Turbogenerator with simplified control system for aircraft
AssigneesSafran Helicopter Engines, Safran Power Units
InventorsFabien Mercier-Calvairac, Patrick Marconi, Denis Antoine Julien Real
Life of this patent
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Abstract
A propulsion assembly for aircraft includes a single-shaft engine turbomachine including a combustion chamber and a rotatably mounted shaft that turns at a turbomachine rating; an electrical generator coupled to the shaft; and a control system. The control system includes a fuel pump that brings 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 that are coupled to the electrical generator and that control an electrical power drawn off the electrical generator so as to attain a target turbomachine rating.
Claims10
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.
A method for controlling a propulsion assembly for aircraft, the method comprising:
- bringing fuel into a combustion chamber of a single-shaft engine turbomachine by a fuel pump by enforcing a fuel flow rate according to a direct function of an ambient pressure and of a turbomachine rating at which the shaft of the turbomachine turns;
- and
- drawing electrical power off an electrical generator coupled to the shaft under control of power electronics, so as to attain a target turbomachine rating,
- the power electronics being configured to control the electrical power drawn off the electrical generator as a function of a power requirement that is lower that the electrical power drawn so as to transiently increase the drawn electrical power and reduce the turbomachine rating, then reduce the drawn electrical power to attain the target electrical power and a constant turbomachine rating.
A method for controlling a propulsion assembly for aircraft, the method comprising:
- bringing fuel into a combustion chamber of a single-shaft engine turbomachine by a fuel pump by enforcing a fuel flow rate according to a direct function of an ambient pressure and of a turbomachine rating at which the shaft of the turbomachine turns;
- drawing electrical power off an electrical generator coupled to the shaft under control of power electronics by increasing or decreasing a resistive torque applied by the electrical generator to the shaft, so as to attain a target turbomachine rating;
- and
- comparing the drawn electrical power to a planned electrical power depending on the ambient pressure.
Dependencies are inferred from the claim text.