US 12,326,113 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. 18/231,578.
Prior Publication US 2025/0052195 A1, Feb. 13, 2025
Int. Cl. F02C 7/047 (2006.01); B64D 29/00 (2006.01)
CPC F02C 7/047 (2013.01) [B64D 29/00 (2013.01)] 20 Claims
OG exemplary drawing
 
1. 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 and a plurality of structure segments;
the inlet lip forming a leading edge of the nacelle inlet structure;
the inner barrel projecting axially aft away from an inner aft end of the inlet lip;
a gap disposed between the inner aft end and the inner barrel;
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;
each of the plurality of structure segments including an exterior skin, an inner mount flange, an outer mount flange and an electric heater configured to heat the exterior skin;
the exterior skin forming at least a respective circumferential section of the inlet lip;
the inner mount flange connected to and projecting radially outward away from the exterior skin, wherein an inner fastener extends axially through the inner mount flange and couples the inner mount flange to the inner barrel; and
the outer mount flange connected to and projecting radially inward away from the exterior skin, wherein an outer fastener extends axially through the outer mount flange and couples the outer mount flange to the bulkhead.