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

Other

General Electric Company

Snecma

Daniel J Marey

Jean-Louis Charbonnel

Jacky S Naudet

Pierre Debeneix

Thierry J Niclot

Yann J Rigaud

Christopher Charles Glynn

Roger C Walker

Gerard G Miraucourt

Jean-Claude L Delonge

Jerome M Friedel

Michel R Ayache

Fabrice Marois

Jean-Jacques R Orsini

Yassin Bouhennicha

Alain Marc Lucien Bromann

Jean-Pierre A Mourlan

L&eacute;opold Jean Marie De Verduzan

Gerard Receveur

Alain M Bromann

High-pressure turbine stator ring for a turbine engine

A heating or cooling apparatus for a turbo-machine housing collar that adjusts the diameter of the housing using chambers that are arcs of a circle through which gas is blown onto the ribs of the housing. The gas circulates in a counterflow direction or in alternate directions for adjacent chambers in order to equalize the blowing conditions at every paint of the ribs.

Apparatus for heating or cooling a circular housing

This ventilation apparatus uses gas under pressure diverted from a cooler area of the turbine that reaches a chamber and (8) successively passes through a cover (6) perforated with flow-restricting apertures (13), and then a wall (7) perforated with distribution apertures (12) before reaching a stator ring exposed to the heat that must be cooled, that economizes the ventilation gas due to the almost unperforated cover (6). This construction can be fitted to high pressure turbine stator rings. The cover and the wall form a single unit and the apertures restricting the flow are in the form of nozzles opening into the volume formed by the unit.

Apparatus for ventilating a turbine stator ring

A turbine engine includes a ferrule formed of a plurality of ferrule elements in the shape of circular sectors, each bearing on one internal face thereof fixed vanes and a circular housing surrounding the ferrule. The turbine has a support ring including a plurality of circular ring sectors each secured to the housing and having a U-shaped section whose opening is directed towards the ferrule, each ferrule element includes a hooking mechanism (9a) to be introduced into the opening of at least one ring sector so as to integrally connect the ring sector and the ferrule element.

Turbine engine equipped with means for controlling the play between the

A system for locking the radial extremity of vanes, wherein the extremities include heels situated behind a ring for delimiting the flow of gases, the heels including hooks between which extend other hooks of the ring. Bolts are disposed in the notches of both types of hooks and fasteners are used to secure the bolts. The assembly obtained is compact, rigid and able to be embodied easily and effectively. It is also virtually free of clearances and vibrations.

Vane extremity locking system

A control ring for a stage of pivotable vanes on the stator of a turbomachine carries a plurality of adjustable shoes for contacting a circular surface to set and maintain the coaxiality of the control ring during rotation thereof to pivot the vanes. The radial position of each shoe is adjusted by virtue of a double screw having two screw-threaded portions, one engaging with an internally threaded portion of a bush fixed to the control ring and the other engaging with an internally threaded portion of a shoe-holder which is mounted slidably and non-rotatably in the bush, the two screw-threaded portions having slightly different pitches so as to permit very fine adjustment of the shoe postion.

Rotationally guided control ring for pivotable vanes in a turbomachine

A turboshaft engine in which the stator comprises an outer casing surrounding a ring formed by a number of ring elements each having an apertured rib which spaces the element from the casing, the ribs dividing the space between the casing and the ring into separate compartments, and each rib having a sealing element disposed alongside it to cover the apertures and seal one compartment from the next. The casing and the ring are fixed together by virtue of bolts which have their axes inclined to the radial direction so that tightening the bolts causes the casing to press radially on the sealing elements at the same time as pressing them axially against the respective ribs.

Turbomachine stator having a double skin casing including means for

A turbjet engine includes various elements for adjustment of play of the stator by having the stator heated or cooled by a gas. The outer housing to which the ferrule bearing the fixed vane stages is secured may be formed of two skins between which the gas is injected. The ferrule may be composed of sectors extending over one circumference fraction and fixed via their center and simply guided at their extremity; finally, it is possible to provide sealing devices between the outer housing and the support bearing surfaces of the ribs of the ferrule elements. The volume between the ferrule and the housing is then sectioned and is able to receive separate gas feedings for play adjustment.

Turbo aero engine equipped with means facilitating adjustment of plays

Each blade of a stage of variably settable stator blades in a compressor of gas turbine engine is supported at its outer end by a journal which is rotatably mounted in a radial bore in a parallelepipedic journal box of trapezoidal section mounted in a housing of complementary shape formed between connected upstream and downstream rings of the outer casing of the compressor. The blade is held radially in the journal box by two parallel pins arranged longitudinally through the box so as to engage in a peripheral groove extending at least partly around the journal of the blade.

Mounting for variably settable stator blades in a compressor

The device consists of an arm having structure for attachment to the bottom pivot of a stator blade. Stopping elements are provided in the inner stator ring against which the arm can come to rest. The stopping elements consist of the sides of a circumferential notch formed in the inner surface of the inner ring. A C-shaped molding fastened onto the inner ring makes the notch leak-proof.

Safety stop for a variable setting stator blade pivot

A device for moving air from the jet flow of an axial compressor of a gas rbine group, to be conducted along the axis of the group to the turbine to be cooled. The air is moved by a wheel having an outer rim serving as a brace between two adjacent compressor disks and centripetal blading which moves the air through openings formed in the rim, to accelerate it and discharge it into a space surrounding the axis of the compressor.

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Soisy S/Seine, France

Daniel J Marey