US 12,146,445 B2
Method and system for regulating the thrust of an aircraft turbomachine
Rémy Henri Pierre Princivalle, Herstal (BE)
Assigned to SAFRAN AERO BOOSTERS, Herstal (BE)
Appl. No. 18/040,583
Filed by SAFRAN AERO BOOSTERS, Herstal (BE)
PCT Filed Aug. 10, 2021, PCT No. PCT/EP2021/072279
§ 371(c)(1), (2) Date Jun. 22, 2023,
PCT Pub. No. WO2022/034083, PCT Pub. Date Feb. 17, 2022.
Claims priority of application No. 2020/5570 (BE), filed on Aug. 14, 2020.
Prior Publication US 2023/0366358 A1, Nov. 16, 2023
Int. Cl. F02C 9/58 (2006.01); F02C 9/22 (2006.01)
CPC F02C 9/58 (2013.01) [F02C 9/22 (2013.01); F05D 2260/70 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A method for regulating the thrust of an aircraft turbomachine, the aircraft turbomachine comprising:
a propeller comprising a plurality of blades, the blades being configured to have selectively variable pitch;
components arranged successively along an engine axis, including:
a low-pressure compressor comprising at least one straightener equipped with vanes configured to have selectively variable pitch,
a high-pressure compressor,
a combustion chamber, and
one or more turbines;
the method comprising the steps of:
(0) selecting a steady regime for the aircraft turbomachine:
(i) varying the pitch of said vanes of the at least one straightener to regulate in an open loop the thrust of the turbomachine; and
(ii) regulating the pitch of said plurality of blades of the propeller in a closed loop based on a rotational speed of the propeller and on the steady regime selected at step (0) so that the rotational speed of the propeller corresponds to a first mathematical function of the pitch of said vanes of the at least one straightener, the first mathematical function depending on the steady regime selected at step (0).