Safran Aircraft Engines

Snecma

Maxime Aurélien Rotenberg

Antoine Jean-Philippe Beaujard

Nicolas Xavier Trappier

Stéphane Pierre Guillaume Blanchard

Philippe Pierre Vincent Bouiller

Patrick Jean Laurent Sultana

Dominik Igel

Renaud James Martet

Julian Nicolas Girardeau

Joao Antonio Amorim

Frédéric Patard

Daniel Bernava

Benissa Boujida

Frédéric François Jean-Yves Patard

Christophe Caplain

The disclosure provides devices for cooling a turbine casing for a turbomachine and methods of using the same. The devices extend around an axis (X) and include air-distribution means configured to take in air and convey it to the casing. The air-distribution means include a first ramp and a second ramp extending circumferentially about the axis (X), each ramp having air ejection orifices intended to be directed towards the casing in order to cool it The devices further include adjustment means capable of adjusting the flow rate of air ejected at the level of the first ramp with respect to the flow rate of air ejected at the level of the second ramp.

Turbine casing cooling device for a turbomachine

The invention relates to a turbojet bearing housing including a fixed envelope traversed by a rotor, this envelope including a cylindrical end surrounding a seal ensuring the leak tightness of the cylindrical end of the envelope with the rotor, this envelope being equipped with a shell screwed onto the cylindrical end thereof, this shell including radial channels emerging opposite the seal while being arranged so that an air stream traversing the seal towards the housing mainly comes from these radial channels.

Shell for reducing overpressure in the vicinity of the upstream seal of a turbojet bearing housing

The invention relates to a turbine engine, comprising:

Cooling device for a turbomachine supplied by a discharge circuit

A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.

Turbine rotor with air separation ferrules for cooling of blade and disk coupling portions, for a turbomachine

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Moissy-Cramayel, France

Maxime Aurélien Rotenberg