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US 12,297,791 B2Granted
Additive manufacturing process of a part for an aircraft propulsion unit nacelle
AssigneesSafran Nacelles, Safran
InventorsFlavie Hubert-Choinard, Aurelie Soula, Jean-François Thouement, Sébastien Richard
Life of this patent
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Abstract
A method for additively manufacturing a part of a nacelle of an aircraft propulsion unit such as an exhaust conduit portion a step of depositing a compound including a TiAl-based powdery intermetallic alloy and consolidating the compound by sintering, without melting the compound.
Claims15
A method for manufacturing a part of a nacelle of an aircraft propulsion unit, the method comprising:
- a step of depositing, by an additive manufacturing process, a compound comprising a TiAl-based powdery intermetallic alloy to form the part having a predetermined shape such that the TiAl-based powdery intermetallic alloy is contained in the part when the part having the predetermined shape is formed;
- and
- a step of consolidating the compound by sintering after the part having the predetermined shape is formed,
- wherein the method is implemented such that the part forms a panel comprising a cellular structure constituting cavities, the method further comprising a step of disposing one or more supports in respective cavities of the cellular structure so as to support a second skin during the manufacture or during the affixation of the second skin, the supports being made of a fugitive material, wherein the supports are auxetic such that under the effect of an increase in temperature, a change in a dimension of the supports between a first skin and the second skin remains less than a predetermined value.
1 more element
A method for manufacturing a part of a nacelle of an aircraft propulsion unit, the method comprising:
- a step of depositing, by an additive manufacturing process, a compound comprising a TiAl-based powdery intermetallic alloy to form the part having a predetermined shape such that the TiAl-based powdery intermetallic alloy is contained in the part when the part having the predetermined shape is formed;
- and
- a step of consolidating the compound by sintering after the part having the predetermined shape is formed,
- wherein the method is implemented such that the part forms a panel comprising a cellular structure constituting cavities,
- the method further comprising a step of disposing one or more supports in respective cavities of the cellular structure so as to support a second skin of the panel during the manufacture or during the affixation of the second skin, the supports being made of a fugitive material so as to remove the supports during sintering,
- wherein the supports are configured to have a shape that provides an auxetic property for the supports in order to reduce a force applied to the second skin by the supports under the effect of an increase in temperature during the manufacture or the affixation of the second skin.
3 more elements
Dependencies are inferred from the claim text.