US 12,351,323 B2
Hybrid electric engine and nacelle system
Marc J. Muldoon, Marlborough, CT (US); Murat Yazici, Glastonbury, CT (US); and Brian Sherman, Chula Vista, CA (US)
Assigned to RTX CORPORATION, Farmington, CT (US); and ROHR, INC., Chula Vista, CA (US)
Filed by RTX Corporation, Farmington, CT (US); and Rohr, Inc., Chula Vista, CA (US)
Filed on Feb. 2, 2023, as Appl. No. 18/163,676.
Prior Publication US 2024/0262515 A1, Aug. 8, 2024
Int. Cl. B64D 27/24 (2024.01); B64D 15/12 (2006.01); B64D 27/10 (2006.01); B64D 29/00 (2006.01); F02C 6/14 (2006.01); B64D 27/02 (2006.01)
CPC B64D 27/24 (2013.01) [B64D 15/12 (2013.01); B64D 27/10 (2013.01); B64D 29/00 (2013.01); F02C 6/14 (2013.01); B64D 27/026 (2024.01)] 17 Claims
OG exemplary drawing
 
1. A propulsion system of an aircraft, comprising:
a hybrid electric gas turbine engine; and
a nacelle at least partially enclosing the hybrid electric gas turbine engine, the nacelle including:
a first nacelle half; and
a second nacelle half;
wherein each of the first nacelle half and the second nacelle half include:
an outer nacelle sleeve;
an inner nacelle sleeve radially offset from the outer nacelle sleeve such that a flowpath is defined between the outer nacelle sleeve and the inner nacelle sleeve; and
an upper bifurcation connecting the outer nacelle sleeve to the inner nacelle sleeve at an upper end of the nacelle;
wherein the flowpath is circumferentially continuous between the upper bifurcation of the first nacelle half and the upper bifurcation of the second nacelle half.