Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Snecma

Gerard Jacques Stangalini

Jacky S Naudet

Jean-Louis Charbonnel

Marc R Marchi

Laurent Donatien Behaghel

Laurent Palmisano

Jean-Pierre Andre Joseph Mourlan

Philippe J Lefebvre

Christian Largillier

Jean-Pierre Andre Mourlan

A turbomachine comprising a diffuser&#x2014;distributor assembly comprising a downstream end-piece connected at its downstream end to means for injecting air for ventilating a turbine and delimiting with the impeller of a centrifugal compressor an annular cavity for the circulation of ventilation air taken from the outlet of the compressor, this turbomachine comprising means for taking air from the injection means and means for guiding this air to the radially internal portion of the downstream face of the impeller.

Turbomachine comprising a system for cooling the downstream face of an impeller of a centrifugal compressor

Device for cooling the external part of a turbine disk (2) by means of an external fresh air current (circuit II) without mixing with the warmer ventilation from the center of the disk (circuit I). A part (30) through which ducts (31, 32) pass that intersect without interruption, prevents mixing of substantially perpendicular streams in front of a part (22) of the disk (2) and a mixture which reduces the cooling efficiency.

Turbine disk cooling device

A gas turbine compressor casing has two inner and outer envelopes forming at least one closed cavity and a locking or clamping ring having a thermal inertia higher than that of the envelopes and mounted in the closed cavity in such a way as to limit its contraction during a lowering of the temperature. The thermal inertia difference can be obtained by using for the locking ring a material having a thermal expansion coefficient lower than the coefficient of the envelopes. It can also be controlled by a ventilation means device for ensuring hot air flow in the cavity.

Device for checking the clearances of a gas turbine compressor casing

The adjustment of clearances at the time of assembly and subsequently during operation of a labyrinth seal lying between the rotor and stator of a turbomachine is effected by radial displacements of a bush radially rigid with an outer pivot pin of each blade of the stator and co-operates with a boss of the casing by means of screw-threads. Such displacements are controlled as a function of a signal provided by a computer which integrates various operational parameters of the turbomachine and acts on a control ring connected by a lever to the said bush. The internal pivot of the blade is rigid with an annular member which carries a layer of abradable material constituting a fixed part of the labyrinth seal. The rotary part of the labyrinth seal is mounted on an opposed part of the rotor. A method for effecting the adjustment of the clearances is also described.

Labyrinth seal adjustment device for incorporation in a turbomachine

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Fontainebleau, France

Gerard Jacques Stangalini