System for converting and transporting electrical energy for the internal hybridisation of an aircraft with turbojet engines

Abstract

In an aircraft propelled by at least one turbojet engine from which power can be drawn or into which power can be injected via a high-pressure (100, 120) and / or low-pressure (102, 122) turbine shaft and comprising at least one gas turbine for ensuring power transients, a system for converting and transporting electrical energy is provided in which each of the high- and / or low-pressure turbine shafts is connected to a first dual-feed asynchronous machine (48, 50, 52, 54) delivering a first three-phase AC voltage to an AC distribution network (46) and a second polyphase AC voltage for a first bidirectional AC / DC converter (56, 58, 60, 62) supplying DC voltage to a DC distribution network (64), at least one second bidirectional DC / AC converter (66, 68) connected to the DC distribution network transforming this DC voltage into a third polyphase AC voltage supplying at least one second dual-feed asynchronous machine (70, 72) engaged with a rotation shaft (140, 160) of the gas turbine, the second dual-feed asynchronous machine further delivering a fourth polyphase alternating voltage to the AC distribution network.

Description

technical field [0001] The present invention relates to the general field of "more electric" propulsion architectures, and more specifically to the internal mixing of aircraft propellers. Background technique [0002] Most high power propulsion solutions have as their supply one or more gas turbines providing mechanical power to a rotating shaft. Specifically, beyond a certain flight time or a certain propulsion power, the power storage unit (such as a battery, fuel cell, or supercapacitor) does not have sufficient performance to be used alone, so it is necessary to transfer mechanical power from one shaft to one or more other axis to obtain a better operating point by adjusting the size of the propeller or by providing propulsion assistance based on an auxiliary source. [0003] Systems that convert and deliver electrical energy in an aircraft typically exhibit one of two types of architectures: [0004] - The most common DC architecture, which consists of a generator (po...

AI Technical Summary

Problems solved by technology

[0008] However, such an architecture does have a number of disadvantages: short-circuit faults inside the PM motor must be addressed as it is considered critical and necessarily involves redundancy (and thus added weight), losses in the static converter lead to associated losses of the generator, which makes any reconfiguration difficult, or here also involves adding redundancy to each type of converter (thus still adding weight), the mass of the protector increases because the architecture is DC voltage, And because of the multiple conversions along the line, it reduces the overall efficiency of the line (about 80% efficiency)

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