US 12,421,864 B2
Controlling excitation loads associated with open rotor aeronautical engines
Amit Zutshi, Mason, OH (US); Rafal Sarba, Warsaw (PL); James Ryan Reepmeyer, Montgomery, OH (US); Stefan Joseph Cafaro, Chapel Hill, NC (US); Inenhe Mohammed Khalid, West Chester, OH (US); Daniel Edward Mollmann, Cincinnati, OH (US); and Arjan Johannes Hegeman, Cincinnati, OH (US)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US); and GENERAL ELECTRIC COMPANY POLSKA SP. Z O.O., Warsaw (PL)
Filed by General Electric Company, Schenectady, NY (US); and General Electric Company Polska Sp. z o.o., Warsaw (PL)
Filed on Dec. 15, 2022, as Appl. No. 18/081,862.
Claims priority of application No. 441991 (PL), filed on Aug. 10, 2022.
Prior Publication US 2024/0052753 A1, Feb. 15, 2024
Int. Cl. F01D 17/16 (2006.01); B64D 27/10 (2006.01)
CPC F01D 17/16 (2013.01) [B64D 27/10 (2013.01)] 16 Claims
OG exemplary drawing
 
1. An open rotor aeronautical engine comprising:
a core engine;
an unducted fan assembly rotatably driven by the core engine;
an unducted guide vane assembly including a plurality of guide vanes extending outwardly from the core engine;
a pitch change assembly operably coupled to the plurality of guide vanes, the pitch change assembly comprising:
one or more actuators configured to change a pitch angle of respective ones of the plurality of guide vanes to augment or compensate for an excitation load; and
a plurality of linkage arms that are respectively movable by actuation of at least one of the one or more actuators, wherein respective ones of the plurality of linkage arms are directly or indirectly coupled to a corresponding one of the plurality of guide vanes,
wherein respective ones of the plurality of linkage arms have a length that differs from at least another one of the plurality of linkage arms respectively corresponding to another one of the plurality of guide vanes, wherein the length of a respective one of the plurality of linkage arms orients a displacement or a range of motion of the respective one of the plurality of linkage arms to an envelope of rotation of the corresponding one of the plurality of guide vanes about a guide vane axis, wherein the envelope of rotation of the corresponding one of the plurality of guide vanes differs from the envelope of rotation of at least another one of the plurality of guide vanes;
a sensor configured to provide sensor data indicative of the excitation load acting upon the open rotor aeronautical engine, wherein the sensor comprises an angle of attack sensor; and
an electronic controller, wherein the electronic controller is configured to actuate the one or more actuators to a first position during a cruise flight condition and to actuate the one or more actuators to a second position during a climbing flight condition, a descending flight condition, or a takeoff flight condition,
wherein the plurality of guide vanes comprises a first guide vane and a second guide vane, wherein the first guide vane and the second guide vane are located at inversely disposed circumferential positions.