Abstract: An aircraft turbomachine (100) comprising a first channel (200) putting into communication the high-pressure compressor (30) and a high-pressure turbine (50), a second channel (400) putting into communication the high-pressure compressor and a low-pressure turbine (60), the first channel being equipped with a valve (600), a third channel (700) being in selective communication with the first channel via the valve, the third channel being in communication with the low-pressure turbine, the valve having a first configuration in which air circulation in the first channel is allowed and prohibited in the third channel, and a second configuration in which air circulation of the first channel is diverted to the third channel, a control device (800) being configured to determine an air pressure of the low-pressure turbine and command the valve to cause it to transition from the first configuration to the second configuration depending on the determined pressure.

Abstract: The invention relates to a turbine engine, comprising: a device for bleeding a compressor, particularly a high-pressure compressor, comprising at least one valve for bleeding said compressor, an outlet of said valve being connected to a bleed system designed to discharge a bleed airflow; and at least one device for cooling at least one unit, comprising a heat exchanger, an air outlet of which is connected to an ejector of the jet pump type, which comprises a feed-through duct for a secondary airflow coming from said air outlet, as well as a nozzle for spraying a primary airflow inside said feed-through duct, wherein the nozzle is connected to said bleed system.

Abstract: An aircraft turbomachine (100) comprising a first channel (200) putting into communication the high-pressure compressor (30) and a high-pressure turbine (50), a second channel (400) putting into communication the high-pressure compressor and a low-pressure turbine (60), the first channel being equipped with a valve (600), a third channel (700) being in selective communication with the first channel via the valve, the third channel being in communication with the low-pressure turbine, the valve having a first configuration in which air circulation in the first channel is allowed and prohibited in the third channel, and a second configuration in which air circulation of the first channel is diverted to the third channel, a control device (800) being configured to determine an air pressure of the low-pressure turbine and command the valve to cause it to transition from the first configuration to the second configuration depending on the determined pressure.

Abstract: The invention relates to a turbine engine, comprising: a device for bleeding a compressor, particularly a high-pressure compressor, comprising at least one valve for bleeding said compressor, an outlet of said valve being connected to a bleed system designed to discharge a bleed airflow; and at least one device for cooling at least one unit, comprising a heat exchanger, an air outlet of which is connected to an ejector of the jet pump type, which comprises a feed-through duct for a secondary airflow coming from said air outlet, as well as a nozzle for spraying a primary airflow inside said feed-through duct, wherein the nozzle is connected to said bleed system.