EP0274293A1 - Air intake housing for a turbo machine with radial struts - Google Patents

Air intake housing for a turbo machine with radial struts Download PDF

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Publication number
EP0274293A1
EP0274293A1 EP19870402659 EP87402659A EP0274293A1 EP 0274293 A1 EP0274293 A1 EP 0274293A1 EP 19870402659 EP19870402659 EP 19870402659 EP 87402659 A EP87402659 A EP 87402659A EP 0274293 A1 EP0274293 A1 EP 0274293A1
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EP
European Patent Office
Prior art keywords
tie rod
turbomachine
arm
carried
hub
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP19870402659
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German (de)
French (fr)
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EP0274293B1 (en
Inventor
Jean-Pierre 431 allée Marquise de Sévigné Ruis
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Definitions

  • the present invention relates to a turbomachine inlet casing of the double flow type comprising radiating arms composed of a fixed part and an associated flap with variable setting and of the type with cantilever mounting without support bearing.
  • French patent applications 86-07369 and 86-08016 present examples of mounting such an inlet casing and more particularly describe embodiments of the device for controlling said flaps.
  • each arm comprises a metal tie rod forming a central core and disposed between an outer ferrule and an inner hub on which it is fixed by a nut on which a tightening is exerted so as to obtain a prestressing of the tie rod.
  • the turbomachine inlet casing produced according to the invention and shown in FIGS. 1 and 2 comprises an outer shell 1 composed of an upstream shell 1a and a downstream shell 1b, upstream and downstream being defined with respect to the direction of circulation in the main stream of gas from the turbomachine.
  • the upstream shell 1a has an upstream flange 2 and a row of bosses 3 peripherally and uniformly distributed. Each boss 3 is capped by a cap 4.
  • the upstream shell 1a On its radially internal face, the upstream shell 1a has a recess 1c in the bottom of which a cutout 1d is formed which extends on the external face between two yokes 1e.
  • the upstream ferrule 1a is secured to the downstream ferrule 1b by means of two flanges 5 and 6 respectively.
  • the downstream ferrule 1b also includes a downstream flange 7, an annular external platform 8. At the level of the flange 7 is provided the connection to a flange of the adjacent casing.
  • the internal wall 9 of the downstream shell 1b is spherical and its function will be specified below.
  • each ferrule respectively has a row of half-bosses, respectively 10 and 11, cooperating, peripherally and uniformly distributed.
  • the inlet casing is associated with a hub 12 consisting of a plurality of metallic inserts 13 each comprising two radial bores upstream 14 and downstream 15. These inserts are embedded in layers 16 of wound filaments, as this is visible for example in Figure 2.
  • the upstream flange 17 of the hub 12 forms an annular lip in which is formed a groove 18 open towards the rear.
  • the downstream flange 19 also has a groove 20 open towards the rear.
  • the turbomachine Downstream of the inlet casing, the turbomachine comprises a rotating compression rotor stage, a blade 21 and the disc 22 are partially shown in FIG. 1. On the disc 22 is fixed a rotating internal cover 23, placed inside of the hub 12.
  • the internal cover 23 has an upstream flange 24 which carries a sealing wiper 25 engaged in the groove 18 of the hub and it likewise comprises a downstream flange 25 which carries a sealing wiper 26 engaged in the groove 20 of the hub 12.
  • a plurality of radiating arms 27 which may be according to the embodiment shown sixteen in number. These arms 27 each consist of an upstream fixed part 27a and a downstream movable part forming a movable flap 27b.
  • Each movable flap 27b has a radially internal pivot 28 capable of rotating inside the downstream bore 15 of the insert 13 of the hub 12 in which it is placed.
  • the movable flap 27b also includes a radially external pivot 29, associated for example with a bushing 30.
  • the pivot 29 and the bushing 30 are placed in a bore 31 formed by the two half-bosses 10 and 11 of the outer shroud 1.
  • head of each external pivot 29 is fixed, for example by means of a bolt 32, the end of a lever 33 connected at its other end, by means of a pin 34, to a ring 35 for control and synchronization movable flaps 27b.
  • An actuating means of a known type for example a jack (not shown in the drawing) is associated with said control ring 35.
  • the pins 34 are housed in a support 36 which rests and slides on the platform 8 of the downstream ferrule 1b.
  • the fixed arm part 27a is composed of a metallic core constituting a tie rod 37 for fixing, surrounded by a sheath 38 of composite material, itself covered with a skin, on the lower side 39 and upper side 40, which can be either metallic or also made of composite material.
  • the head 37a of a tie rod 37 is fixed between the two yokes 1e carried by the outer shell 1 by means of an axis 41.
  • the foot 37b of a tie rod 37 is placed in the upstream bore 14 of an insert 13 of the hub 12 and it ends in a threaded part 37c cooperating with a tightening nut 42.
  • the radially outer apex of the fixed part 27a of the casing arms 27 is first embedded in the recess 1c on the inner face of the upstream shell 1a.
  • a tie rod 37 is inserted from the inside into the composite assembly 38-39-40 of the arm, it slides until it comes to place the head 37a of the tie rod between the two yokes 1e to which it is secured by the axis 41.
  • L 'nut 42 is placed on the foot 37b of the tie without tightening. All the fixed parts 27a of the arms 27 and all the tie rods 37 are thus successively mounted between the upstream ferrule 1a and the hub 12.
  • the internal pivots 28 and the external pivots 29 of the movable flaps 27b are successively and respectively placed in the downstream bores 15 of the inserts 13 of the hub 12 and in the half-bosses 10 of the upstream shell 1a.
  • the upstream ferrules 1a and downstream 1b are then assembled at their respective flanges 5 and 6, the half-bosses 11 of the downstream ferrule 1b covering the external pivots 29 and sockets 30 of the movable flaps 27b.
  • the nuts 42 are then tightened so as to obtain a prestressing of the tie rods 37.
  • the internal cover 23 is also fixed to the disc 22 of the rotor.
  • the assembly of the inlet casing is then assembled at the level of the cooperating flanges of the outer shroud and of the adjacent turbomachine casing, taking care to correctly engage the sealing wipers 25 and 26 of the cover 22 in the corresponding grooves 18 and 20 from hub 12.
  • F1 is the aerodynamic force applied to the movable flaps 27b.
  • the prestressing obtained by the tightening mentioned above which is applied to the nuts 42 for fixing the tie rods 37 can be broken down into an axial component F2 and a radial component F3.
  • the radial component F3 is a force taken up by the winding of the internal hub 12.
  • an electrical resistance can be placed in the sheath 38, respectively 43 upstream side and 44 downstream side.
  • the connections 43a and 44a of these resistors are then placed on the cap 4, connecting them to the incoming electrical conductors 45 and 46.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Un carter d'entrée de turbomachine comporte une virole extérieure (1) supportant des bras rayonnants (27) composés d'une partie fixe (27a) et d'un volet mobile (27b) associé. Chaque bras (27) comporte en outre un tirant métallique (37) dont la tête (37a) radialement externe est solidaire de deux chapes (1e) portées par la virole externe (1) et dont le pied (37b) coopère avec un insert métallique (13) noyé dans les couches (16) de filaments bobinés en matérieu composite, constituant ainsi un moyeu flottant (12) porté par les tirants (37). Le pied (37b) de tirant est fixé sur l'insert (13) par un écrou (42) qui assure un serrage en précontrainte du tirant lors du montage.A turbomachine inlet casing includes an outer shroud (1) supporting radiating arms (27) composed of a fixed part (27a) and an associated movable flap (27b). Each arm (27) further comprises a metal tie rod (37) whose radially outer head (37a) is integral with two yokes (1e) carried by the outer ferrule (1) and whose foot (37b) cooperates with a metallic insert (13) embedded in the layers (16) of filaments wound in composite material, thus constituting a floating hub (12) carried by the tie rods (37). The foot (37b) of the tie rod is fixed on the insert (13) by a nut (42) which ensures a pre-stressed tightening of the tie rod during assembly.

Description

La présente invention concerne un carter d'entrée de turbomachine à double flux du genre comportant des bras rayonnants composés d'une partie fixe et d'un volet associé à calage variable et du type à montage en porte-à-­faux sans palier support.The present invention relates to a turbomachine inlet casing of the double flow type comprising radiating arms composed of a fixed part and an associated flap with variable setting and of the type with cantilever mounting without support bearing.

Les demandes de brevet français 86-07369 et 86-08016 présentent des exemples de montage de carter d'entrée de ce genre et décrivent plus particulièrement des réalisations du dispositif de commande desdits volets.French patent applications 86-07369 and 86-08016 present examples of mounting such an inlet casing and more particularly describe embodiments of the device for controlling said flaps.

En fonctionnement, dans une construction de ce type, des efforts aérodynamiques importants se développent et s'exercent sur lesdits volets mobiles. Par ailleurs, la recherche d'une réduction de masse, particulièrement avantageuse dans les applications aéronautiques, amène, compte-tenu des développements récents de nouveaux matériaux, à prévoir la réalisation des bras de carter et du moyeu, auquel ils sont reliés, en matériaux composites.In operation, in a construction of this type, significant aerodynamic forces develop and are exerted on said movable flaps. In addition, the search for a reduction in mass, particularly advantageous in aeronautical applications, leads, in view of recent developments in new materials, to provide for the production of the casing arms and of the hub, to which they are connected, in materials composites.

L'invention vise à permettre ces choix de matériaux et à obtenir une compensation des efforts aérodynamiques exercés sur les volets mobiles des bras par des moyens de reprise desdits efforts. Ces résultats sont obtenus par un carter d'entrée du genre précité, conforme à l'invention, caractérisé en ce que chaque bras comporte un tirant métallique formant une âme centrale et disposé entre une virole extérieure et un moyeu intérieur sur lequel il est fixé par un écrou sur lequel un serrage est exercé de manière à obtenir une mise en précontrainte du tirant.The invention aims to allow these choices of materials and to obtain compensation for the aerodynamic forces exerted on the movable flaps of the arms by means for taking up said forces. These results are obtained by an inlet casing of the aforementioned type, in accordance with the invention, characterized in that each arm comprises a metal tie rod forming a central core and disposed between an outer ferrule and an inner hub on which it is fixed by a nut on which a tightening is exerted so as to obtain a prestressing of the tie rod.

D'autres caractéristiques et avantages de l'invention ressortent de la description qui va suivre d'un mode de réalisation de l'invention, en référence aux dessins annexés, sur lesquels :

  • - la figure 1 représente une demi-vue, en coupe longitudinale par un plan passant par l'axe de rotation d'une turbomachine, d'un carter d'entrée de turbomachine conforme à l'invention ;
  • - la figure 2 représente une vue partielle en coupe transversale par rapport à la turbomachine, au niveau d'un bras de carter, selon la ligne II-II du carter d'entrée représenté à la figure 1 ;
  • - la figure 3a représente une vue schématique analogue à la figure 1 du carter d'entrée montrant la répartition des efforts s'exerçant sur un bras de carter ;
  • - la figure 3b représente une vue schématique d'une section selon la ligne III-III de la figure 3a.
Other characteristics and advantages of the invention emerge from the description which follows of a mode of embodiment of the invention, with reference to the accompanying drawings, in which:
  • - Figure 1 shows a half view, in longitudinal section through a plane passing through the axis of rotation of a turbomachine, of a turbomachine inlet casing according to the invention;
  • - Figure 2 shows a partial view in cross section with respect to the turbomachine, at the level of a casing arm, along line II-II of the inlet casing shown in Figure 1;
  • - Figure 3a shows a schematic view similar to Figure 1 of the inlet housing showing the distribution of forces exerted on a housing arm;
  • - Figure 3b shows a schematic view of a section along line III-III of Figure 3a.

Le carter d'entrée de turbomachine réalisé selon l'invention et représenté sur les figures 1 et 2 comporte une virole extérieure 1 composée d'une virole amont 1a et d'une virole aval 1b, amont et aval étant définis par rapport au sens de circulation dans la veine principale des gaz de la turbomachine. La virole amont 1a comporte une bride amont 2 et une rangée de bossages 3 périphériquement et uniformément répartis. Chaque bossage 3 est coiffé par un chapeau 4.The turbomachine inlet casing produced according to the invention and shown in FIGS. 1 and 2 comprises an outer shell 1 composed of an upstream shell 1a and a downstream shell 1b, upstream and downstream being defined with respect to the direction of circulation in the main stream of gas from the turbomachine. The upstream shell 1a has an upstream flange 2 and a row of bosses 3 peripherally and uniformly distributed. Each boss 3 is capped by a cap 4.

Sur sa face radialement interne, la virole amont 1a comporte un évidement 1c dans le fond duquel est ménagée une découpe 1d qui se prolonge sur la face extérieure entre deux chapes 1e.On its radially internal face, the upstream shell 1a has a recess 1c in the bottom of which a cutout 1d is formed which extends on the external face between two yokes 1e.

La virole amont 1a est solidarisée avec 1a virole aval 1b au moyen de deux brides respectivement 5 et 6. La virole aval 1b comporte également une bride aval 7, une plateforme 8 externe annulaire. Au niveau de la bride 7 est assurée la liaison à une bride du carter adjacent. La paroi interne 9 de la virole aval 1b est sphérique et sa fonction sera précisée plus loin. Au niveau du plan de joint entre les viroles amont 1a et aval 1b, chaque virole comporte respectivement une rangée de demi-bossages, respectivement 10 et 11, coopérants, périphériquement et uniformément répartis. Du côté radialement interne, le carter d'entrée est associé à un moyeu 12 constitué d'une pluralité d'inserts métalliques 13 comportant chacun deux alésages radiaux amont 14 et aval 15. Ces inserts sont noyés dans des couches 16 de filaments bobinés, comme cela est visible par exemple sur la figure 2. Le rebord amont 17 du moyeu 12 forme une lèvre annulaire dans laquelle est ménagée une gorge 18 ouverte vers l'arrière. De même le rebord aval 19 comporte également une gorge 20 ouverte vers l'arrière. En aval du carter d'entrée, la turbomachine comporte un étage rotorique tournant de compression dont une aube 21 et le disque 22 sont partiellement représentés sur la figure 1. Sur le disque 22 est fixé un capot interne tournant 23, placé à l'intérieur du moyeu 12. Le capot interne 23 comporte un rebord amont 24 qui porte une léchette d'étanchéité 25 engagée dans la gorge 18 du moyeu et il comporte de même un rebord aval 25 qui porte une léchette d'étanchéité 26 engagée dans la gorge 20 du moyeu 12. Entre la virole extérieure 1 et le moyeu interne 12 sont montés une pluralité de bras rayonnants 27, qui peuvent être selon le mode de réalisation représenté au nombre de seize. Ces bras 27 sont constitués chacun d'une partie fixe amont 27a et d'une partie mobile aval formant un volet mobile 27b.The upstream ferrule 1a is secured to the downstream ferrule 1b by means of two flanges 5 and 6 respectively. The downstream ferrule 1b also includes a downstream flange 7, an annular external platform 8. At the level of the flange 7 is provided the connection to a flange of the adjacent casing. The internal wall 9 of the downstream shell 1b is spherical and its function will be specified below. At the joint plane between the upstream ferrules 1a and downstream 1b, each ferrule respectively has a row of half-bosses, respectively 10 and 11, cooperating, peripherally and uniformly distributed. On the radially internal side, the inlet casing is associated with a hub 12 consisting of a plurality of metallic inserts 13 each comprising two radial bores upstream 14 and downstream 15. These inserts are embedded in layers 16 of wound filaments, as this is visible for example in Figure 2. The upstream flange 17 of the hub 12 forms an annular lip in which is formed a groove 18 open towards the rear. Similarly, the downstream flange 19 also has a groove 20 open towards the rear. Downstream of the inlet casing, the turbomachine comprises a rotating compression rotor stage, a blade 21 and the disc 22 are partially shown in FIG. 1. On the disc 22 is fixed a rotating internal cover 23, placed inside of the hub 12. The internal cover 23 has an upstream flange 24 which carries a sealing wiper 25 engaged in the groove 18 of the hub and it likewise comprises a downstream flange 25 which carries a sealing wiper 26 engaged in the groove 20 of the hub 12. Between the outer shroud 1 and the inner hub 12 are mounted a plurality of radiating arms 27, which may be according to the embodiment shown sixteen in number. These arms 27 each consist of an upstream fixed part 27a and a downstream movable part forming a movable flap 27b.

Chaque volet mobile 27b comporte un pivot radialement interne 28 susceptible de tourner à l'intérieur de l'alésage aval 15 de l'insert 13 du moyeu 12 dans lequel il est placé. Le volet mobile 27b comporte également un pivot radialement externe 29, associé par exemple à une douille 30. Le pivot 29 et la douille 30 sont placés dans un alésage 31 formé par les deux demi-bossages 10 et 11 de la virole extérieure 1. En tête de chaque pivot externe 29 est fixé, par exemple au moyen d'un boulon 32, l'extrémité d'un levier 33 relié à son autre extrémité, au moyen d'un axe 34, à un anneau 35 de commande et de synchronisation des volets mobiles 27b. Un moyen d'actionnement d'un type connu, par exemple un vérin (non représenté au dessin) est associé audit anneau de commande 35. Les axes 34 sont logés dans un support 36 qui repose et coulisse sur la plateforme 8 de la virole aval 1b. Lors du braquage des volets mobiles 27b, un jeu radial minimal est conservé entre les sommets de volets et la paroi interne 9 de la virole aval 1b, du fait de la forme sphérique de cette dernière qui a été précédemment décrite. La partie fixe 27a de bras est composée d'une âme métallique constituant un tirant 37 de fixation, entourée d'une gaine 38 en matériau composite, elle-même recouverte d'une peau, côté intrados 39 et côté extrados 40, qui peut être soit métallique, soit également en matériau composite. La tête 37a d'un tirant 37 est fixée entre les deux chapes 1e portées par la virole extérieure 1 au moyen d'un axe 41. Le pied 37b d'un tirant 37 est placé dans l'alésage amont 14 d'un insert 13 du moyeu 12 et il se termine par une partie filetée 37c coopérant avec un écrou de serrage 42. On va maintenant décrire le mode de montage du carter d'entrée de turbomachine qui vient d'être décrit et examiner la répartition des efforts s'exerçant en fonctionnement d'où il ressort quelques-uns des avantages de la présente invention.Each movable flap 27b has a radially internal pivot 28 capable of rotating inside the downstream bore 15 of the insert 13 of the hub 12 in which it is placed. The movable flap 27b also includes a radially external pivot 29, associated for example with a bushing 30. The pivot 29 and the bushing 30 are placed in a bore 31 formed by the two half-bosses 10 and 11 of the outer shroud 1. By head of each external pivot 29 is fixed, for example by means of a bolt 32, the end of a lever 33 connected at its other end, by means of a pin 34, to a ring 35 for control and synchronization movable flaps 27b. An actuating means of a known type, for example a jack (not shown in the drawing) is associated with said control ring 35. The pins 34 are housed in a support 36 which rests and slides on the platform 8 of the downstream ferrule 1b. During the turning of the movable flaps 27b, a minimum radial clearance is preserved between the vertices of the flaps and the internal wall 9 of the downstream shell 1b, due to the spherical shape of the latter which has been previously described. The fixed arm part 27a is composed of a metallic core constituting a tie rod 37 for fixing, surrounded by a sheath 38 of composite material, itself covered with a skin, on the lower side 39 and upper side 40, which can be either metallic or also made of composite material. The head 37a of a tie rod 37 is fixed between the two yokes 1e carried by the outer shell 1 by means of an axis 41. The foot 37b of a tie rod 37 is placed in the upstream bore 14 of an insert 13 of the hub 12 and it ends in a threaded part 37c cooperating with a tightening nut 42. We will now describe the method of mounting the turbomachine inlet casing which has just been described and examine the distribution of the forces exerted in operation from which some of the advantages emerge of the present invention.

Pour le montage, le sommet radialement externe de la partie fixe 27a des bras 27 de carter est d'abord encastré dans l'évidement 1c de la face interne de la virole amont 1a. Un tirant 37 est introduit par l'intérieur dans l'ensemble composite 38-39-40 du bras, il coulisse jusqu'à venir placer la tête 37a du tirant entre les deux chapes 1e auxquelles il est solidarisé par l'axe 41. L'écrou 42 est placé sur le pied 37b du tirant sans serrage. Toutes les parties fixes 27a des bras 27 et tous les tirants 37 sont ainsi successivement montés entre la virole amont 1a et le moyeu 12. Puis les pivots internes 28 et les pivots externes 29 des volets mobiles 27b sont successivement et respectivement placés dans les alésages avals 15 des inserts 13 du moyeu 12 et dans les demi-bossages 10 de la virole amont 1a. Les viroles amont 1a et aval 1b sont alors assemblées au niveau de leurs brides respectives 5 et 6, les demi-bossages 11 de la virole aval 1b venant coiffer les pivots externes 29 et douilles 30 des volets mobiles 27b. Les écrous 42 sont alors serrés de manière à obtenir une mise en précontrainte des tirants 37. Indépendamment, le capot interne 23 est également fixé sur le disque 22 du rotor. L'ensemble du carter d'entrée est alors assemblé au niveau des brides coopérantes de la virole extérieure et du carter de turbomachine adjacent, en prenant soin d'engager correctement les léchettes d'étanchéité 25 et 26 du capot 22 dans les gorges correspondantes 18 et 20 du moyeu 12.For mounting, the radially outer apex of the fixed part 27a of the casing arms 27 is first embedded in the recess 1c on the inner face of the upstream shell 1a. A tie rod 37 is inserted from the inside into the composite assembly 38-39-40 of the arm, it slides until it comes to place the head 37a of the tie rod between the two yokes 1e to which it is secured by the axis 41. L 'nut 42 is placed on the foot 37b of the tie without tightening. All the fixed parts 27a of the arms 27 and all the tie rods 37 are thus successively mounted between the upstream ferrule 1a and the hub 12. Then the internal pivots 28 and the external pivots 29 of the movable flaps 27b are successively and respectively placed in the downstream bores 15 of the inserts 13 of the hub 12 and in the half-bosses 10 of the upstream shell 1a. The upstream ferrules 1a and downstream 1b are then assembled at their respective flanges 5 and 6, the half-bosses 11 of the downstream ferrule 1b covering the external pivots 29 and sockets 30 of the movable flaps 27b. The nuts 42 are then tightened so as to obtain a prestressing of the tie rods 37. Independently, the internal cover 23 is also fixed to the disc 22 of the rotor. The assembly of the inlet casing is then assembled at the level of the cooperating flanges of the outer shroud and of the adjacent turbomachine casing, taking care to correctly engage the sealing wipers 25 and 26 of the cover 22 in the corresponding grooves 18 and 20 from hub 12.

On a représenté schématiquement sur les figures 3a et 3b les efforts s'exerçant sur le carter d'entrée en fonctionnement. F1 est l'effort aérodynamique appliqué sur les volets mobiles 27b. La mise en précontrainte obtenue par le serrage mentionné ci-dessus qui est appliqué sur les écrous 42 de fixation des tirants 37 peut se décomposer en une composante axiale F2 et une composante radiale F3. La composante radiale F3 est un effort repris par le bobinage du moyeu interne 12.Schematically shown in Figures 3a and 3b the forces exerted on the input housing in operation. F1 is the aerodynamic force applied to the movable flaps 27b. The prestressing obtained by the tightening mentioned above which is applied to the nuts 42 for fixing the tie rods 37 can be broken down into an axial component F2 and a radial component F3. The radial component F3 is a force taken up by the winding of the internal hub 12.

La composante axiale F2 est un effort repris par le volet mobile 27b. Cet effort de sens contraire à l'effort F1 compense ainsi en fonctionnement, partiellement, l'effort aérodynamique F1. Selon le niveau de précontrainte appliqué au tirant 37, on peut par exemple dans un mode de réalisation obtenir une compensation F₂ = F1/2.The axial component F2 is a force taken up by the movable flap 27b. This effort of direction opposite to the effort F1 thus compensates in operation, partially, for the aerodynamic effort F1. Depending on the level of prestressing applied to the tie rod 37, it is possible for example in one embodiment to obtain compensation F₂ = F1 / 2.

D'autres dispositions complémentaires peuvent en variante être appliquées au carter d'entrée selon l'invention. Ainsi, de part et d'autre du tirant 37, une résistance électrique peut être placée dans la gaine 38, respectivement 43 côté amont et 44 côté aval. Les connexions 43a et 44a de ces résistances sont alors placées sur le chapeau 4, les reliant aux conducteurs électriques d'arrivée 45 et 46 . Ces éléments constituent un système de dégivrage électrique utilisable en fonction des conditions de fonctionnement de la turbomachine, en particulier pour des applications aéronautiques.Other complementary provisions may alternatively be applied to the inlet casing according to the invention. Thus, on either side of the tie rod 37, an electrical resistance can be placed in the sheath 38, respectively 43 upstream side and 44 downstream side. The connections 43a and 44a of these resistors are then placed on the cap 4, connecting them to the incoming electrical conductors 45 and 46. These elements constitute an electrical deicing system which can be used as a function of the operating conditions of the turbomachine, in particular for aeronautical applications.

Claims (6)

1. - Carter d'entrée de turbomachine à double flux du genre comportant des bras rayonnants (27) composés d'une partie fixe (27a) et d'un volet (27b) associé à calage variable et du type à montage en porte-à-faux sans palier support caractérisé en ce que chaque bras (27b) comporte un tirant métallique (37) formant une âme centrale et disposé entre une virole extérieure (1) et un moyeu intérieur (12) sur lequel il est fixé par un écrou (42), ledit tirant (37) étant mis en précontrainte par serrage dudit écrou (42).1. - Input casing of a turbomachine with double flow of the type comprising radiating arms (27) composed of a fixed part (27a) and of a flap (27b) associated with variable setting and of the door-mounting type overhang without support bearing characterized in that each arm (27b) comprises a metal tie rod (37) forming a central core and disposed between an outer ferrule (1) and an inner hub (12) on which it is fixed by a nut (42), said tie rod (37) being prestressed by tightening said nut (42). 2. - Carter d'entrée de turbomachine selon la revendication 1 caractérisé en ce que ledit tirant (37) de chaque bras (27) est entouré d'une gaine (38) en matériaux composites recouverte du côté intrados et du côté extrados d'une peau en matériau composite (39,40).2. - turbomachine inlet casing according to claim 1 characterized in that said tie rod (37) of each arm (27) is surrounded by a sheath (38) made of composite materials covered on the pressure side and on the suction side of a composite material skin (39.40). 3. - Carter d'entrée de turbomachine selon la revendication 1 caractérisé en ce que ledit tirant (37) de chaque bras (27) est entouré d'une gaine (38) en matériaux composites recouverte du côté intrados et du côté extrados d'une peau métallique (39,40).3. - turbomachine inlet casing according to claim 1 characterized in that said tie rod (37) of each arm (27) is surrounded by a sheath (38) made of composite materials covered on the pressure side and on the suction side of a metallic skin (39.40). 4. - Carter d'entrée de turbomachine selon l'une quelconque des revendications 1 à 3 caractérisé en ce que la tête (37a) radialement externe de chaque tirant (37) est placée entre deux chapes (1e) portées par la virole extérieure (1) et auxquelles ladite tête (37a) de tirant est solidarisée par un axe (41).4. - turbomachine inlet casing according to any one of claims 1 to 3 characterized in that the head (37a) radially external of each tie rod (37) is placed between two yokes (1e) carried by the outer shell ( 1) and to which said drawing head (37a) is secured by an axis (41). 5. - Carter d'entrée de turbomachine selon l'une quelconque des revendications 1 à 4 caractérisé en ce que ledit moyeu (12) intérieur est constitué d'inserts métalliques (13), chaque tirant (37) coopérant avec un insert (13), lesdits inserts (13) étant noyés dans des couches (16) superposées de filaments en matériau composite bobinés, de telle sorte que ledit moyeu (12) est du type flottant et est porté par lesdits tirants (37).5. - turbomachine inlet housing according to any one of claims 1 to 4 characterized in that said inner hub (12) consists of inserts metallic (13), each tie rod (37) cooperating with an insert (13), said inserts (13) being embedded in layers (16) superimposed of filaments of composite material wound, so that said hub (12) is floating type and is carried by said tie rods (37). 6. - Carter d'entrée de turbomachine selon la revendication 5 caractérisé en ce que ledit moyeu (12) intérieur comporte, d'une part, une lèvre amont (17) dans laquelle est ménagée une gorge (18) où se place une léchette (25) d'étanchéité portée par un capot (23) fixé sur le disque (22) du rotor de soufflante et, d'autre part, une lèvre aval (19) dans laquelle est ménagée également une gorge (20) où se place une léchette (26) d'étanchéité également solidaire dudit capot (23).6. - turbomachine inlet housing according to claim 5 characterized in that said inner hub (12) comprises, on the one hand, an upstream lip (17) in which is formed a groove (18) where a wiper is placed (25) sealing carried by a cover (23) fixed on the disc (22) of the fan rotor and, on the other hand, a downstream lip (19) in which is also formed a groove (20) where is placed a sealing wiper (26) also integral with said cover (23).
EP19870402659 1986-11-26 1987-11-25 Air intake housing for a turbo machine with radial struts Expired - Lifetime EP0274293B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8616449A FR2607188B1 (en) 1986-11-26 1986-11-26 TURBOMACHINE INPUT CASING WITH RADIANT ARMS
FR8616449 1986-11-26

Publications (2)

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EP0274293A1 true EP0274293A1 (en) 1988-07-13
EP0274293B1 EP0274293B1 (en) 1990-04-11

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US (1) US4821758A (en)
EP (1) EP0274293B1 (en)
DE (1) DE3762257D1 (en)
FR (1) FR2607188B1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2266562A (en) * 1992-04-23 1993-11-03 Turbo Propulsores Ind Gas turbine engine variable stator vane assembly.
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
FR2714109A1 (en) * 1993-12-22 1995-06-23 Snecma Turbomachine blade with variable camber.
EP2083174A1 (en) 2008-01-25 2009-07-29 Siemens Aktiengesellschaft Inlet guide vane for a gas compressor

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4212878A1 (en) * 1992-04-17 1993-03-18 Daimler Benz Ag Adjustable guide vane ring - is located in ring-shaped channel, with cross section decreasing in direction of flow
GB2339244B (en) 1998-06-19 2002-12-18 Rolls Royce Plc A variable camber vane
US6619916B1 (en) * 2002-02-28 2003-09-16 General Electric Company Methods and apparatus for varying gas turbine engine inlet air flow
US6725645B1 (en) * 2002-10-03 2004-04-27 General Electric Company Turbofan engine internal anti-ice device
FR2857699B1 (en) 2003-07-17 2007-06-29 Snecma Moteurs DEFROSTING DEVICE FOR TURBOMACHINE INPUT DIRECTION WHEEL DARK, DAWN WITH SUCH A DEFROSTING DEVICE, AND AIRCRAFT ENGINE EQUIPPED WITH SUCH AUBES
US7246480B2 (en) * 2004-11-04 2007-07-24 Siemens Power Generation, Inc. System for heating an air intake of turbine engine
US7230205B2 (en) * 2005-03-29 2007-06-12 Siemens Power Generation, Inc. Compressor airfoil surface wetting and icing detection system
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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR57426E (en) * 1946-01-11 1953-01-28 Improvements to gas turbines
GB774501A (en) * 1953-10-15 1957-05-08 Power Jets Res & Dev Ltd A stator guide vane construction for elastic fluid turbines
US2807433A (en) * 1952-07-10 1957-09-24 Havilland Engine Co Ltd Stationary blade rings of axial flow turbines or compressors
US3224666A (en) * 1963-04-16 1965-12-21 Svenska Aeroplan Ab Rotary fan arrangement
GB1023766A (en) * 1964-02-14 1966-03-23 Bristol Siddeley Engines Ltd Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
FR2526485A1 (en) * 1982-05-07 1983-11-10 Snecma Inlet for turbomachine - has movable front section to vary pitch angle of blades on support sleeve

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR57426E (en) * 1946-01-11 1953-01-28 Improvements to gas turbines
US2807433A (en) * 1952-07-10 1957-09-24 Havilland Engine Co Ltd Stationary blade rings of axial flow turbines or compressors
GB774501A (en) * 1953-10-15 1957-05-08 Power Jets Res & Dev Ltd A stator guide vane construction for elastic fluid turbines
US3224666A (en) * 1963-04-16 1965-12-21 Svenska Aeroplan Ab Rotary fan arrangement
GB1023766A (en) * 1964-02-14 1966-03-23 Bristol Siddeley Engines Ltd Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
FR2526485A1 (en) * 1982-05-07 1983-11-10 Snecma Inlet for turbomachine - has movable front section to vary pitch angle of blades on support sleeve

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
GB2266562A (en) * 1992-04-23 1993-11-03 Turbo Propulsores Ind Gas turbine engine variable stator vane assembly.
GB2266562B (en) * 1992-04-23 1995-10-11 Turbo Propulsores Ind Gas turbine stator vane assembly
FR2714109A1 (en) * 1993-12-22 1995-06-23 Snecma Turbomachine blade with variable camber.
EP0659979A1 (en) * 1993-12-22 1995-06-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Variable camber turbine blade
US5520511A (en) * 1993-12-22 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomachine vane with variable camber
EP2083174A1 (en) 2008-01-25 2009-07-29 Siemens Aktiengesellschaft Inlet guide vane for a gas compressor

Also Published As

Publication number Publication date
FR2607188B1 (en) 1991-02-08
DE3762257D1 (en) 1990-05-17
FR2607188A1 (en) 1988-05-27
EP0274293B1 (en) 1990-04-11
US4821758A (en) 1989-04-18

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