摘要：
A method and apparatus for manufacturing an aircraft component by performing an additive manufacturing process to form an initial object 4 comprising an inner tube 42 inside an outer tube 40 attached together only at respective ends 44, 46, the inner and outer tube being spaced apart as to form a chamber (50, fig 4) having a chamber opening 52; establishing within the chamber a predetermined environment and thereafter sealing the chamber opening to maintain the established environment. Preferably, the aircraft component is a pipe and fluid is permitted to flow through the inner tube. The step of establishing a predetermined environment may comprise evacuating the chamber to form a vacuum (or partial vacuum); or at least partially filling the chamber with a material having low thermal conductivity (e.g. thermosetting foam or a fluid) such as to form an insulated pipe. The additive manufacturing process may be a powder bed fusion process. The pipe may be non-straight or bent. The chamber opening may be a capillary tube.
权利要求：
CLAIMS
1. A method of manufacturing an aircraft component (54), the method comprising:
performing, by Additive Manufacturing apparatus (2), an Additive Manufacturing process to form an initial object (4), the initial object (4) comprising:
an inner tube (42) comprising a first end, a second end opposite to
the first end, and a first intermediate portion between the first end and
the second end:
an outer tube (40) comprising a third end, a fourth end opposite to
the third end, and a second intermediate portion between the third end
and the fourth end: wherein
the inner tube (42) is inside the outer tube (40);
the inner tube (42) and the outer tube (40) are attached together
in such a way that only the first end and the third end are attached
together and the second end and the fourth end are attached together,
and such that the first intermediate portion and the second intermediate
portion are spaced apart and not directly connected together; and
there is a chamber (50) between the first intermediate portion and
the second intermediate portion, the chamber (50) having a chamber
opening (52);
establishing, within the chamber (50), via the chamber opening (52), a predetermined environment; and
thereafter, sealing the chamber opening (52) so as to maintain, within the chamber (50), the established environment, thereby producing the aircraft component (54).
2. A method according to claim 1, wherein
the initial object (4) further comprises a first annular portion (44) and a second annular portion (46);
the first annular portion (44) connects together the first end and the third end;
the second annular portion (46) connects together the second end and the fourth end; and
the inner tube (42) and the outer tube (40) are connected together only by the first annular portion (44) and the second annular portion (46).
3. A method according to claim 1 or 2, wherein the aircraft component (54) is a pipe, and a fluid is permitted to flow through the inner tube (42).
4. A method according to claim 3, wherein the pipe is non-straight.
dS. A method according to any of claims 1 to 4, wherein the initial object (4) further comprises at least one further inner tube, each further inner tube being attached to the outer tube (40) such that at least part of that further inner tube is inside at least part of the outer tube (40) and such that the chamber (50) is between the outer tube (40) and the at least part of that further inner tube that is inside the outer tube (40).
6. A method according to claim 5, wherein:
each further inner tube comprises respective opposite ends and an intermediate portion between those ends; and
for each further inner tube, only the ends of that further inner tube are attached to the outer tube (40) such that the intermediate portions of the further inner tubes are not directly connected to the second intermediate portion.
I A method according to any of claims 1 to 6, wherein:
the step of establishing comprises at least partially evacuating the chamber (50); and
the step of sealing is performed such that the chamber (50) is airtight.
8. A method according to claim 7, wherein the step of evacuating the chamber (50) is performed such that the chamber (50) is fully evacuated.
9. A method according to any of claims 1 to 6, wherein:
the step of establishing comprises at least partially filling the chamber (50) with an amount of material; and
the step of sealing is performed such that movement of the material from the chamber (50) is prevented.
10. A method according to claim 9, wherein the material has a low thermal conductivity.
11. A method according to any of claims 1 to 10, wherein the Additive Manufacturing process is a powder bed fusion process.
12. A method according to any of claims 1 to 11, wherein the chamber opening (52) is a capillary tube having a relatively small cross section.
13. An aircraft component (54) manufactured using a method according to any of claims 1 to 12.
14. Apparatus for manufacturing an aircraft component (54), the apparatus comprising:
Additive Manufacturing apparatus (2) configured to perform an Additive Manufacturing process to form an initial object (4), the initial object (4) comprising:
an inner tube (42) comprising a first end, a second end opposite to
the first end, and a first intermediate portion between the first end and
the second end; and
an outer tube (40) comprising a third end, a fourth end opposite to
the third end, and a second intermediate portion between the third end
and the fourth end: wherein
the inner tube (42) is inside the outer tube (40);
the inner tube (42) and the outer tube (40) are attached together
in such a way that only the first end and the third end are attached
together and the second end and the fourth end are attached together,
and such that the first intermediate portion and the second intermediate
portion are spaced apart and not directly connected together; and
there is a chamber (50) between the first intermediate portion and
the second intermediate portion, the chamber (50) having a chamber
opening (52);
means for establishing, within the chamber (50), via the chamber opening (52), a predetermined environment; and
means for sealing the chamber opening (52) so as to maintain, within the chamber (50), the established environment, thereby producing the aircraft component (54).
15. Apparatus according to claim 14, wherein
the initial object (4) further comprises a first annular portion (44) and a second annular portion (46);
the first annular portion (44) connects together the first end and the third end;
the second annular portion (46) connects together the second end and the fourth end: and
the inner tube (42) and the outer tube (40) are connected together only by the first annular portion (44) and the second annular portion (48).