US 12,410,751 B2
Air intake for an aircraft propulsion system engine assembly
Michel Desjardins, Saint-Hubert (CA); and Guillaume Landry-Drolet, Boucherville (CA)
Assigned to Pratt & Whitney Canada Corp., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Sep. 25, 2023, as Appl. No. 18/372,493.
Prior Publication US 2025/0101915 A1, Mar. 27, 2025
Int. Cl. F02C 7/055 (2006.01); F02C 7/36 (2006.01)
CPC F02C 7/055 (2013.01) [F02C 7/36 (2013.01); F05D 2220/323 (2013.01)] 17 Claims
OG exemplary drawing
 
1. An engine assembly for an aircraft propulsion system, the engine assembly comprising:
a gas turbine engine including:
an engine output shaft configured for rotation about a first rotational axis,
an air intake including an air intake body forming an air inlet, an air outlet, and an air plenum extending between and connecting the air inlet and the air outlet in fluid communication, the air plenum extends circumferentially about the engine output shaft between and to a first circumferential end of the air intake and a second circumferential end of the air intake, the first circumferential end and the second circumferential end enclosing the air plenum opposite the air inlet relative to the first rotational axis, and the first circumferential end and the second circumferential end form a circumferential gap outside of the air intake and circumferentially between the first circumferential end and the second circumferential end, the circumferential gap located opposite the air inlet relative to the first rotational axis, and
a compressor connected in fluid communication with the air intake at the air outlet;
a gearbox including a gear assembly operably connected to the engine output shaft; and
a first drive shaft operably connected to the gear assembly, the first drive shaft is rotatable about a second rotational axis, the second rotational axis is radially offset from the first rotational axis, and the first drive shaft extends along the second rotational axis through the circumferential gap.