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1. An aircraft turbomachine comprising at least one high-pressure compressor, a high-pressure turbine, a low-pressure turbine, a stator arranged axially between the high-pressure turbine and the low-pressure turbine, a rotor of said low-pressure turbine having an axis and carrying vanes, and a device for ventilating and pressurising this rotor comprising at least one collection pipe suitable for collecting a fraction of air circulating in the high-pressure compressor and of conveying it to a first internal enclosure which is delimited internally to the stator, the first enclosure communicating with at least one second internal enclosure delimited by said rotor of the low-pressure turbine, said first and second enclosures being separated at least in part by a stationary shroud having said axis, said device comprising at least one injector passing through said stationary shroud parallel to said axis and establishing communication between the first and second enclosures, wherein the injector has a variable cross-section configured to vary progressively in response to a pressure difference between said first and second enclosures.
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