20240044492. DOUBLE WALL FOR AIRCRAFT GAS TURBINE COMBUSTION CHAMBER AND METHOD OF PRODUCING SAME simplified abstract (SAFRAN HELICOPTER ENGINES)

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DOUBLE WALL FOR AIRCRAFT GAS TURBINE COMBUSTION CHAMBER AND METHOD OF PRODUCING SAME

Organization Name

SAFRAN HELICOPTER ENGINES

Inventor(s)

Thomas Sébastien Alexandre Gresy of MOISSY-CRAMAYEL (FR)

Jean-Paul Didier Autret of MOISSY-CRAMAYEL (FR)

Nicolas Roland Guy Savary of MOISSY-CRAMAYEL (FR)

DOUBLE WALL FOR AIRCRAFT GAS TURBINE COMBUSTION CHAMBER AND METHOD OF PRODUCING SAME - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240044492 titled 'DOUBLE WALL FOR AIRCRAFT GAS TURBINE COMBUSTION CHAMBER AND METHOD OF PRODUCING SAME

Simplified Explanation

The abstract describes a double wall design for an aircraft gas turbine combustion chamber. The design includes an internal wall that comes into contact with the combustion reaction and an external wall that is spaced apart from the internal wall. The external wall has openings that allow cooling air streams to circulate and cool the internal wall. The internal wall does not have any perforations to prevent the circulation of cooling air towards the center of the combustion chamber. The internal wall also has projecting members that extend towards the external wall, creating calibrated cross-sectional areas through which cooling air can flow.

  • The patent application describes a double wall design for an aircraft gas turbine combustion chamber.
  • The internal wall is in contact with the combustion reaction, while the external wall is spaced apart from the internal wall.
  • The external wall has openings that allow cooling air streams to circulate and cool the internal wall.
  • The internal wall does not have any perforations to prevent cooling air from flowing towards the center of the combustion chamber.
  • The internal wall has projecting members that create calibrated cross-sectional areas through which cooling air can flow.

Potential Applications:

  • This technology can be applied in aircraft gas turbine engines to improve the cooling efficiency of the combustion chamber.
  • It can also be used in other types of combustion chambers where cooling of the internal wall is necessary.

Problems Solved:

  • The double wall design prevents the circulation of cooling air towards the center of the combustion chamber, ensuring efficient cooling of the internal wall.
  • The calibrated cross-sectional areas created by the projecting members allow controlled flow of cooling air, enhancing cooling effectiveness.

Benefits:

  • Improved cooling efficiency of the combustion chamber, leading to enhanced engine performance and durability.
  • Reduced risk of overheating and damage to the internal wall of the combustion chamber.
  • Increased safety and reliability of aircraft gas turbine engines.


Original Abstract Submitted

a double wall for an aircraft gas turbine combustion chamber comprising an internal wall which is configured to be in contact with the combustion reaction, and an external wall which is at a distance from the internal wall, comprising a plurality of openings so as to allow the circulation of cooling air streams outside the external wall, which cool the internal wall. the internal wall being free of perforations prevent any circulation of a cooling air stream towards the centre of the combustion chamber. the the internal wall comprises a plurality of members projecting towards the external wall, each projecting member comprising a foot portion and a cylindrical head portion with a circular cross-section, the head portion extending into an opening with a circular cross-section so as to define a calibrated cross-sectional area between the projecting member and the opening, through which area a cooling air stream can flow.

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