Safran Helicopter Engines

Pierre Chabanne

Julien Fabrice Girardot

Lionel Scuiller

Christophe Michel Georges Marcel Brillet

Thibaut Maxime Javoy

Sylvain Jacques Marie Gourdant

Alexandre Auduberteau

Frédéric Anthony Alain Imbourg

Device () for controlling an airflow guiding system (), comprising at least one actuator () configured to translate a control rod () between a first and a second end position of a nominal operating range in which at least one vane () of the airflow guiding system () can be moved between a first and a second angle, the control rod () being connected to the vane () by a control lever () comprising a first control rod () and a second control rod () which are hinged together. The actuator () is configured to bring the control rod () into a safety position located beyond the second end position of the nominal operating range and to orient the vane () at a safe pitch angle between the first angle and the second angle.

Device for controlling an airflow guiding system, in particular in an aircraft turbine engine

The invention concerns a turbomachine rotor (), characterised in that it comprises a threaded or tapped part () and a damping nut () screwed onto the threaded or tapped part () so as to allow the threads of the nut () and of the threaded or tapped part () to rub against each other in the event of vibration of the rotor ().

Turbomachine rotor

The invention relates to a turbine engine comprising an air compression stage comprising at least one movable compressor wheel, an air inlet duct coupled to said air compression stage, a first sealing device, which is arranged between a front portion of the movable compressor wheel and the air inlet duct and comprising at least one seal, a channel for conveying the air compressed by the movable wheel and a second sealing device, which is arranged between a rear portion of the movable compressor wheel and the conveying channel and is configured to receive an airflow coming from the conveying channel, the turbine engine being remarkable in that the second sealing device is configured to allow some of the air passing therethrough to be bled and in that the bleed air is conveyed to the seal of the first sealing device so as to keep it under pressure.

Sealing assembly for turbomachine

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Idron, France

Pierre Chabanne