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US 10,737,343 B2Granted
Method for producing an especially large aeronautical part
AssigneeSafran Nacelles
InventorsPhilippe Bienvenu, Helene Malot, Charlotte Julienne
Life of this patent
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Abstract
The present disclosure relates to a method for producing a final metal part for a nacelle of a turbojet. The method includes brazing at least two parts, one being an inner part having an inner surface and the other being an outer part having an outer surface. The method further includes a step of heating the outer surface of the outer part using an external heating means, and a step of heating the inner surface of the inner part using an internal heating means.
Claims9
A method for manufacturing an acoustic structure of a turbojet engine nacelle, the method comprising:
- brazing an inner acoustically reflective skin and an outer acoustically transparent skin to a honeycomb structure, the inner acoustically reflective skin and an outer acoustically transparent skin each comprising an inner surface and an outer surface;
- heating the outer acoustically transparent skin by an outer network of heater resistors;
- and
- heating an inner tool spaced a distance from the inner acoustically reflective skin by an inner network of heating resistors, the heated inner tool heating the inner acoustically reflective skin.
1 more element
Dependencies are inferred from the claim text.