Safran Aircraft Engines

Snecma

Daniel Bernava

Dominik Igel

Maxime Aurélien Rotenberg

Maxime Aurelien Rotenberg

Benissa Boujida

Michael Alain Eric Sauve

Yolande Chantal Ohouan Ekra Devalere

Maxime Rotenberg

An aircraft turbomachine () comprising a first channel () putting into communication the high-pressure compressor () and a high-pressure turbine (), a second channel () putting into communication the high-pressure compressor and a low-pressure turbine (), the first channel being equipped with a valve (), a third channel () 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 () 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.

Device and method for cooling a low pressure turbine in a turbomachine

The invention relates to a turbine engine, comprising:

Cooling device for a turbomachine supplied by a discharge circuit

Growing community of inventors

Moissy-Cramayel, France

Daniel Bernava