Module for supplying pressurized fresh air to an air-conditioning pack of an aircraft cabin, air-conditioning system equipped with such a module, and corresponding method

An auxiliary module for supplying pressurized air to an air-conditioning system of a cabin of an aircraft comprising a device or bleeding pressurized air from a propulsion engine of the aircraft and an air-conditioning pack comprising a pack air inlet fluidically connected to said pressurized air bleed device, and a pack air outlet fluidically connected to said cabin in order to be able to supply it with air at controlled pressure and temperature, the module comprising:

• a turbomachine, referred to as auxiliary turbomachine, comprising at least one compressor provided with an air inlet and an air outlet, and at least one turbine provided with an air inlet and an air outlet which are mechanically coupled to each other,
• a conduit, referred to as fresh air inlet conduit, suitable to be able to fluidically connect a scoop for drawing in external air and said air inlet of the compressor,
• a conduit, referred to as bleed air inlet conduit, suitable to be able to connect in fluid communication said pressurized air bleed device and said air inlet of the turbine, said conduit being equipped with a valve for regulating the air flow rate, referred to as module valve, controlled by a control unit in order to be able to activate at least the following two modes:
• a mode, referred to as standard mode, in which said module valve is closed, so that said pack air inlet is exclusively supplied with the bleed air coming from the pressurized air bleed device,
• a mode, referred to as fresh air mode, in which said module valve is open, so that said pack air inlet can be supplied with the pressurized air coming from the auxiliary module and wherein said bleed air coming from said engine bleed device is ejected to the outside the aircraft,
• a conduit, referred to as pressurized fresh air outlet conduit, suitable to be able to fluidically connect said air outlet of the compressor and said pack air inlet.

An aircraft comprising at least one propulsion engine, a cabin and an air-conditioning system of said cabin, said air-conditioning system comprising:

• a device for bleeding pressurized air from a propulsion engine of the aircraft, referred to as engine bleed device,
• an air-conditioning pack comprising a pack air inlet fluidically connected to said engine bleed device, and a pack air outlet suitable to be able to be fluidically connected to said cabin in order to be able to supply it with air at controlled pressure and temperature,
• an auxiliary module for supplying pressurized air comprising:
• a turbomachine, referred to as auxiliary turbomachine, comprising at least one compressor provided with an air inlet and an air outlet, and at least one turbine provided with an air inlet and an air outlet which are mechanically coupled to each other, a conduit, referred to as fresh air inlet conduit, suitable to be able to fluidically connect a scoop for drawing in external air and said air inlet of the compressor,
• a conduit, referred to as bleed air inlet conduit, suitable to be able to connect in fluid communication said engine bleed device and said inlet of the turbine, said conduit being equipped with a valve for regulating the flow rate of air supplying said turbine, referred to as module valve,
• a conduit, referred to as pressurized fresh air outlet conduit, suitable to be able to fluidically connect said air outlet of the compressor and said pack air inlet,
• and a unit for controlling said module valve configured to be able to activate at least the following two modes:
• a mode, referred to as standard mode, in which said module valve is closed, so that said pack air inlet is exclusively supplied with the pressurized bleed air coming from the engine bleed device,
• a mode, referred to as fresh air mode, in which said module valve is open, so that said pack air inlet can be supplied with the pressurized air coming from the auxiliary module and wherein said bleed air coming from said engine bleed device is ejected to the outside the aircraft.