US 12,227,284 B2
Pitch change mechanism for an aircraft engine
Krzysztof Jedliński, Raszyn (PL); Mirosław Sobaniec, Grodzisk Mazowiecki (PL); Mateusz Gołdyn, Warsaw (PL); Tomasz Biwański, Koszalin (PL); Tomasz Kosieradzki, Michalowice (PL); and Dariusz Łodkowski, Warsaw (PL)
Assigned to General Electric Company Polska sp. z o.o., Warsaw (PL)
Filed by General Electric Company Polska sp. z o.o., Warsaw (PL)
Filed on Jan. 17, 2024, as Appl. No. 18/415,155.
Claims priority of application No. 445528 (PL), filed on Jul. 10, 2023.
Prior Publication US 2025/0019065 A1, Jan. 16, 2025
Int. Cl. B64C 11/30 (2006.01); B64C 11/06 (2006.01)
CPC B64C 11/305 (2013.01) [B64C 11/06 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A pitch change mechanism for an aircraft engine, the pitch change mechanism comprising:
a unison ring;
a plurality of crankshafts coupled to the unison ring, the plurality of crankshafts configured to receive a plurality of blades and each of the plurality of crankshafts having a longitudinal axis;
an inner shaft coupled to the plurality of crankshafts and the unison ring;
an actuator piston fixed along a longitudinal axis of the pitch change mechanism; and
an actuator cylinder coupled to the inner shaft, the actuator cylinder configured to move relative to the actuator piston along the longitudinal axis of the pitch change mechanism,
wherein movement of the actuator cylinder relative to the actuator piston is transferred to a rotation of each of the plurality of crankshafts around the longitudinal axis of each of the plurality of crankshafts to change a pitch of the plurality of blades.