Method for manufacturing an air intake structure for a turbojet engine nacelle
A method for manufacturing an air-intake structure for a turbojet-engine nacelle includes two component parts, i.e. one air-intake lip structure and one outer cowl for the air-intake structure. In particular, the method includes the following steps: separately manufacturing the component parts such that each integrates one overlapping portion with a part to which is to be attached. The overlapping portion is configured such that an outer surface of the outer overlapping portion provides continuity with an outer surface of the outer cowl associated with the inner overlapping portion. To secure the overlapping portions, glue or a fastener may be used.
1. A method for manufacturing an air intake structure for a turbojet engine nacelle comprising at least one air intake lip structure and at least one air intake structure outer cowl, the method comprising:
making at least one overlapping portion of said at least one air intake lip structure and another overlapping portion of said at least one air intake structure outer cowl separately in the nacelle, said overlapping portion of said at least one air intake lip structure being attached over said overlapping portion of said at least one air intake structure outer cowl such that an outer surface of said at least one overlapping portion of said at least one air intake lip structure provides a continuous outer mold line with an outer surface of said at least one air intake structure outer cowl; and
securing said overlapping portions by at least one of gluing and fastening means.
2. The method according to claim 1 , wherein the securing is done by overmolding the overlapping portions.
3. The method according to claim 1 , wherein the overlapping portion of said at least one air intake structure outer cowl is substantially longitudinal and at least partially peripheral.
4. The method according to claim 3 , wherein the overlapping portion of said at least one air intake lip structure is substantially longitudinal and completely peripheral.
5. The method according to claim 1 , wherein a part forming said at least one air intake lip structure is a single piece.
6. The method according to claim 1 , wherein a part making up said at least one air intake structure outer cowl is a single piece.
7. The method according to claim 6 , wherein said at least one air intake structure outer cowl forms a drum.
8. The method according to claim 6 , wherein the outer cowl forms a shroud open.
9. The method according to claim 1 , wherein a part making up said at least one air intake structure outer cowl is made from two half-parts, configured to be clipped to each other.