US 12,537,466 B2Granted

Electrical system for an aircraft equipped with a motor

AssigneeSafran

InventorsAnne Marie Lienhardt, Yann Fefermann, Florent Rougier

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Abstract

An electrical system for an aircraft includes first and second buses, first and second electric generators, and first and second AC-to-DC converters. The first bus is connected to an AC network. The second bus is connected to a DC network of the aircraft. The first electric generator is connected to the first bus and a first rotary spool of an engine of the aircraft to exchange mechanical and/or electrical power. The first AC-to-DC converter is connected to the first and second buses. The second electric generator is connected to a second rotary spool of the engine of the aircraft. The second AC-to-DC converter connected to the second electric generator and to the second bus. One or more of the converters operates in a forced mode providing regulation of the electrical power of one or more buses, and/or a free mode providing regulation of a voltage of the second bus.

Claims11

Dependent claims

A method of control of an electrical system comprising:

a first bus configured to be connected to an AC network of an aircraft to allow transfer of electrical power from the first bus to the AC network;
a second bus configured to be connected to a DC network of the aircraft to allow transfer of electrical power from the second bus to the DC network;
a first electric generator connected to the first bus to inject electrical power into or draw electrical power off the first bus, the first electric generator being configured to be connected to a first rotary spool of an engine of the aircraft to allow an exchange of mechanical and/or electrical power between the first rotary spool and the first electric generator;
a first AC-to-DC converter, the first converter being connected to the first bus to inject electrical power into or draw electrical power off the first bus and to the second bus to inject electrical power into or draw electrical power off the second bus;
a second electric generator configured to be connected to a second rotary spool of the engine of the aircraft to allow an exchange of mechanical and/or electrical power between the second rotary spool and the second electric generator;
and
a second AC-to-DC converter, the second converter being connected to the second electric generator to allow an exchange of electrical power between the second electric generator and the second converter, and to the second bus to inject electrical power into or draw electrical power off the second bus;
wherein at least one of the converters is configured to operate according to at least one of the following operating modes:
a forced mode, in which the at least one of the converters provides regulation of the electrical power of at least one bus to which the at least one of the converters is connected;
and
a free mode, in which the at least one of the converters provides regulation of a voltage of the second bus, and
wherein the electrical system further comprises a controller configured to drive at least one of the converters so as to an operating mode of the at least one of the converters,
the method being implemented by the controller and comprising:
driving of the second converter so that the second converter operates in free mode to provide the regulation of the voltage of the second bus;
receiving of a first measurement of an electrical power injected by the first electric generator into the first bus;
receiving of a second measurement of an electrical power exchanged between the second electric generator and the second converter;
comparison of a ratio of the first measurement to the second measurement with a reference value;
and
driving of the first converter so that, if the ratio is different from the reference value, the first converter operates in a forced mode in which the first converter regulates the electrical power of the first bus.

16 more elements

The method of control of an electrical system comprising:

a first bus configured to be connected to an AC network of an aircraft to allow transfer of electrical power from the first bus to the AC network;
a second bus configured to be connected to a DC network of the aircraft to allow transfer of electrical power from the second bus to the DC network;
a first electric generator connected to the first bus to inject electrical power into or draw electrical power off the first bus, the first electric generator being configured to be connected to a first rotary spool of an engine of the aircraft to allow an exchange of mechanical and/or electrical power between the first rotary spool and the first electric generator;
a first AC-to-DC converter, the first converter being connected to the first bus to inject electrical power into or draw electrical power off the first bus and to the second bus to inject electrical power into or draw electrical power off the second bus;
a second electric generator configured to be connected to a second rotary spool of the engine of the aircraft to allow an exchange of mechanical and/or electrical power between the second rotary spool and the second electric generator;
and
a second AC-to-DC converter, the second converter being connected to the second electric generator to allow an exchange of electrical power between the second electric generator and the second converter, and to the second bus to inject electrical power into or draw electrical power off the second bus;
wherein at least one of the converters is configured to operate according to at least one of the following operating modes:
a forced mode, in which the at least one of the converters provides regulation of the electrical power of at least one bus to which the at least one of the converters is connected;
and
a free mode, in which the at least one of the converters provides regulation of a voltage of the second bus, and
wherein the electrical system further comprises a controller configured to drive at least one of the converters so as to an operating mode of the at least one of the converters,
the method being implemented by the controller and comprising:
receiving of a measurement of an electrical power injected by the first electric generator into the first bus;
comparison of the measurement with a reference value;
driving of the first converter so that, if the measurement is different from the reference value, the first converter operates in a forced mode in which the first converter regulates the electrical power of the first bus;
and
driving of the second converter so that the second converter operates in free mode to provide the regulation of the voltage of the second bus.

15 more elements

The method of control of an electrical system comprising:

a first bus configured to be connected to an AC network of an aircraft to allow transfer of electrical power from the first bus to the AC network;
a second bus configured to be connected to a DC network of the aircraft to allow transfer of electrical power from the second bus to the DC network;
a first electric generator connected to the first bus to inject electrical power into or draw electrical power off the first bus, the first electric generator being configured to be connected to a first rotary spool of an engine of the aircraft to allow an exchange of mechanical and/or electrical power between the first rotary spool and the first electric generator;
a first AC-to-DC converter, the first converter being connected to the first bus to inject electrical power into or draw electrical power off the first bus and to the second bus to inject electrical power into or draw electrical power off the second bus;
a second electric generator configured to be connected to a second rotary spool of the engine of the aircraft to allow an exchange of mechanical and/or electrical power between the second rotary spool and the second electric generator;
and
a second AC-to-DC converter, the second converter being connected to the second electric generator to allow an exchange of electrical power between the second electric generator and the second converter, and to the second bus to inject electrical power into or draw electrical power off the second bus;
wherein at least one of the converters is configured to operate according to at least one of the following operating modes:
a forced mode, in which the at least one of the converters provides regulation of the electrical power of at least one bus to which the at least one of the converters is connected;
and
a free mode, in which the at least one of the converters provides regulation of a voltage of the second bus, and
wherein the electrical system further comprises a controller configured to drive at least one of the converters so as to determine an operating mode of the at least one of the converters,
the method being implemented by the controller and comprising:
receiving of a measurement of an electrical power exchanged between the second electric generator and the second converter;
comparison of the measurement with a reference value;
and
driving of the second converter so that, if the measurement is different from the reference value, the second converter operates in a forced mode in which the second converter regulates the electrical power of the second bus;
and
driving of the first converter so that the first converter operates in free mode to provide the regulation of the voltage of the second bus.

16 more elements

Dependencies are inferred from the claim text.