Aircraft electrical energy supply network

Patent metadata

Field	Value
Publication number	US-12597779-B2
Application number	US-202017604504-A
Country	US
Kind code	B2
Filing date	Apr 23, 2020
Priority date	Apr 25, 2019
Publication date	Apr 7, 2026
Grant date	Apr 7, 2026

Abstract

An electrical energy supply network of an aircraft equipped with a plurality of electrical loads to be supplied includes at least two generators of a turbogenerator of the aircraft, each suitable for providing an electrical energy source, and at least one stator associated with a rectifier. The stators of the generators are mounted in parallel on at least two distribution buses designed to supply the plurality of electrical loads. The supply network also includes contactors suitable for electrically connecting or disconnecting the distribution buses from each other.

First claim

The invention claimed is:

1 . An electrical energy supply network of an aircraft provided with a plurality of electrical loads to be supplied, said electrical energy supply network comprising:
at least two generators of a turbogenerator of the aircraft adapted to provide an electrical energy source, each of the least two generators comprising at least two electrical chains, each electrical chain comprising a stator and a rectifier having an AC input electrically connected to said stator and a DC output electrically connected to a rectifier contactor, the DC output of each rectifier contactor electrically connected to one of at least two distribution buses arranged to supply the plurality of electrical loads; energy storage electrically connected to the at least two distribution buses, wherein the energy storage comprises batteries and converters electrically connected to said batteries; a plurality of load contactors, at least one load contactor electrically connected between each electrical load of the plurality of electrical loads and the at least two distribution buses and at least one load contactor electrically connected between each converter and the at least two distribution buses, wherein each of the at least two distribution buses is connected to the other through a bus connection circuit, the bus connection circuit comprising an inductor, a resistor and a bus contactor connected in series, the inductor and the resistor being configured to limit the transient current variations and to dissipate a part of this current as heat and the bus contactor being configured to electrically disconnect the at least two distribution buses from each other, and wherein for each one of the at least two generators, each one of the least two electrical chains is connected to a different one of the at least two distribution buses.

2 . The electrical energy supply network according to claim 1 , further comprising a centralized control unit operatively coupled to the at least two generators and the energy storage means.

3 . An aircraft turbogenerator, comprising the electrical energy supply network of claim 1 .

4 . The electrical energy supply network according to claim 1 , wherein the bus contactors are configured to disconnect the at least two distribution buses from each other under a short-circuit current.

Assignees

• Safran Helicopter Engines

Inventors

• Barraco Thomas
• Klonowski Thomas
• Poumarede Vincent

Classifications

• B64D27/357

  using batteries · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D47/00 Primary

  Equipment not otherwise provided for · CPC title

• H02J3/32

  using batteries or super capacitors with converting means · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title