| 摘要 |
The present invention proposes an air conditioning system for an aircraft powered solely using electrical energy, intended to draw air in from outside the aircraft and deliver conditioned air to the interior of the aircraft, comprising at most three motorized rotary machines made up of: - a first and a second motorized turbocompressor (11, 12) which are independent of one another, each motorized turbocompressor being formed of a compressor (14, 15), of a turbine (20, 21) and of an electric motor (17, 18); and - a motor compressor (13) interconnected between the motorized turbocompressors (11, 12) via an interconnection pipe and formed of a compressor (16) and of an electric motor (19), and in which the motor compressor (13) is designed to: - generate a primary air flow, which entrains a secondary air flow, allowing a flow of air for breathing to be cooled in a first phase of operation corresponding to a phase of operation on the ground or at relatively low altitude and at relatively low aircraft speed; - be at shutdown or at low idle in a second phase of operation at relatively low altitude and relatively high aircraft speed; and - provide a top up flow of air for breathing in a third phase of operation at relatively high altitude and relatively high aircraft speed. Figure 1 |
