Outer barrel support structure for nacelle inlet structure
An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure extending axially along and circumferentially about an axis. The nacelle inlet structure includes an inlet lip, an inner barrel, an outer barrel and a plurality of supports. The inlet lip forms a leading edge of the nacelle inlet structure. The inner barrel projects axially aft away from the inlet lip. The outer barrel projects axially aft away from the inlet lip. The outer barrel is radially outboard of and axially overlaps the inner barrel. The supports are arranged circumferentially about the axis in an array. Each of the supports extends longitudinally along the axis. Each of the supports extends radially between and is connected to the inner barrel and the outer barrel.
1. An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure extending axially along and circumferentially about an axis, the nacelle inlet structure including an inlet lip, an inner barrel, an outer barrel and a plurality of supports;
the inlet lip forming a leading edge of the nacelle inlet structure, the inlet lip including an outer aft end;
the inner barrel projecting axially aft away from the inlet lip;
the outer barrel projecting axially aft away from the inlet lip, the outer barrel including a mounting flange, the mounting flange connected to the outer aft end forming an interface between the outer barrel and the inlet lip, and the outer barrel radially outboard of and axially overlapping the inner barrel; and
the plurality of supports arranged circumferentially about the axis in an array and configured to support the outer barrel, each of the plurality of supports extending longitudinally along the axis, each of the plurality of supports extending radially between and connected to the inner barrel and the outer barrel, and forward ends of the plurality of supports disposed aft of the interface between the outer barrel and the inlet lip.
2. The assembly of claim 1 , wherein at least one support of the plurality of supports comprises a gusset.
3. The assembly of claim 1 , wherein at least one support of the plurality of supports comprises a channeled beam.
4. The assembly of claim 1 , wherein
at least one support of the plurality of supports includes a base and a port; and
the port project laterally through the base.
5. The assembly of claim 1 , wherein
at least one support of the plurality of supports includes an inner flange, an outer flange and a base extending radially between and integral with the inner flange and the outer flange;
the inner flange is connected to the inner barrel; and
the outer flange is connected to the outer barrel.
6. The assembly of claim 5 , wherein the inner flange is bonded to the inner barrel.
7. The assembly of claim 5 , wherein the outer flange is mechanically fastened to the outer barrel.
8. The assembly of claim 1 , wherein
the plurality of supports include a first support and a second support circumferentially neighboring the first support within the array;
the first support radially tapers as the first support extends longitudinally along the axis towards the leading edge; and
the second support radially tapers as the second support extends longitudinally along the axis away from the leading edge.
9. The assembly of claim 1 , wherein
the plurality of supports include a first support and a second support;
the first support radially tapers as the first support extends longitudinally along the axis towards the leading edge; and
the second support radially tapers as the second support extends longitudinally along the axis towards the leading edge.
10. The assembly of claim 9 , wherein
the plurality of supports further include a third support circumferentially between the first support and the second support within the array; and
the third support radially tapers as the third support extends longitudinally along the axis away from the leading edge.
11. The assembly of claim 1 , wherein
the plurality of supports include a first support and a second support;
the first support radially tapers as the first support extends longitudinally along the axis away from the leading edge; and
the second support radially tapers as the second support extends longitudinally along the axis away from the leading edge.
12. The assembly of claim 11 , wherein
the plurality of supports further include a third support circumferentially between the first support and the second support within the array; and
the first support radially tapers as the third support extends longitudinally along the axis towards the leading edge.
13. The assembly of claim 1 , wherein
the nacelle inlet structure further includes a bulkhead radially between and connected to the inner barrel and the outer barrel;
the plurality of supports are arranged axially between the inlet lip and the bulkhead; and
each of the plurality of supports is axially next to and connected to the bulkhead.
14. The assembly of claim 13 , wherein at least one support of the plurality of supports is mechanically fastened to the outer barrel axially next to the bulkhead.
15. The assembly of claim 1 , wherein at least one support of the plurality of supports is mechanically fastened to the outer barrel axially next to the interface between the outer barrel and the inlet lip.
16. The assembly of claim 1 , wherein each of the plurality of supports is bonded to the inner barrel.
17. The assembly of claim 1 , wherein each of the plurality of supports comprises thermoplastic material.
18. The assembly of claim 1 , wherein
the nacelle inlet structure further includes a plurality of structure segments;
each of the plurality of structure segments includes an exterior skin and an electric heater; and
the exterior skin forms a respective circumferential section of the inlet lip.
19. An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure extending axially along and circumferentially about an axis, the nacelle inlet structure including an inlet lip, an inner barrel, an outer barrel, a bulkhead, a cavity and a support structure;
the inlet lip forming a leading edge of the nacelle inlet structure;
the inner barrel connected to the inlet lip at an inner connection;
the outer barrel connected to the inlet lip at an outer connection, and the outer barrel radially outboard of and axially overlapping the inner barrel;
the bulkhead radially between and connected to the inner barrel and the outer barrel;
the cavity extending radially within the nacelle inlet structure from the inner barrel to the outer barrel, and the cavity extending axially within the nacelle inlet structure from the bulkhead to the inlet lip; and
the support structure disposed within the cavity, the support structure supporting the outer barrel, the support structure disposed aft of the outer connection and the inner connection, and the support structure formed by a plurality of discrete axially extending supports arranged and spaced apart circumferentially about the axis in an array.
20. An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure extending axially along and circumferentially about an axis, the nacelle inlet structure including an inlet lip, an inner barrel, an outer barrel, a cavity, a support structure and an electric heater configured with an exterior skin of the inlet lip;
the inlet lip forming a leading edge of the nacelle inlet structure;
the inner barrel connected to and projecting axially aft away from the inlet lip at a first interface;
the outer barrel connected to and projecting axially aft away from the inlet lip at a second interface, and the outer barrel radially outboard of and axially overlapping the inner barrel;
the cavity extending radially within the nacelle inlet structure from the inner barrel to the outer barrel, and the cavity extending axially within the nacelle inlet structure to a portion of the inlet lip forming the leading edge; and
the support structure disposed within the cavity and supporting the outer barrel, the support structure disposed axially downstream of the first interface and axially downstream of the second interface, and the support structure formed by a plurality of discrete axially extending supports arranged and spaced apart circumferentially about the axis in an array.