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

Philippe J Lefebvre

Robert Kervistin

Gerard Jacques Stangalini

Jacques A Boury

Alain F Teissier

Anne E Bourguignon

A fluid cooled guide vane is disclosed for use in a gas turbine engine which defines a plurality of separate cooling circuits to guide a cooling fluid through the interior of the vane, while at the same time minimizing the pressure drop of the cooling fluid as it passes through the vane. Each cooling circuit has a cooling fluid inlet, a cooling fluid outlet, a cavity and a chamber which is in fluid communication with the cavity and either the fluid cooling inlet, or the fluid cooling outlet. The multiple chambers are located in mounting bases attached at either end of the vane. The mounting bases define the several chambers as well as the cooling fluid inlets. The cooling fluid outlets may either be defined by the mounting bases, or may be formed by rows of orifices through the vane wall in communication with the cavities within the vane.

Guide vane with a plurality of cooling circuits

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

Apparatus associated with a labyrinth seal of a turbo machine for automatically maintaining a desired clearance between lip members and a wear seal of the labyrinth seal over a range of operational states of the turbo machine. The wear seal comprises a first part made of honeycomb material and a second smooth part spaced axially from the first part. An annular carrier supports the wear seal, and a stator supports the carrier, thereby defining between the carrier and the stator an annular chamber having radially outer orifices for admission of an air supply to the chamber. An annular sheet member disposed within the annular chamber has a plurality of holes and is spaced at a small distance from the carrier. Whereas acceleration and deceleration of the turbo machine normally would tend to alter the spacing of the wear seal and the lip members, the structure recited above corrects for this effect, thereby maintaining a desired clearance between the wear seal and the lip members.

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Chennevieres, France

Philippe J Lefebvre