EP0342087A1 - Turbo machine having an entry stator grill with built-in oil passage tubes - Google Patents

Turbo machine having an entry stator grill with built-in oil passage tubes Download PDF

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Publication number
EP0342087A1
EP0342087A1 EP89401184A EP89401184A EP0342087A1 EP 0342087 A1 EP0342087 A1 EP 0342087A1 EP 89401184 A EP89401184 A EP 89401184A EP 89401184 A EP89401184 A EP 89401184A EP 0342087 A1 EP0342087 A1 EP 0342087A1
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EP
European Patent Office
Prior art keywords
arm
oil
oil passage
downstream
tube
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
EP89401184A
Other languages
German (de)
French (fr)
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EP0342087B1 (en
Inventor
Jean-Claude Asselin
Pierre Antoine Glowacki
Daniel Jean-Marie Martin
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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Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids

Definitions

  • the thickness of the arms is itself very reduced, of the order of 8.5 mm at point where it is impossible to accommodate the oil circuit piping of the upstream bearing.
  • a conventional technology consists in making some of the radiating arms with a thicker section than the others.
  • the object of the present invention is to produce an inlet gate structure in which all the arms have the same section and therefore the same thickness, but in which certain arms are still suitable for receiving an oil piping intended for the servitudes of the engine and in particular for the lubrication of the upstream bearing.
  • the invention therefore relates to an aviation turbomachine having an inlet grid formed of radiating arms, support of the inlet casing, arranged between an internal ferrule and an external ferrule, some of them comprising a passage pipe of oil, the grid further comprising variable setting input guidelines, turbomachine in which all the arms of the input grid are of the same section including those comprising an oil passage pipe and of which said radiating arms are in two parts, a first fixed upstream structural part and a second part forming a downstream shutter with variable setting articulated on the upstream structural part and constituting the inlet director.
  • those of the radiating arms which comprise an oil passage pipe have in section their structural part divided into three enclosures separated by two radial partitions, the two upstream enclosures being traversed by hot air flow rates, while the 'downstream enclosure, open over its entire length along the trailing edge is capable of receiving the oil passage manifold.
  • the input guide wheel located upstream of the first stage 2 of the low pressure compressor rotor is made up of 1,1 ′ radial arms arranged between the outer ring 3 of the vein 4 and the internal ferrule 5 secured to the upstream central cone 6 of the engine.
  • the arms 1,1 ′ have an aerodynamic profile comprising a leading edge, a lower surface and an upper surface and comprise an adjustable downstream part formed by a flap 7 mounted rotating on an external pivot 8 and an internal pivot 9 arranged at the inside of bearings 10, the flaps 7 of all the radial arms being controlled in rotation by means of a control ring 11 to which they are connected by connecting rods 12.
  • the blades 1,1 ′ are hollow to allow a circulation of hot air, taken in an air collector 14, intended to prevent icing of the leading edge of the blade and of the central cone 6.
  • the blades 1,1 ′ have an upstream part, located between the leading edge 15 and a downstream partition 15a, which also forms an enclosure 16 reinforced by a rib 17 for the circulation of hot air taken from the manifold 14.
  • the part of the arm 1 located downstream of the partition 15a forms an enclosure 21 open over its entire length downstream to receive the tube 13 for the passage of oil.
  • FIG. 2 shows the example of an oil return organized according to the invention.
  • the internal ferrule of the inlet grille comprises an oil collector 18 which receives the recovery oil from the bearing P, said collector opening radially at the level of an arm 1 having an oil tube 13, in a cylindrical housing 19 receiving an end piece 20 of the tube 13 of the arm.
  • the downstream enclosure 21 of the structural arm is integral with the housing 22 of the external pivot of the downstream flap and said housing 22 comprises (see FIG. 3) a radial cutout 23 making the bore 22 receiving the pivot 8 communicate and the downstream enclosure 21 of the structural arm to allow the insertion by sliding of the tube 13 for the passage of oil into the downstream enclosure of the arm.
  • the tube 13 has a thinned central part of oblong section, internally matching the spindle shape of the structural arm which contains it and bent in three places 24 so as to correspond to the bent shape of the enclosure 21.
  • the thinned central part is connected to welded cylindrical end pieces 20 which each have a seal 25.
  • the external ferrule 3 of the grid receives, to the right of each oil passage pipe, a removable connection 26 comprising a bore coming to be positioned on the external nozzle 20 of the oil pipe, said connection being screwed onto a boss 27 of the outer shell and being hydraulically connected to a pump for recovering the oil circuit (not shown) of the turbomachine.
  • the arm 1 has a groove, or constricted, 28 (see FIGS. 6 to 8) about half of its length, intended to receive a shaped clip 29 of plastic stirrup which is mounted on the rear flanks of the arm at the level of the constriction and provides a double function of fixing the tube 13 in its enclosure 21 and of damping vibrations including sides of the arm, cantilevered, could be the object.
  • the tube 13 is slid into the bore 22 of the pivot of the flap 7, then (FIGS. 10 and 11), it is pushed upstream, parallel to itself, and the end 20 is radially external. of the tube 13 is slid towards its housing through the lumen 21, while the central part of the tube is received in the clip 29. Then, the tube is pushed radially inward until the internal end piece 20 is in place in its housing 19. Finally, the removable connector 26 is positioned, which is screwed onto the boss 27 of the outer shell 3.
  • the arm structure according to the invention allows the inlet grille to have externally identical arms, which constitutes a notable advantage for manufacturing and maintenance and also ensures the elimination of aerodynamic singularities which could exist in the past.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Lubrication Of Internal Combustion Engines (AREA)
  • Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)

Abstract

The turbo-machine according to the invention has an entry blade grill, of which all the arms (1,1') have the same thickness, including those (1) in which is accommodated an oil passage tubing (13), the special structure of which makes mounting in the arms (1) easier, before these receive their downstream variable-setting movable flap (7) forming the entry guide device. <??>The invention is used on aircraft jet engines with a small mainframe. <IMAGE>

Description

La plupart des turbomachines d'aviation actuelles comportent un carter d'entrée avec des bras rayonnants jouant le rôle de support de palier et de directrices d'entrée.Most current aviation turbomachines have an inlet casing with radiating arms acting as a bearing support and inlet directors.

Dans les moteurs d'avion par exemple de type supersonique dont le maître-couple est réduit, de l'ordre de 600 à 800 mm, l'épaisseur des bras est elle-même très réduite, de l'ordre de 8,5mm au point qu'il s'avère impossible d'y loger les tuyauteries de circuit d'huile du palier amont. Pour permettre le passage de ces tuyauteries, une technologie classique consiste à réaliser quelques uns des bras rayonnants avec une section plus épaisse que les autres.In aircraft engines, for example of the supersonic type, the master torque of which is reduced, of the order of 600 to 800 mm, the thickness of the arms is itself very reduced, of the order of 8.5 mm at point where it is impossible to accommodate the oil circuit piping of the upstream bearing. To allow the passage of these pipes, a conventional technology consists in making some of the radiating arms with a thicker section than the others.

Cette technologie a pour inconvénient de créer des distorsions d'entrée et une mauvaise répartition circulaire du flux d'air à l'entrée du compresseur. Par ailleurs, on réalise depuis peu des bras d'entrée en deux parties, l'une en amont fixe et jouant un rôle structural et l'autre en aval mobile, à calage variable servant de directrice d'entrée réglable. Le document FR-A 2 526 485 en est un exemple. FR-A-2 599 086 en montre un autre exemple dans lequel des tubes d'huile sont insérés dans la partie amont des bras dont la structure est classique et comporte un profil aérodynamique fermé délimitant une cavité interne unique. US 3 844 110 (ou son correspondant français FR-A-2 219 312) est un autre exemple de la technologie décrite ci-dessus.This technology has the disadvantage of creating inlet distortions and poor circular distribution of the air flow at the inlet of the compressor. In addition, input arms have recently been produced in two parts, one upstream fixed and playing a structural role and the other downstream mobile, with variable setting serving as adjustable input director. Document FR-A 2,526,485 is an example. FR-A-2 599 086 shows another example in which oil tubes are inserted in the upstream part of the arms, the structure of which is conventional and has a closed aerodynamic profile delimiting a single internal cavity. US 3 844 110 (or its French correspondent FR-A-2 219 312) is another example of the technology described above.

La technologie précitée comportant quelques bras de forte section s'accomode mal à cette structure en deux parties dont une mobile.The aforementioned technology comprising a few arms of large section does not fit well with this structure in two parts, one of which is movable.

La présente invention a pour but de réaliser une structure de grille d'entrée dont tous les bras ont la même section et donc la même épaisseur, mais dont certains bras sont tout de même aptes à recevoir une tuyauterie d'huile destinée aux servitudes du moteur et notamment à la lubrification du palier amont.The object of the present invention is to produce an inlet gate structure in which all the arms have the same section and therefore the same thickness, but in which certain arms are still suitable for receiving an oil piping intended for the servitudes of the engine and in particular for the lubrication of the upstream bearing.

L'invention a donc pour objet une turbomachine d'aviation possédant une grille d'entrée formée de bras rayonnants, support du carter d'entrée, disposés entre une virole interne et une virole externe, certains d'entre eux comportant une tubulure de passage d'huile, la grille comportant en outre des directrices d'entrée à calage variable, turbomachine dans laquelle tous les bras de la grille d'entrée sont de même section y compris ceux comportant une tubulure de passage d'huile et dont lesdits bras rayonnants sont en deux parties, une première partie amont structurale fixe et une seconde partie formant volet aval à calage variable articulée sur la partie structurale amont et constituant la directrice d'entrée.The invention therefore relates to an aviation turbomachine having an inlet grid formed of radiating arms, support of the inlet casing, arranged between an internal ferrule and an external ferrule, some of them comprising a passage pipe of oil, the grid further comprising variable setting input guidelines, turbomachine in which all the arms of the input grid are of the same section including those comprising an oil passage pipe and of which said radiating arms are in two parts, a first fixed upstream structural part and a second part forming a downstream shutter with variable setting articulated on the upstream structural part and constituting the inlet director.

Selon l'invention ceux des bras rayonnants qui comportent une tubulure de passage d'huile ont en section leur partie structurale divisée en trois enceintes séparées par deux cloisons radiales, les deux enceintes amont étant parcourues par des débits d'air chaud, tandis que l'enceinte aval, ouverte sur toute sa longueur le long du bord de fuite est apte à recevoir la tubulure de passage d'huile.According to the invention those of the radiating arms which comprise an oil passage pipe have in section their structural part divided into three enclosures separated by two radial partitions, the two upstream enclosures being traversed by hot air flow rates, while the 'downstream enclosure, open over its entire length along the trailing edge is capable of receiving the oil passage manifold.

D'autre caractéristiques de l'invention seront précisées ci-après en regard des planches annexées parmi lesquelles :

  • - la figure 1 est une demi-vue en coupe longitudinale des premiers étages d'un compresseur basse pression de turboréacteur incorporant une grille d'entrée conforme à l'invention,
  • - la figure 2 est une vue en coupe d'un des bras de la grille d'entrée comportant un tube de passage d'huile,
  • - la figure 3 est une vue en coupe de la partie radialement externe du même bras, dont le volet aval a été retiré, selon AA de la figure 2.
  • - la figure 4 est une vue en coupe suivant F1 de la figure 2, du raccord entre le tube et le circuit d'huile de la turbomachine,
  • - la figure 5 est une vue en coupe suivant F2 de l'extrémité interne du tube, montée dans le collecteur d'huile de la virole interne,
  • - la figure 6 est une vue en coupe de la partie centrale du bras montrant un détail de la fixation antivibration du tube dans le bras,
  • - la figure 7 est une vue du même détail selon F3 de la figure 6,
  • - la figure 8 est une vue en coupe de ce même détail selon BB de la figure 6.
  • - les figures 9 à 12 montrent en quatre étapes le montage d'un tube d'huile dans un bras conforme à l'invention.
Other characteristics of the invention will be specified below with reference to the attached plates, among which:
  • FIG. 1 is a half-view in longitudinal section of the first stages of a low pressure turbojet compressor incorporating an inlet grid according to the invention,
  • FIG. 2 is a sectional view of one of the arms of the inlet grid comprising an oil passage tube,
  • FIG. 3 is a sectional view of the radially external part of the same arm, from which the downstream flap has been removed, according to AA in FIG. 2.
  • FIG. 4 is a sectional view along F1 of FIG. 2, of the connection between the tube and the oil circuit of the turbomachine,
  • FIG. 5 is a sectional view along F2 of the internal end of the tube, mounted in the oil collector of the internal ferrule,
  • FIG. 6 is a sectional view of the central part of the arm showing a detail of the anti-vibration attachment of the tube in the arm,
  • FIG. 7 is a view of the same detail along F3 of FIG. 6,
  • FIG. 8 is a sectional view of this same detail along BB of FIG. 6.
  • - Figures 9 to 12 show in four steps the mounting of an oil tube in an arm according to the invention.

En se référant à la figure 1, où a été représenté le compresseur basse pression d'une turbomachine de nouvelle génération, par exemple du type comprenant en aval deux turbines libres contrarotatives, on voit que la roue directrice d'entrée située en amont du premier étage 2 du rotor du compresseur basse pression est constituée de bras radiaux 1,1′ disposés entre la virole externe 3 de la veine 4 et la virole interne 5 solidaire du cône central amont 6 du moteur. Les bras 1,1′ ont un profil aérodynamique comportant un bord d'attaque, un intrados et un extrados et comprennent une partie aval orientable formée d'un volet 7 monté tournant sur un pivot externe 8 et un pivot interne 9 disposés à l'intérieur de paliers 10, les volets 7 de tous les bras radiaux étant commandés en rotation au moyen d'un anneau de commande 11 auquel ils sont reliés par des biellettes 12.Referring to FIG. 1, where the low pressure compressor of a new generation turbomachine has been shown, for example of the type comprising downstream two counter-rotating free turbines, it can be seen that the input guide wheel located upstream of the first stage 2 of the low pressure compressor rotor is made up of 1,1 ′ radial arms arranged between the outer ring 3 of the vein 4 and the internal ferrule 5 secured to the upstream central cone 6 of the engine. The arms 1,1 ′ have an aerodynamic profile comprising a leading edge, a lower surface and an upper surface and comprise an adjustable downstream part formed by a flap 7 mounted rotating on an external pivot 8 and an internal pivot 9 arranged at the inside of bearings 10, the flaps 7 of all the radial arms being controlled in rotation by means of a control ring 11 to which they are connected by connecting rods 12.

Si l'on se réfère maintenant aux figures 2 à 5, on voit tout d'abord sur la figure 5 qu'entre deux bras ou aubages ordinaires 1′ (qui ne comportent pas de tube de passage d'huile) est réalisé un bras ou aubage radial 1 incorporant un tube d'huile 13.If we now refer to Figures 2 to 5, we first see in Figure 5 that between two arms or ordinary blades 1 ′ (which do not have an oil passage tube) is formed an arm or radial blading 1 incorporating an oil tube 13.

Les aubages 1,1′ sont creux pour permettre une circulation d'air chaud, prélevé dans un collecteur d'air 14, destiné à empêcher le givrage du bord d'attaque de l'aubage et du cône central 6.The blades 1,1 ′ are hollow to allow a circulation of hot air, taken in an air collector 14, intended to prevent icing of the leading edge of the blade and of the central cone 6.

Les aubages 1,1′ont une partie amont, située entre le bord d'attaque 15 et une cloison aval 15a, qui forme également une enceinte 16 renforcée par une nervure 17 pour la circulation d'air chaud prélevé dans le collecteur 14. La partie du bras 1 située en aval de la cloison 15a forme une enceinte 21 ouverte sur toute sa longueur vers l'aval pour recevoir le tube 13 de passage d'huile.The blades 1,1 ′ have an upstream part, located between the leading edge 15 and a downstream partition 15a, which also forms an enclosure 16 reinforced by a rib 17 for the circulation of hot air taken from the manifold 14. The part of the arm 1 located downstream of the partition 15a forms an enclosure 21 open over its entire length downstream to receive the tube 13 for the passage of oil.

La figure 2 montre l'exemple d'un retour d'huile organisé selon l'invention.FIG. 2 shows the example of an oil return organized according to the invention.

La virole interne de la grille d'entrée comporte un collecteur d'huile 18 qui reçoit l'huile de récupération du palier P, ledit collecteur débouchant radialement au niveau d'un bras 1 possédant une tubulure d'huile 13, dans un logement cylindrique 19 recevant un embout d'extrémité 20 du tube 13 du bras.The internal ferrule of the inlet grille comprises an oil collector 18 which receives the recovery oil from the bearing P, said collector opening radially at the level of an arm 1 having an oil tube 13, in a cylindrical housing 19 receiving an end piece 20 of the tube 13 of the arm.

Sur son extrémité radialement externe, l'enceinte aval 21 du bras structural est solidaire du logement 22 du pivot externe du volet aval et ledit logement 22 comporte (voir figure 3) une découpe radiale 23 faisant communiquer l'alésage 22 recevant le pivot 8 et l'enceinte aval 21 du bras structurel pour permettre l'introduction par glissement de la tubulure 13 de passage d'huile dans l'enceinte aval du bras.On its radially external end, the downstream enclosure 21 of the structural arm is integral with the housing 22 of the external pivot of the downstream flap and said housing 22 comprises (see FIG. 3) a radial cutout 23 making the bore 22 receiving the pivot 8 communicate and the downstream enclosure 21 of the structural arm to allow the insertion by sliding of the tube 13 for the passage of oil into the downstream enclosure of the arm.

Le tube 13 comporte une partie centrale amincie de section oblongue, épousant intérieurement la forme en fuseau du bras structural qui la contient et coudée en trois endroits 24 afin de correspondre à la forme coudée de l'enceinte 21.The tube 13 has a thinned central part of oblong section, internally matching the spindle shape of the structural arm which contains it and bent in three places 24 so as to correspond to the bent shape of the enclosure 21.

A ces deux extrémités, la partie centrale amincie se raccorde à des embouts cylindriques 20 soudés qui comportent chacun un joint d'étanchéité 25.At these two ends, the thinned central part is connected to welded cylindrical end pieces 20 which each have a seal 25.

La virole externe 3 de la grille reçoit au droit de chaque tubulure de passage d'huile un raccord amovible 26 comportant un alésage venant se positionner sur l'embout 20 externe de la tubulure d'huile, ledit raccord étant vissé sur un bossage 27 de la virole externe et étant relié hydrauliquement à une pompe de récupération du circuit d'huile (non représenté) de la turbomachine.The external ferrule 3 of the grid receives, to the right of each oil passage pipe, a removable connection 26 comprising a bore coming to be positioned on the external nozzle 20 of the oil pipe, said connection being screwed onto a boss 27 of the outer shell and being hydraulically connected to a pump for recovering the oil circuit (not shown) of the turbomachine.

Pour en terminer avec la description structurelle de l'invention, il faut ajouter que le bras 1 comporte un soyage, ou rétreint, 28 (voir figures 6 à 8) environ à la moitié de sa longueur, destiné à recevoir un clip 29 en forme d'étrier en matière plastique qui se monte sur les flancs arrières du bras au niveau du rétreint et assure une double fonction de fixation du tube 13 dans son enceinte 21 et d'amortissement des vibrations dont les flancs du bras, en porte-à-faux, pourraient être l'objet.To finish with the structural description of the invention, it should be added that the arm 1 has a groove, or constricted, 28 (see FIGS. 6 to 8) about half of its length, intended to receive a shaped clip 29 of plastic stirrup which is mounted on the rear flanks of the arm at the level of the constriction and provides a double function of fixing the tube 13 in its enclosure 21 and of damping vibrations including sides of the arm, cantilevered, could be the object.

Si l'on se réfère maintenant aux figures 9 à 12, on verra comment le tube 13 est introduit dans l'enceinte 21.If we now refer to FIGS. 9 to 12, we will see how the tube 13 is introduced into the enclosure 21.

A la figure 9, le tube 13 est glissé dans l'alésage 22 du pivot du volet 7, puis (figures 10 et 11), il est poussé vers l'amont, parallèlement à lui-même, et l'extrémité 20 radialement externe du tube 13 est glissée vers son logement au travers de la lumière 21, tandis que la partie centrale du tube vient se loger dans le clip 29. Ensuite, le tube est poussé radialement vers l'intérieur jusqu'à ce que l'embout interne 20 soit en place dans son logement 19. On vient enfin positionner le raccord amovible 26 que l'on visse sur le bossage 27 de la virole externe 3.In FIG. 9, the tube 13 is slid into the bore 22 of the pivot of the flap 7, then (FIGS. 10 and 11), it is pushed upstream, parallel to itself, and the end 20 is radially external. of the tube 13 is slid towards its housing through the lumen 21, while the central part of the tube is received in the clip 29. Then, the tube is pushed radially inward until the internal end piece 20 is in place in its housing 19. Finally, the removable connector 26 is positioned, which is screwed onto the boss 27 of the outer shell 3.

Lorsque tous les tubes d'huile sont mis en place dans les bras 1, on peut alors mettre en place les volets 7 de façon connue.When all the oil tubes are in place in the arms 1, the flaps 7 can then be put in place in a known manner.

La structure de bras selon l'invention permet à la grille d'entrée d'avoir des bras extérieurement tous identiques, ce qui constitue un avantage notable pour la fabrication et la maintenance et assure en outre, la suppression des singularités aérodynamiques qui pouvaient exister dans le passé.The arm structure according to the invention allows the inlet grille to have externally identical arms, which constitutes a notable advantage for manufacturing and maintenance and also ensures the elimination of aerodynamic singularities which could exist in the past.

Claims (7)

1. Turbomachine d'aviation possédant une grille d'entrée formée de bras rayonnants (1,1′), support du carter d'entrée, disposés entre une virole interne (5) et une virole externe (3), certains d'entre eux (1) comportant une tubulure de passage d'huile, la grille comportant en outre des directrices d'entrée à calage variable, lesdits bras rayonnants étant en deux parties, une première partie amont structurale fixe et une seconde partie formant volet aval (7) à calage variable, articulée sur la partie structurale amont et constituant la directrice d'entrée, caractérisée en ce que tous les bras (1,1′) de la grille d'entrée sont de même section y compris ceux (1) comportant une tubulure (13) de passage d'huile et en ce que ceux des bras rayonnants (1) qui comportent une tubulure (13) de passage d'huile ont en section leur partie structurale divisée en trois enceintes séparées par deux cloisons radiales (15a, 17) les deux enceintes amont (16) étant parcourues par des débits d'air chaud et en ce que l'enceinte aval (21), ouverte sur toute sa longueur le long du bord de fuite est apte à recevoir la tubulure (13) de passage d'huile.1. Aviation turbomachine having an inlet grid formed by radiating arms (1.1 ′), support for the inlet casing, arranged between an internal ferrule (5) and an external ferrule (3), some of them them (1) comprising an oil passage manifold, the grid further comprising variable wedge entry guidelines, said radiating arms being in two parts, a first fixed structural upstream part and a second part forming a downstream flap (7 ) with variable setting, articulated on the upstream structural part and constituting the inlet director, characterized in that all the arms (1,1 ′) of the inlet grille are of the same section including those (1) comprising a oil passage pipe (13) and in that those of the radiating arms (1) which comprise an oil passage pipe (13) have in section their structural part divided into three enclosures separated by two radial partitions (15a, 17) the two upstream chambers (16) being traversed by hot air flow rates and e n that the downstream enclosure (21), open over its entire length along the trailing edge is capable of receiving the pipe (13) for passing the oil. 2. Turbomachine selon la revendication 1 caractérisée en ce que la virole interne (5) de la grille d'entrée comporte un collecteur d'huile (18) débouchant radialement au niveau de chaque bras (1) possédant une tubulure d'huile, dans un logement cylindrique (19) recevant un embout d'extrémité (20) de la tubulure (13) du bras.2. Turbomachine according to claim 1 characterized in that the internal ferrule (5) of the inlet grid comprises an oil collector (18) opening radially at each arm (1) having an oil tube, in a cylindrical housing (19) receiving an end piece (20) of the tube (13) of the arm. 3. Turbomachine selon l'une quelconque des revendications 1 ou 2 caractérisée en ce que la tubulure (13) comporte à chacune de ses extrémités un embout cylindrique (20) portant un joint d'étanchéité (25) et apte à coopérer respectivement avec le logement (19) de la virole interne et avec un raccord amovible (26) de la virole externe.3. Turbomachine according to any one of claims 1 or 2 characterized in that the tube (13) comprises at each of its ends a cylindrical end piece (20) carrying a seal (25) and able to cooperate respectively with the housing (19) of the internal ferrule and with a removable connection (26) of the outer shell. 4. Turbomachine selon la revendication 3, caractérisée en ce que la virole externe de la grille reçoit au droit de chaque tubulure de passage d'huile un raccord (26) comportant un alésage venant se positionner sur l'embout externe de la tubulure d'huile, ledit raccord étant vissé sur un bossage (27) de la virole externe (3) et étant relié hydrauliquement au circuit d'huile de la turbomachine.4. Turbomachine according to claim 3, characterized in that the external ferrule of the grid receives at the right of each oil passage pipe a fitting (26) comprising a bore coming to be positioned on the external end piece of the pipe. oil, said connector being screwed onto a boss (27) of the outer shell (3) and being hydraulically connected to the oil circuit of the turbomachine. 5. Turbomachine selon l'une quelconque des revendications 1 à 4 caractérisée en ce que l'extrémité radialement externe de l'enceinte aval (21) du bras structurel (1) est solidaire du logement (22) du pivot externe (8) du volet aval (7) et en ce que ledit logement (22) comporte une découpe radiale (23) faisant communiquer l'alésage (22) recevant le pivot et l'enceinte aval (21) du bras structurel pour permettre l'introduction par glissement de la tubulure de passage d'huile dans l'enceinte aval du bras.5. A turbomachine according to any one of claims 1 to 4 characterized in that the radially external end of the downstream enclosure (21) of the structural arm (1) is integral with the housing (22) of the external pivot (8) of the downstream flap (7) and in that said housing (22) comprises a radial cutout (23) communicating the bore (22) receiving the pivot and the downstream enclosure (21) of the structural arm to allow insertion by sliding of the oil passage pipe in the downstream enclosure of the arm. 6. Turbomachine selon l'une quelconque des revendications 3 à 5 caractérisée en ce que la tubulure de passage d'huile comporte, sur toute la longueur séparant ses deux embouts cylindriques d'extrémité (20), une section oblongue épousant intérieurement la forme en fuseau du bras structurel qui la contient.6. A turbomachine according to any one of claims 3 to 5 characterized in that the oil passage manifold comprises, over the entire length separating its two cylindrical end fittings (20), an oblong section internally matching the shape in spindle of the structural arm that contains it. 7. Turbomachine selon la revendication 6, caractérisée en ce que l'enceinte aval du bras comporte intérieurement un clip de fixation (29) antivibration coopérant avec un soyage (28) du bras (1) pour maintenir la tubulure (13) en position à l'intérieur de l'enceinte aval (21) du bras (1).7. A turbomachine according to claim 6, characterized in that the downstream enclosure of the arm internally comprises a anti-vibration fixing clip (29) cooperating with a groove (28) of the arm (1) to hold the tubing (13) in position inside the downstream enclosure (21) of the arm (1).
EP89401184A 1988-05-11 1989-04-26 Turbo machine having an entry stator grill with built-in oil passage tubes Expired - Lifetime EP0342087B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8806340 1988-05-11
FR8806340A FR2631386A1 (en) 1988-05-11 1988-05-11 TURBOMACHINE HAVING AN INPUT GRID INCORPORATING OIL PIPING TUBES

Publications (2)

Publication Number Publication Date
EP0342087A1 true EP0342087A1 (en) 1989-11-15
EP0342087B1 EP0342087B1 (en) 1991-09-04

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EP89401184A Expired - Lifetime EP0342087B1 (en) 1988-05-11 1989-04-26 Turbo machine having an entry stator grill with built-in oil passage tubes

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US (1) US4972671A (en)
EP (1) EP0342087B1 (en)
JP (1) JPH0211833A (en)
DE (1) DE68900238D1 (en)
FR (1) FR2631386A1 (en)

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* Cited by examiner, † Cited by third party
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Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5564903A (en) * 1993-11-23 1996-10-15 Alliedsignal Inc. In-line ram air turbine power system
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US5746574A (en) * 1997-05-27 1998-05-05 General Electric Company Low profile fluid joint
US6735954B2 (en) 2001-12-21 2004-05-18 Pratt & Whitney Canada Corp. Offset drive for gas turbine engine
US6619916B1 (en) * 2002-02-28 2003-09-16 General Electric Company Methods and apparatus for varying gas turbine engine inlet air flow
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EP1505263A1 (en) * 2003-08-08 2005-02-09 Siemens Aktiengesellschaft Guiding device in a diffuser flow passage of a turbomachine and method of operation
US7278516B2 (en) * 2004-03-09 2007-10-09 Honeywell International, Inc. Apparatus and method for bearing lubrication in turbine engines
FR2875855B1 (en) * 2004-09-27 2006-12-22 Snecma Moteurs Sa TURBOREACTOR WITH A MONOBLOC SERVITUDE CONNECTION ARM AND THE MONOBLOC SERVITUDE CONNECTION ARM
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US7594794B2 (en) * 2006-08-24 2009-09-29 United Technologies Corporation Leaned high pressure compressor inlet guide vane
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US8348600B2 (en) * 2008-05-27 2013-01-08 United Technologies Corporation Gas turbine engine having controllable inlet guide vanes
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US11555418B2 (en) 2019-06-12 2023-01-17 General Electric Company Oil supply system for a gas turbine engine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2919888A (en) * 1957-04-17 1960-01-05 United Aircraft Corp Turbine bearing support
US2930579A (en) * 1955-09-19 1960-03-29 Dominion Eng Works Ltd Turbine guide vane locking and vibration preventing arrangement
FR2219312A1 (en) * 1973-02-26 1974-09-20 Gen Electric
US4034558A (en) * 1975-10-14 1977-07-12 Westinghouse Canada Limited Cooling apparatus for split shaft gas turbine
US4076452A (en) * 1974-04-09 1978-02-28 Brown, Boveri-Sulzer Turbomaschinen Ag Gas turbine plant
US4183207A (en) * 1978-03-07 1980-01-15 Avco Corporation Oil-conducting strut for turbine engines
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
FR2599086A1 (en) * 1986-05-23 1987-11-27 Snecma Device for controlling the variable-pitch air inlet directing vanes of a jet engine

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2487842A (en) * 1948-03-09 1949-11-15 Westinghouse Electric Corp Aircraft power plant apparatus
GB702931A (en) * 1951-04-18 1954-01-27 Bristol Aeroplane Co Ltd Improvements in or relating to rotary machines comprising fluid compressing means
US3312448A (en) * 1965-03-01 1967-04-04 Gen Electric Seal arrangement for preventing leakage of lubricant in gas turbine engines

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2930579A (en) * 1955-09-19 1960-03-29 Dominion Eng Works Ltd Turbine guide vane locking and vibration preventing arrangement
US2919888A (en) * 1957-04-17 1960-01-05 United Aircraft Corp Turbine bearing support
FR2219312A1 (en) * 1973-02-26 1974-09-20 Gen Electric
US4076452A (en) * 1974-04-09 1978-02-28 Brown, Boveri-Sulzer Turbomaschinen Ag Gas turbine plant
US4034558A (en) * 1975-10-14 1977-07-12 Westinghouse Canada Limited Cooling apparatus for split shaft gas turbine
US4183207A (en) * 1978-03-07 1980-01-15 Avco Corporation Oil-conducting strut for turbine engines
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
FR2599086A1 (en) * 1986-05-23 1987-11-27 Snecma Device for controlling the variable-pitch air inlet directing vanes of a jet engine

Cited By (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
EP1149986A2 (en) * 2000-04-29 2001-10-31 General Electric Company Turbine frame assembly
EP1149986A3 (en) * 2000-04-29 2003-11-19 General Electric Company Turbine frame assembly
FR3051854A1 (en) * 2016-05-30 2017-12-01 Snecma TURBOMACHINE EXHAUST CASE
US11136894B2 (en) 2017-03-23 2021-10-05 Safran Aircraft Engines Central support for auxiliary tubes with elastic return
WO2018172715A1 (en) * 2017-03-23 2018-09-27 Safran Aircraft Engines Central support for auxiliary tubes with elastic return
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CN110546350B (en) * 2017-03-23 2022-06-17 赛峰飞机发动机公司 Center support with elastic return for an auxiliary conduit
FR3083260A1 (en) * 2018-06-28 2020-01-03 Safran Aircraft Engines MODULE OF A DOUBLE FLOW AIRCRAFT ENGINE WITH AN ARM INCORPORATING A STATOR VANE
US11319899B2 (en) 2018-06-28 2022-05-03 Safran Aircraft Engines Module of an aircraft bypass engine of which one arm integrates a stator blade
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US11156129B2 (en) 2019-02-25 2021-10-26 Safran Aircraft Engines Turbine engine casing
EP3705686A1 (en) 2019-02-25 2020-09-09 Safran Aircraft Engines Turbine engine housing
CN111608750A (en) * 2019-02-25 2020-09-01 赛峰航空器发动机 Turbine engine casing
CN111608750B (en) * 2019-02-25 2024-04-19 赛峰航空器发动机 Turbine engine housing
EP3967855A1 (en) * 2020-09-11 2022-03-16 Pratt & Whitney Canada Corp. Boss for gas turbine engine
US11384659B2 (en) 2020-09-11 2022-07-12 Pratt & Whitney Canada Corp. Boss for gas turbine engine

Also Published As

Publication number Publication date
US4972671A (en) 1990-11-27
JPH0211833A (en) 1990-01-16
FR2631386A1 (en) 1989-11-17
JPH0587650B2 (en) 1993-12-17
DE68900238D1 (en) 1991-10-10
EP0342087B1 (en) 1991-09-04

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