US 12,305,582 B2
Turbogenerator with simplified control system for aircraft
Fabien Mercier-Calvairac, Moissy-Cramayel (FR); Patrick Marconi, Moissy-Cramayel (FR); and Denis Antoine Julien Real, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR); and SAFRAN POWER UNITS, Toulouse (FR)
Appl. No. 17/608,685
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR); and SAFRAN POWER UNITS, Toulouse (FR)
PCT Filed Jul. 3, 2020, PCT No. PCT/EP2020/068804
§ 371(c)(1), (2) Date Nov. 3, 2021,
PCT Pub. No. WO2021/001527, PCT Pub. Date Jan. 7, 2021.
Claims priority of application No. 1907426 (FR), filed on Jul. 3, 2019.
Prior Publication US 2022/0213842 A1, Jul. 7, 2022
Int. Cl. F02C 9/30 (2006.01); B64D 27/02 (2006.01); F02C 9/28 (2006.01)
CPC F02C 9/30 (2013.01) [B64D 27/026 (2024.01); F02C 9/28 (2013.01); F05D 2220/76 (2013.01); F05D 2270/312 (2013.01); F05D 2270/335 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A propulsion assembly for aircraft, the propulsion assembly comprising:
a single-shaft engine turbomachine comprising a combustion chamber and a rotatably mounted shaft configured to turn at a turbomachine rating;
an electrical generator coupled to the shaft;
at least one ambient pressure sensor;
an engine health monitoring system and
a control system, the control system comprising:
a fuel pump configured to bring fuel into the combustion chamber at a fuel flow rate which is a direct function of an ambient pressure and of the turbomachine rating; and
power electronics coupled to the electrical generator and configured to control an electrical power drawn off the electrical generator, so as to attain a target turbomachine rating,
the engine health monitoring system being configured to compare the electrical power drawn to a planned electrical power depending on the ambient pressure.