage the engine.
• By providing a de-icing space, the technology ensures that the air entering the engine remains free from ice or other contaminants, optimizing engine performance.

Benefits of this technology:

• Improved engine efficiency and performance due to the optimized airflow provided by the supersonic air intake.
• Enhanced safety by preventing ice formation and maintaining clean air intake, reducing the risk of engine malfunctions.
• Potential fuel savings and reduced maintenance costs resulting from the improved efficiency and reliability of the engine.

Potential Applications

• Aircraft propulsion systems
• Military aircraft
• Commercial aircraft

Problems Solved

• Prevention of ice formation on outer walls of the support arm
• Ensuring clean air intake to optimize engine performance

Benefits

• Improved engine efficiency and performance
• Enhanced safety
• Potential fuel savings
• Reduced maintenance costs

Original Abstract Submitted

a supersonic air intake of an aircraft propulsion assembly comprises: a pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, a speed reducer fixedly mounted inside the pipe along the longitudinal axis, at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.