Safran Electrical & Power

Safran Aircraft Engines

Safran

Philippe Delbosc

Vincent François Georges Millier

Loïc Paul Yves Guillotel

Clément Dupays

Anne Lienhardt

Pierre-Alain Jean Philippe Reigner

Benoit Michaud

Cyrille Gautier

Anthony Gimeno

Philippe Naneix

Sonia Dhokkar

Christophe Viguier

Samir Nehme

Rémi Goncalves

Yann Fefermann

Udo Muller

The present invention relates to a system for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system including:

System for converting and transporting electrical energy for the internal hybridisation of an aircraft turbomachine

An electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft which includes a high-voltage DC propulsive electric distribution network, a non-propulsive electric distribution network which is connected to loads of the aircraft, and an electric distribution network which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

Electric architecture for a hybrid thermal/electric propulsion aircraft and twin-engined aircraft comprising such an architecture

An aircraft with hybrid thermal/electrical propulsion includes a turbomachine; a first electrical source; a second electrical source equipped with an electrical energy storage device; a non-propulsion electrical distribution network; a low-voltage electrical distribution network; and a propulsion electrical distribution network. The three electrical distribution networks are electrically supplied by the first and second electrical sources and electrically interconnected by static converters.

Electric architecture for hybrid propulsion

A system for controlling an aircraft power network including at least a first propulsion assembly having at least one left-hand starter-generator and a second propulsion assembly having at least one right-hand starter-generator as well as other electrical motors, the system including first and second power electronics boxes each including at least two so-called generic control boards for controlling the power network, each of these at least two generic control electronics boards being connected by a fast communication link to separate first and second data switches, the first and second data switches of the first power electronics box being respectively connected to the first and second data switches of the second power electronics box by a first fast communication bus.

System for controlling an aircraft electrical network

Disclosed is an electrically conductive rigid bar () for electrically connecting an electric machine () of an aircraft turbine engine, characterised in that it comprises: —an elongate body () made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm, and— an electrical insulation sheath () that surrounds the body, at least one of the longitudinal ends () of the body not being covered by the sheath and comprising a through-hole () in which a bolt () for fastening and electrically connecting this end is mounted.

Rigid bar for electrically connecting a machine in an aircraft turbine engine

Growing community of inventors

Moissy-Cramayel, France

Philippe Delbosc