US 12,110,824 B2
Aircraft propulsion system with variable area inlet assembly
Timothy Gormley, Bonita, CA (US)
Assigned to ROHR, INC., Chula Vista, CA (US)
Filed by Rohr, Inc., Chula Vista, CA (US)
Filed on May 1, 2023, as Appl. No. 18/141,817.
Application 18/141,817 is a continuation of application No. 17/159,343, filed on Jan. 27, 2021, granted, now 11,639,686.
Prior Publication US 2023/0265795 A1, Aug. 24, 2023
Int. Cl. F02C 7/042 (2006.01); B64D 33/02 (2006.01)
CPC F02C 7/042 (2013.01) [B64D 33/02 (2013.01)] 20 Claims
OG exemplary drawing
 
17. An assembly for an aircraft propulsion system, comprising:
a center body comprising a center body surface with a trailing edge;
a nacelle inlet structure extending circumferentially around the center body, the nacelle inlet structure having a leading edge;
an inlet passage radially between and formed by at least the center body and the nacelle inlet structure, the inlet passage comprising a metering portion; and
a turbine engine comprising a plurality of flowpaths fluidly coupled in parallel to and downstream of the inlet passage;
a first component of the assembly configured to rotate about a rotational axis of the first component of the assembly relative to a second component of the assembly between
a first position where the metering portion has a first area, and where the trailing edge is axially displaced from the leading edge by a first distance; and
a second position where the metering portion has a second area that is different than the first area, and where the trailing edge is axially displaced from the leading edge by a second distance that is different than the first distance;
the first component of the assembly comprising one of the center body or the nacelle inlet structure; and
the second component of the assembly comprising the other one of the center body or the nacelle inlet structure, and the rotational axis offset from a centerline of the turbine engine.