EP0342087B1 - 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
EP0342087B1
EP0342087B1 EP89401184A EP89401184A EP0342087B1 EP 0342087 B1 EP0342087 B1 EP 0342087B1 EP 89401184 A EP89401184 A EP 89401184A EP 89401184 A EP89401184 A EP 89401184A EP 0342087 B1 EP0342087 B1 EP 0342087B1
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EP
European Patent Office
Prior art keywords
oil
pipe
strut
turboshaft engine
accordance
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.)
Expired - Lifetime
Application number
EP89401184A
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German (de)
French (fr)
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EP0342087A1 (en
Inventor
Jean-Claude Asselin
Pierre Antoine Glowacki
Daniel Jean-Marie Martin
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Safran Aircraft Engines SAS
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Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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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. to the point where it is impossible to accommodate the oil circuit pipes 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, a 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 passing 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 plastic stirrup which mounts 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 grid 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 Details And Ventilation Of Internal Combustion Engines (AREA)
  • Lubrication Of Internal Combustion Engines (AREA)

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 8,5 mm 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. to the point where it is impossible to accommodate the oil circuit pipes 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-2526485 en est un exemple. FR-A-2599086 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. US3844110 (ou son correspondant français FR-A-2219312) 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-2526485 is an example. FR-A-2599086 shows another example in which oil tubes are inserted in the upstream part of the arms whose structure is conventional and has a closed aerodynamic profile delimiting a single internal cavity. US3844110 (or its French correspondent FR-A-2219312) 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, a 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 passing 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 plastic stirrup which mounts 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 grid 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. Aircraft turboshaft engine having an intake grille composed of radiating struts (1, 1′), supporting the intake cowling, arranged between an inner shell (5) and an outer shell (3), certain of which (1) comprising a pipe for the conveyance of oil, the grille comprising in addition intake guide vanes of variable pitch, the said radiating struts being in two parts, a first fixed structural upstream part and a second part forming a downstream vane (7) of variable pitch, hinged on the upstream structural part and constituting the intake guide vane, characterised in that all the struts (1, 1′) of the intake grille have the same cross section including those (1) incorporating a pipe (13) for the conveyance of oil and in that the radiating struts (1) which comprise a pipe (13) for the conveyance of oil have their structural part divided, in cross section, into three compartments separated by two radial walls (15a, 17) the two upstream compartments (16) being traversed by flows of hot air and in that the downstream compartment (21), open along all the length of its trailing edge is able to receive the pipe (13) for the conveyance of oil.
2. Turboshaft engine in accordance with Claim 1 characterised in that the inner shell (5) of the intake grille comprises an oil collection manifold (18) opening radially, at the point of each strut (1) equipped with an oil pipe, into a cylindrical housing (19) receiving an end (20) of the pipe (13) of the strut.
3. Turboshaft engine in accordance with either of Claims 1 or 2 characterised in that the pipe (13) has at each of its extremities a cylindrical end (20) with a seal (25) and able to work in conjunction respectively with the housing (19) of the inner shell and with a fixed connector (26) on the outer shell.
4. Turboshaft engine in accordance with Claim 3 characterised in that the outer shell of the grille, at the point of each oil-conveying pipe, receives a connector (26) comprising a bore which fits over the end of the oil pipe, the said connector being screwed to a boss (27) on the outer shell (3) and being connected hydraulically to the oil circuit of the turboshaft engine.
5. Turboshaft engine in accordance with any of Claims 1 to 4 characterised in that the radially outer end of the downstream compartment (21) of the structural strut (1) is fixed to the housing (22) of the outer pivot (8) of the downstream vane (7) and in that the said housing (22) comprises a radial cut-out (23) causing the bore (22) receiving the pivot to be in communication with the downstream compartment (21) of the structural strut so as to allow the insertion of the oil-conveying pipe by a sliding motion into the downstream compartment of the strut.
6. Turboshaft engine in accordance with any of Claims 3 to 5 characterised in that the oil-conveying pipe comprises, along all its length between the two cylindrical ends (20), an oblong section assuming the inner spindle-shaped profile of the inside of the structural strut which contains it.
7. Turboshaft engine in accordance with Claim 6 characterised in that the downstream compartment of the strut comprises in the inside an anti-vibration fixing clip (29) working in conjunction with a swaged section (28) of the strut (1) to hold the pipe (13) in position within the downstream compartment (21) of the strut (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
FR8806340A FR2631386A1 (en) 1988-05-11 1988-05-11 TURBOMACHINE HAVING AN INPUT GRID INCORPORATING OIL PIPING TUBES
FR8806340 1988-05-11

Publications (2)

Publication Number Publication Date
EP0342087A1 EP0342087A1 (en) 1989-11-15
EP0342087B1 true 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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EP (1) EP0342087B1 (en)
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JPH0211833A (en) 1990-01-16
JPH0587650B2 (en) 1993-12-17
DE68900238D1 (en) 1991-10-10
FR2631386A1 (en) 1989-11-17
EP0342087A1 (en) 1989-11-15
US4972671A (en) 1990-11-27

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