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Structural and/or acoustic panel comprising a u-shaped sealing flange orientated into the panel, and method for manufacturing such

A technology for sealing flanges and panels, applied in the direction of manufacturing tools, engine manufacturing, sound-producing instruments, etc., can solve the problems of complicated assembly of panels and another structure, etc.

Pending Publication Date: 2022-05-13
SAFRAN NASEL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] Given the geometry of such sealing flanges, the lateral boundaries of the panel include hollows that complicate the assembly of this panel with another structure

Method used

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  • Structural and/or acoustic panel comprising a u-shaped sealing flange orientated into the panel, and method for manufacturing such
  • Structural and/or acoustic panel comprising a u-shaped sealing flange orientated into the panel, and method for manufacturing such
  • Structural and/or acoustic panel comprising a u-shaped sealing flange orientated into the panel, and method for manufacturing such

Examples

Experimental program
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Embodiment Construction

[0076] exist figure 1 In , an aircraft propulsion assembly 1 comprising a turbine engine 2 rectified by a nacelle 3 is shown. In this example, the turbine engine 2 is a two-body and two-flow jet engine.

[0077] In the following, the terms "upstream", "downstream", "front" and "rear" are defined with respect to the direction D1 of gas flow through the propulsion assembly 1 when the propulsion assembly is propelled.

[0078] The jet engine 2 has a longitudinal central axis A1 around which the various components of the jet engine extend, in this case from upstream to downstream of the jet engine 2 the fans 4, the low pressure compressor 5, the high pressure compressor engine 6, combustion chamber 7, high pressure turbine 8 and low pressure turbine 9. The compressors 5 and 6, the combustion chamber 7 and the turbines 8 and 9 form a gas generator.

[0079] Normally, during operation of such a jet engine 2 , an airflow 10 enters the propulsion assembly 1 through an air inlet 11...

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PUM

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Abstract

The invention relates to a structural and / or acoustic panel (30) comprising an inner skin (31), an outer skin (32), a honeycomb structure (33) and at least one sealing flange (40). The sealing flange (40) has a U-shaped cross-section oriented towards the honeycomb structure (33) and is clamped with the honeycomb structure (33) between the inner skin (31) and the outer skin (32). The invention also relates to a method for producing such a panel by welding the constituent elements of the panel.

Description

technical field [0001] The invention relates to the field of manufacture of structural and / or acoustic panels of the type comprising two skins and a honeycomb structure enclosed between these skins. In particular, the invention relates to the field of aviation, and more particularly to an aircraft propulsion assembly component comprising at least one such panel. Background technique [0002] Aircraft propulsion assemblies comprise a plurality of structural panels commonly referred to as "sandwich panels", formed essentially of two skins and a honeycomb structure enclosed between these skins. Such panels are used, for example, to form all or part of jet jet nozzles or internal fixed structures of the nacelle forming the propulsion assembly. [0003] The honeycomb structure of the panels generally includes transverse partitions connecting the skins and thus contributing to the structural strength of the panels. The transverse partitions delimit pockets, ie spaces free of mat...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/045F02K1/82B23K1/00
CPCF02C7/045F02K1/827B23K1/0008B23K1/0014F05D2250/283F05D2260/96F05D2230/237F05D2250/75F05D2260/963G10K11/172Y02T50/60
Inventor 托尼·迈奥斯克菲利普·比安弗尼埃米莉·贝蒙特
Owner SAFRAN NASEL