US 12,296,971 B2
Segmented nacelle inlet lip with electric anti-icing system
Jeffrey W. Moe, Chula Vista, CA (US); John E. Van Doren, San Diego, CA (US); and Aleksandar Ratajac, San Diego, CA (US)
Assigned to Rohr, Inc., Chula Vista, CA (US)
Filed by Rohr, Inc., Chula Vista, CA (US)
Filed on Aug. 8, 2023, as Appl. No. 18/231,572.
Prior Publication US 2025/0051025 A1, Feb. 13, 2025
Int. Cl. B64D 33/02 (2006.01); B64D 15/12 (2006.01); F01D 25/02 (2006.01); F01D 25/24 (2006.01); F02C 7/04 (2006.01)
CPC B64D 33/02 (2013.01) [B64D 15/12 (2013.01); F01D 25/02 (2013.01); F01D 25/243 (2013.01); F02C 7/04 (2013.01); B64D 2033/0233 (2013.01)] 20 Claims
OG exemplary drawing
 
13. An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure extending axially along and circumferentially around a centerline, the nacelle inlet structure including an inlet lip, an inner barrel, an outer barrel, a bulkhead, a plurality of structure segments and an internal cavity;
the inlet lip forming a leading edge of the nacelle inlet structure;
the inner barrel projecting axially aft away from the inlet lip;
the outer barrel projecting axially aft away from the inlet lip, and the outer barrel radially outboard of and axially overlapping the inner barrel;
the bulkhead connected to the inner barrel and the outer barrel, and the bulkhead radially tapering as the bulkhead extends axially towards the leading edge;
each of the plurality of structure segments attached to the inner barrel and the bulkhead, each of the plurality of structure segments comprising an exterior skin, and the exterior skin forming a respective circumferential section of the inlet lip; and
the internal cavity extending axially within the nacelle inlet structure from the exterior skin of each of the plurality of structure segments to the bulkhead;
wherein each of the plurality of structure segments further comprises a mount bonded to the exterior skin and mechanically attached to the bulkhead and the inner barrel.