WO2017212196A1 - Tubular rotor element for a turbomachine, having a star-shaped cross-section - Google Patents

Tubular rotor element for a turbomachine, having a star-shaped cross-section Download PDF

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Publication number
WO2017212196A1
WO2017212196A1 PCT/FR2017/051476 FR2017051476W WO2017212196A1 WO 2017212196 A1 WO2017212196 A1 WO 2017212196A1 FR 2017051476 W FR2017051476 W FR 2017051476W WO 2017212196 A1 WO2017212196 A1 WO 2017212196A1
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WO
WIPO (PCT)
Prior art keywords
wall
oil
tubular
section
shaft
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PCT/FR2017/051476
Other languages
French (fr)
Inventor
Benjamin LEMENAND
Serge René Morreale
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Safran Aircraft Engines
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Application filed by Safran Aircraft Engines filed Critical Safran Aircraft Engines
Publication of WO2017212196A1 publication Critical patent/WO2017212196A1/en

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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
    • F01D25/18—Lubricating arrangements

Definitions

  • the invention relates to the lubrication of the turbomachine bearings, and in particular the multi-shaft gas turbine shaft bearings that are supplied with oil by oil passage holes.
  • the invention relates more particularly to a tubular rotor element for a turbomachine having first through-holes for passing oil, and to a turbomachine comprising such a tubular element.
  • a dual-body gas turbine engine comprises a first rotary assembly, said low-pressure body, LP, formed of a shaft connecting a BP compressor upstream, and a LP turbine downstream.
  • the upstream and downstream are defined with respect to the direction of flow of air in the turbomachine.
  • Each of the compressor and turbine elements may be composed of one or a plurality of stages.
  • the two elements are spaced axially from each other and provide a location for a second rotary assembly, said high-pressure body, HP, formed of an HP compressor, disposed downstream of the compressor BP, and a turbine HP, arranged upstream of the LP turbine.
  • the HP compressor and the HP turbine are mechanically connected to each other by an HP high-pressure shaft, which surrounds the BP low-pressure shaft.
  • a combustion chamber of the engine fixed relative to the two bodies HP and BP, and generally annular, is housed circumferentially around the high-pressure shaft upstream of the HP turbine.
  • the combustion chamber receives the compressed air successively by the stages of the compressors BP and HP, and delivers high-energy combustion gases to the stages of the HP and LP turbines successively.
  • the engine may also include, upstream of BP and HP compressors, a blower rotor which is driven by the BP body shaft, for example via a gearbox, or counter-rotating propellers coupled to the BP body shaft via a epicyclic train.
  • Such an engine comprises structural housing elements supporting in particular the rotary assemblies by bearings.
  • a housing element said intermediate housing defines an upstream enclosure which comprises a hub supporting the LP shaft via an upstream LP bearing.
  • a casing element said exhaust casing, defines a downstream oil enclosure which also comprises a hub supporting the LP shaft via a downstream LP bearing.
  • the HP body is in particular supported by the LP shaft by means of an inter-shaft bearing, for which it is necessary to provide lubrication.
  • Such an inter-shaft bearing must be lubricated with oil from the downstream enclosure.
  • an oil path is provided between the downstream enclosure and this bearing.
  • This oil path must for example cross, successively and radially from the inside to the outside, the LP shaft, a first wall of a member secured to the LP shaft, or BP sleeve which seals with an HP trunnion carried by the downstream end of the HP shaft via a seal, and said trunnion.
  • the inter-shaft bearing is carried externally by this journal and it is interposed between the journal and a second wall of the member integral with the LP shaft, this second wall being secured to the LP shaft and the BP sleeve downstream of the downstream end of the HP trunnion.
  • the oil is centrifuged by the rotation of the BP shaft along this oil path.
  • the oil path generally comprises an oil supply rod which is housed inside the LP shaft, radial orifices arranged substantially axially facing each other, which respectively pass through the LP shaft, the sleeve BP, the HP trunnion and cavities, arranged between these orifices and between these various elements, which are traversed by the oil.
  • cavities are arranged between the supply rod and the LP shaft, between the LP shaft and the LP sleeve, and between the LP sleeve and the HP pin.
  • a problem arises particularly with regard to the cavity which is arranged between the LP sleeve and the HP spigot. Indeed, this cavity is subjected to a flow of air under pressure moving substantially longitudinally between the sleeve and the journal, which comes from the dynamic seal which is interposed between the sleeve and the trunnion.
  • Such a seal is in particular a labyrinth seal which is capable of allowing the passage of a flow of air under pressure.
  • the sheath is rotatably connected to the low-pressure shaft and the journal is integral in rotation with the high-pressure shaft.
  • the sheath and the trunnion rotate in the same direction or in opposite directions to one another, at different speeds, so that the oil flow does not benefit from an optimal centrifugation effect.
  • the crossing zone of the oil flow and the air flow is therefore a critical zone, because the pressurized air flow tends to drive the oil away from the pin holes. This phenomenon is even more critical when the sheath and the trunnion are counter-rotating, because in this case the oil passes through a point zero radial velocity.
  • the invention therefore aims to limit the previously mentioned effect by providing a tubular sheath which is configured to promote the passage of the air flow between the through holes of said sheath, so that said air flow does not deviate or little the oil flow, an oil chamber comprising such a sleeve and a turbomachine comprising such an oil chamber.
  • a sleeve is necessarily tubular and can not have a shoulder wall having a large footprint in which there would be separate passages for oil and air.
  • Such a design which relates to journals extending in a plane transverse to the axis of the turbomachine and having separate oil and air passages, has already been proposed in documents FR-2878287 and FR- 2992680, but is not transferable to a sheath.
  • the invention proposes a tubular rotor element for a turbomachine, comprising a first section of longitudinal axis comprising an annular row of first radial through-holes of oil passage configured to facilitate the passage of a flow of oil. air between said orifices.
  • the invention does not intend to be limited to a sleeve secured to a low-pressure shaft and to its interaction with a high-pressure journal in the context of an oil chamber of a turbomachine, but is applicable to any tubular rotor element intended to allow the routing of a radial oil flow in an environment traversed by a flow of air.
  • the invention also proposes a turbomachine comprising such a tubular element.
  • a tubular rotor element for a turbomachine comprising a first section of longitudinal axis A comprising first sealing means and a second section of adjacent longitudinal axis A comprising an annular row of first orifices.
  • radial oil passing through characterized in that said second section has in cross section an alternation of first angular sectors of oil passage, comprising the first through radial orifices, which have a first diametral space D1 around said longitudinal axis, and second angular air guide sectors which have a second diametral bulk D2 about said longitudinal axis, said first and second diametral bulk D1 and D2 being different.
  • the first diameter space D1 is greater than the second diameter space D2,
  • the second section has a cross section of substantially corrugated or star shape
  • the second section comprises a wall of substantially constant thickness.
  • the invention also relates to an annular turbomachine oil enclosure, defined by:
  • first tubular member comprising first and second coaxial tubular walls connected to one another by at least one transverse wall
  • the first wall comprises at least one tubular element of the type previously described, said element being housed in a bore of the third wall of the second member, said bore comprising a first section comprising second means of sealing substantially extending around said first sealing means of the tubular element and a second section comprising an annular row of second radial oil passage orifices situated substantially in line with said first radial orifices passing through the tubular element.
  • said element and the third wall of the second member define between them a longitudinal cavity into which the first and second orifices open, said cavity being traversed by a flow of air coming from the first and second sealing means configured as sealing means; of labyrinth type and traversed by the flow of oil circulating between the first and second orifices,
  • the first wall of the first member is mounted on an inner shaft and is integral in rotation with said shaft, said element of the first wall and said shaft defining between them a longitudinal cavity into which the first orifices open and an annular row of third radial orifices; oil passagethroughs formed in said shaft,
  • the invention also relates to a turbomachine comprising an oil chamber of the type previously described, characterized in that the first wall is a sleeve of a low-pressure body of the turbomachine, in that the inner shaft is an inner shaft low-pressure of the turbomachine, in that the second wall is fixed to said first wall and to said inner shaft, and in that the second member is a journal of a high-pressure outer shaft of the turbomachine.
  • FIG. 1 is a half-view in axial section of a turbomachine
  • FIG. 2 is a detail view in axial section of an oil chamber according to a prior art formed in a downstream portion of the turbomachine of Figure 1, in the vicinity of its inter-shaft bearing;
  • Figure 3 is a detail view of Figure 2;
  • FIG. 4 is a cross-sectional view of a tubular element according to a prior art
  • FIG. 5 is a cross-sectional view of a tubular element according to the invention.
  • FIGS. 6A and 6B are detailed views in axial section of downstream parts of an oil enclosure according to the invention formed in a downstream part of a turbomachine, in the vicinity of its inter-shaft bearing, in two positions. angles of the angular element.
  • FIG. 1 shows diagrammatically and by way of example a turbomachine 10 of double-body and double-flow type.
  • a turbomachine here a turbojet engine 10
  • Such a turbomachine comprises, in known manner, a fan 12, a low-pressure compressor 14, a high-pressure compressor 1 6, a combustion chamber 18, a high-pressure turbine 20, a low-pressure turbine 22, and an exhaust nozzle 24.
  • the rotor of the HP high-pressure compressor 1 6 and the rotor of the high-pressure turbine 20 are connected by an HP high-pressure shaft 26 and form with it a high-pressure body.
  • the rotor of the LP low pressure compressor 14 and the rotor of the LP low pressure turbine 22 are connected by a LP low pressure shaft 28 and form with it a low-pressure body.
  • Each compressor 14, 1 6 or turbine 20, 22 may consist of several stages of compressor or turbine in series.
  • the HP shaft 26 and the LP shaft 28 extend along an axis A which is the global axis of the turbojet engine 10. In the remainder of the description, the notions of longitudinal or radial are relative to this axis A.
  • Each of the Low-pressure BP 28 and high-pressure HP 26 trees are rotatably mounted in a housing 30 of the turbojet engine, the LP shaft 28 being coaxial and mounted internally to the HP shaft 26.
  • the high-pressure and low-pressure bodies are traversed by a primary air flow P and the fan 12 produces a secondary air flow S which circulates in the turbojet engine 10, between the casing 30 and an outer casing 32 of the turbojet engine.
  • the gases from the primary flow P are mixed with the secondary flow S to produce a propulsive force, the secondary flow S providing the majority of the thrust.
  • the turbojet engine 10 has, substantially at the upstream end of the high-pressure body, a so-called "upstream” chamber 34 containing gears bearings and, substantially at the downstream end of the high-pressure body, a so-called “downstream” chamber 36 containing bearing members, including bearings.
  • the BP 28 and HP 26 trees are mounted rotating relative to each other via an inter-shaft bearing 52.
  • FIGS. 2 and 3 show such an inter-shaft bearing 52 within of the downstream chamber 36 of the turbomachine.
  • the downstream chamber 36 of the turbomachine comprises an annular oil enclosure 38.
  • this oil enclosure 38 is delimited, first, by a first tubular member 37 having a first tubular wall 39 and a second coaxial tubular wall 54.
  • the first and second coaxial tubular walls 39, 54 are connected to one another by at least one transverse wall 63.
  • the oil enclosure 38 is delimited, secondly, by a second tubular member 40 of axis A, which is received at least partly in the first member 37 and which comprises a third tubular wall 41 which receives internally at least in part said first tubular wall 39 of the first annular member 37.
  • sealing means 48, 49 are interposed between the first and third tubular walls 39, 54.
  • the oil enclosure 38 is delimited, thirdly, by a sealing element 51, for example a labyrinth seal 51 which is interposed between the third wall 41 of the second tubular member 40 and a third coaxial wall 55 of the first member 37.
  • the sealing member 51 thus substantially closes the oil chamber 38.
  • a bearing 52 is housed in the oil enclosure 38 and is more particularly interposed between the third wall 41 of the second tubular member 40 and the second wall 54 of the first member 37.
  • the first wall 39 is a sleeve of a low-pressure body LP and it receives a downstream end of the LP low pressure shaft 28 of the turbomachine 10, which it is fixed.
  • the second wall 54 is fixed to said first wall and to said inner shaft 28.
  • the second member 40 with axis A and coaxial with the BP shaft 28, consists of an HP high-pressure journal which forms a terminal downstream end of the HP shaft 26.
  • the third tubular wall 41 of this second member 40 receives in a bore 44 the tubular element 42 of the first wall 39.
  • the tubular element 42 comprises a first section 46 of longitudinal axis A comprising first sealing means 48, which are surrounded by second sealing means 49 carried by a first section 43 of the bore 44.
  • the second sealing means 49 of the first section 43 of the second member 40 are preferably made of an abradable material cooperating with wipers forming the first sealing means 48.
  • the wipers form with the abradable material a labyrinth seal.
  • a pressurized air flow F represented by arrows in FIGS. 2 and 3 is able to pass through the labyrinth seal and a longitudinal cavity 50 defined between the element 42 and the third wall 41 of the second member 40 .
  • the second member 40 externally carries the bearing 52, interposed between the third wall 41 and the second wall 54 of the first member 37, to allow the rotational guidance of the HP shaft 26 relative to the BP shaft 28.
  • the second wall 54 and the first wall 39 are separate parts, joined together by a bolted connection. More particularly, the tubular element 42 or sheath is bonded to both the shaft BP 28 and the tubular part 54 by means of a bolted connection 56, a screw 58 passes through a shoulder 60 of the BP shaft 28, a shoulder 62 of the second wall 54, and a shoulder 64 of the element tubular 42.
  • the inter-shaft bearing 52 must be lubricated with oil coming from the downstream enclosure 36.
  • an oil path H represented by arrows, is provided between the downstream enclosure 36 and this Bearing 52.
  • the path of the oil H must for example cross, successively and radially from the inside to the outside, the LP shaft 28, the tubular element 42 or sleeve BP, and the third wall 41 of the second member 40 or HP journal, which carries the bearing 52.
  • the oil path H generally comprises an oil supply rod 66 which is housed inside the LP shaft 28, radial orifices 68, 70, 72, 74 arranged in the form of annular rows and arranged substantially axially to the right of each other, which respectively pass through the rod 66, the LP shaft 28, the tubular element 42 or sleeve BP, and a second section 45 of the third wall 41 of the second member 40 or LP trunnion.
  • the radial orifices 72, 74 and 70 will respectively be designated first radial orifices 72, second radial orifices 74, and third radial orifices 70.
  • the oil path passes through cavities 50, 76, 78.
  • a cavity 76 is arranged between the supply rod 66 and the LP shaft 28
  • a cavity 78 is arranged between the LP shaft 28 and the tubular element 42 or sleeve BP
  • the cavity 50 is arranged between the tubular element 42 and the third wall 41 of the second member 40 or HP trunnion.
  • the first through orifices 72 and the third through orifices 70 thus open into the cavity 78, while the first orifices through-holes 72 and the second through-holes 74 open into the cavity 50.
  • the air flow F is therefore likely to interfere with the flow of oil H and to deflect it, which can lead to poor lubrication of the bearing or bearing 52.
  • the oil passing through the cavity 50 passes through a point of zero velocity, and is therefore able to be more easily deflected.
  • the crossing zone of the oil flow H and the air flow F in the cavity 50 is in any case a critical zone, the element 42 and the third wall 41 are co-rotating or counter-rotating.
  • the invention proposes a tubular element 42 which is configured to promote the passage of air flow between its through holes 72, so that said air flow F bathing said element 42 does not deviate
  • the invention also proposes an oil cavity 38 comprising such an element 42, and a turbomachine 10 comprising such an oil cavity 38.
  • the tubular element 42 comprises the first section 46. longitudinal axis A comprising the first sealing means 48, and a second section 80 of adjacent longitudinal axis A which comprises the annular row of the first radial orifices 72 passing through oil.
  • the second section 80 of the element 42 has a constant diameter D, so that the clearance J corresponding to the cavity 50, between the second section 80 and the second member 40, is identical along the entire periphery of said second section 80.
  • the second section 80 has in cross-section an alternation of first angular sectors 82 of oil passage, comprising the first radial orifices passing through. 72, which have a first diametral space D1 around the longitudinal axis A, and second angular sectors 84 of air guide which have a second diameter space D2 around said longitudinal axis A.
  • the first diameter space D1 is configured so that the first radial through-holes 72 are as close as the bore 44 of the third wall 41 of the HP trunnion 40, and the second diametrical space D2 is configured so that, in the second angular sectors 84, the wall of the second segment 80 is further away from the bore 44 of the third wall 41 of the HP 40 trunnion.
  • the first diametral space D1 is greater than second diameter space D2. It will be understood that an opposite configuration would be expected in the case of a tubular element 42 surrounding on the contrary a coaxial member 40 that must supply oil, for example a coaxial tube for supplying oil.
  • the second section 80 would have in cross section an alternation of first angular sectors of oil passage, comprising the first radial orifices through which would have a first reduced diametral space around the longitudinal axis A, less than that of second angular sectors of air guide which in turn have a second diameter space around said longitudinal axis A.
  • the second section 80 would thus have a lobed shape.
  • each angular sector 82 which comprises the first orifices 72, forms with the third wall 41 of the second member 40 a clearance J1 which is smaller than a clearance J2 formed between the adjacent angular sector 84 and the same third wall 41.
  • This upper clearance J2 is thus able to allow the angular sector 84 to form a preferred passage of high passage section for the flow of pressurized air F, which therefore passes in each angular sector 84 between two angular sectors 82, rather than above the first orifices 72.
  • This configuration thus makes it possible to largely avoid the deflection of the flow of oil H by the flow of air F.
  • the flow of oil H can pass virtually without being deviated from the first radial orifices 72 passing through the tubular element 42 to the annular row of second radial oil passage orifices 74 formed in the second section 45 of the third wall 41.
  • the clearance J1 can correspond to approximately 3% of the diameter of the second member 40 or trunnion, while the clearance J2 can correspond to approximately 8% of the diameter of the member 40. or trunnion.
  • the second section 80 has a substantially corrugated cross section or star.
  • This section can be obtained by any known method of the state of the art for carrying out this section.
  • the tubular element 42 may thus be the result of molding and machining operations. It can also be realized in the form of an assembly of axial sections obtained by different techniques. One could thus consider making the second section 82 in the form of a profile obtained by passing through a die.
  • the wall 85 is continuous, that is to say there is no discontinuity of this wall between a first sector 82 and a second sector 84 adjacent.
  • the corrugated or star-shaped section of the second section thus has arms 88 which delimit the first angular sectors 82 of oil passage and whose connecting walls 90, arranged between two consecutive arms 88 constitute the second angular sectors 84 of air guidance.
  • FIGS. 6A and 6B which represent the arrangement of an element 42 according to the invention in the downstream enclosure 36 of a turbomachine according to two angular positions of the element 42
  • the second section 80 preferably extends axially on the LP shaft 28 from the first orifices 72 to at least a portion 92 of the LP shaft 28 which is arranged outside the member 40. to ensure the passage of air along the angular sectors 84 to a portion of the BP shaft 28 where they open freely, and thus avoid any restriction of the air flow.
  • the axes of the first orifices 72 of the tubular element of the second orifices 74 are preferably close, in order to limit the dispersions of the oil flow H.
  • the axes of the first orifices 72 of the element 42 and second orifices 74 of the member 40 intersect substantially in the cavity 50, without this configuration being limiting of the invention.
  • the invention has been described in relation to an oil chamber 38 receiving an inter-shaft bearing 52 arranged between a BP 28 and HP 26 shaft and delimiting between these trees a cavity 50. It will be understood that the invention can also be to apply to a cavity arranged between a shaft and a fixed casing without changing the nature of the invention.
  • the invention therefore applies to any rotatable tubular element mounted in an organ that it must feed through a series of through holes arranged one to the right of the others.

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Abstract

The invention relates to a tubular rotor element (42) for a turbomachine, comprising a first portion that has a longitudinal axis (A) and includes first sealing means, and an adjacent second portion (80) that has a longitudinal axis (A) and includes an annular row of first oil-penetrated radial through-holes (72), characterized in that in a cross-sectional view, the second portion (80) has an alternating succession of first, oil-penetrated angular sectors (82) comprising the first radial through-holes (72) having a first outer diameter D1 about the longitudinal axis (A), and second, air-conducting angular sectors (84) having a second outer diameter D2 about the longitudinal axis (A), the two outer diameters D1 and D2 being different. The invention also relates to a turbomachine comprising a tubular element (42) of said type.

Description

Elément tubulaire de rotor à section étoilée pour une turbomachine  Tubular rotor element with a star section for a turbomachine
L'invention se rapporte à la lubrification des paliers de turbomachine, et en particulier des paliers inter-arbres de turbine à gaz multicorps alimentés en huile par des orifices de passage d'huile. The invention relates to the lubrication of the turbomachine bearings, and in particular the multi-shaft gas turbine shaft bearings that are supplied with oil by oil passage holes.
L'invention se rapporte plus particulièrement à un élément tubulaire de rotor pour une turbomachine comportant des premiers orifices traversants de passage d'huile, et à une turbomachine comportant un tel élément tubulaire.  The invention relates more particularly to a tubular rotor element for a turbomachine having first through-holes for passing oil, and to a turbomachine comprising such a tubular element.
ETAT DE LA TECHNIQUE ANTERIEURE STATE OF THE PRIOR ART
Un moteur à turbine à gaz à double corps comprend un premier ensemble rotatif, dit corps basse-pression, BP, formé d'un arbre reliant un compresseur BP à l'amont, et une turbine BP à l'aval. Dans la suite de la présente description, l'amont et l'aval sont définis par rapport à la direction d'écoulement de l'air dans la turbomachine. A dual-body gas turbine engine comprises a first rotary assembly, said low-pressure body, LP, formed of a shaft connecting a BP compressor upstream, and a LP turbine downstream. In the following description, the upstream and downstream are defined with respect to the direction of flow of air in the turbomachine.
Chacun des éléments de compresseur et de turbine peut être composé d'un ou d'une pluralité d'étages. Les deux éléments sont espacés axialement l'un de l'autre et ménagent un emplacement pour un second ensemble rotatif, dit corps haute-pression, HP, formé d'un compresseur HP, disposé en aval du compresseur BP, et d'une turbine HP, disposée en amont de la turbine BP. Le compresseur HP et la turbine HP sont reliés mécaniquement l'un à l'autre par un arbre haute-pression HP, qui entoure l'arbre basse-pression BP. Une chambre de combustion du moteur, fixe par rapport aux deux corps HP et BP, et généralement annulaire, est logée circonférentiellement autour de l'arbre haute-pression en amont de la turbine HP. La chambre de combustion reçoit l'air comprimé successivement par les étages des compresseurs BP et HP, et délivre des gaz de combustion à haute énergie aux étages des turbines HP et BP successivement. Le moteur peut également comprendre, en amont des compresseurs BP et HP, un rotor de soufflante qui est entraîné par l'arbre du corps BP, par exemple par l'intermédiaire d'un réducteur, ou des hélices contrarotatives accouplées à l'arbre du corps BP par l'intermédiaire d'un train épicycloïdal. Each of the compressor and turbine elements may be composed of one or a plurality of stages. The two elements are spaced axially from each other and provide a location for a second rotary assembly, said high-pressure body, HP, formed of an HP compressor, disposed downstream of the compressor BP, and a turbine HP, arranged upstream of the LP turbine. The HP compressor and the HP turbine are mechanically connected to each other by an HP high-pressure shaft, which surrounds the BP low-pressure shaft. A combustion chamber of the engine, fixed relative to the two bodies HP and BP, and generally annular, is housed circumferentially around the high-pressure shaft upstream of the HP turbine. The combustion chamber receives the compressed air successively by the stages of the compressors BP and HP, and delivers high-energy combustion gases to the stages of the HP and LP turbines successively. The engine may also include, upstream of BP and HP compressors, a blower rotor which is driven by the BP body shaft, for example via a gearbox, or counter-rotating propellers coupled to the BP body shaft via a epicyclic train.
Un tel moteur comporte des éléments de carter structuraux supportant notamment les ensembles rotatifs par des paliers. A l'amont, un élément de carter, dit carter intermédiaire, délimite une enceinte amont qui comprend un moyeu supportant l'arbre BP par l'intermédiaire d'un palier BP amont. A l'aval, un élément de carter, dit carter d'échappement, délimite une enceinte d'huile aval qui comprend également un moyeu supportant l'arbre BP par l'intermédiaire d'un palier BP aval. A l'aval, le corps HP est notamment supporté par l'arbre BP au moyen d'un palier inter-arbres, pour lequel il est nécessaire d'assurer une lubrification.  Such an engine comprises structural housing elements supporting in particular the rotary assemblies by bearings. Upstream, a housing element, said intermediate housing defines an upstream enclosure which comprises a hub supporting the LP shaft via an upstream LP bearing. Downstream, a casing element, said exhaust casing, defines a downstream oil enclosure which also comprises a hub supporting the LP shaft via a downstream LP bearing. Downstream, the HP body is in particular supported by the LP shaft by means of an inter-shaft bearing, for which it is necessary to provide lubrication.
Un tel palier inter-arbres doit être lubrifié à l'aide de l'huile provenant de l'enceinte aval. A cet effet, un chemin d'huile est ménagé entre l'enceinte aval et ce palier. Ce chemin d'huile doit par exemple traverser, successivement et radialement de l'intérieur vers l'extérieur, l'arbre BP, une première paroi d'un organe solidaire de l'arbre BP, ou fourreau BP qui assure l'étanchéité avec un tourillon HP porté par l'extrémité aval de l'arbre HP par l'intermédiaire d'un joint d'étanchéité, et ledit tourillon. Le palier inter-arbres est porté extérieurement par ce tourillon et il est interposé entre le tourillon et une deuxième paroi de l'organe solidaire de l'arbre BP, cette deuxième paroi étant solidarisée à l'arbre BP et au fourreau BP en aval de l'extrémité aval du tourillon HP. L'huile est centrifugée par la rotation de l'arbre BP le long de ce chemin d'huile.  Such an inter-shaft bearing must be lubricated with oil from the downstream enclosure. For this purpose, an oil path is provided between the downstream enclosure and this bearing. This oil path must for example cross, successively and radially from the inside to the outside, the LP shaft, a first wall of a member secured to the LP shaft, or BP sleeve which seals with an HP trunnion carried by the downstream end of the HP shaft via a seal, and said trunnion. The inter-shaft bearing is carried externally by this journal and it is interposed between the journal and a second wall of the member integral with the LP shaft, this second wall being secured to the LP shaft and the BP sleeve downstream of the downstream end of the HP trunnion. The oil is centrifuged by the rotation of the BP shaft along this oil path.
Le chemin d'huile comporte généralement une canne d'alimentation en huile qui est logée à l'intérieur de l'arbre BP, des orifices radiaux agencés sensiblement axialement en regard les uns des autres, qui traversent respectivement l'arbre BP, le fourreau BP, le tourillon HP et des cavités, agencées entre ces orifices et entre ces différents éléments, qui sont traversées par l'huile. En particulier, des cavités sont agencées entre la canne d'alimentation et l'arbre BP, entre l'arbre BP et le fourreau BP, et entre le fourreau BP et le tourillon HP. Un problème se pose particulièrement en ce qui concerne la cavité qui est agencée entre le fourreau BP et le tourillon HP. En effet, cette cavité est soumise à un flux d'air sous pression se déplaçant sensiblement longitudinalement entre le fourreau et le tourillon, qui provient du joint d'étanchéité dynamique qui est interposé entre le fourreau et le tourillon. The oil path generally comprises an oil supply rod which is housed inside the LP shaft, radial orifices arranged substantially axially facing each other, which respectively pass through the LP shaft, the sleeve BP, the HP trunnion and cavities, arranged between these orifices and between these various elements, which are traversed by the oil. In particular, cavities are arranged between the supply rod and the LP shaft, between the LP shaft and the LP sleeve, and between the LP sleeve and the HP pin. A problem arises particularly with regard to the cavity which is arranged between the LP sleeve and the HP spigot. Indeed, this cavity is subjected to a flow of air under pressure moving substantially longitudinally between the sleeve and the journal, which comes from the dynamic seal which is interposed between the sleeve and the trunnion.
Un tel joint d'étanchéité est notamment un joint à labyrinthe qui est susceptible de permettre le passage d'un flux d'air sous pression.  Such a seal is in particular a labyrinth seal which is capable of allowing the passage of a flow of air under pressure.
Le flux d'air sous pression coupe par conséquent le flux d'huile qui circule des orifices débouchant du fourreau vers ceux du tourillon.  The flow of air under pressure consequently cuts the flow of oil flowing from the openings opening from the sleeve to those of the journal.
Par ailleurs, le fourreau est lié en rotation à l'arbre basse-pression et le tourillon est solidaire en rotation de l'arbre haute-pression. Généralement, le fourreau et le tourillon tournent dans le même sens ou en sens inverse l'un de l'autre, à des vitesses différentes, de sorte que le flux d'huile ne bénéficie pas d'un effet de centrifugation optimal. La zone de croisement du flux d'huile et du flux d'air est donc une zone critique, car le flux d'air sous pression tend à chasser l'huile et à la détourner des orifices du tourillon. Ce phénomène est encore plus critique lorsque le fourreau et le tourillon sont contra-rotatifs, car dans ce cas l'huile passe par un point de vitesse radiale nulle.  Furthermore, the sheath is rotatably connected to the low-pressure shaft and the journal is integral in rotation with the high-pressure shaft. Generally, the sheath and the trunnion rotate in the same direction or in opposite directions to one another, at different speeds, so that the oil flow does not benefit from an optimal centrifugation effect. The crossing zone of the oil flow and the air flow is therefore a critical zone, because the pressurized air flow tends to drive the oil away from the pin holes. This phenomenon is even more critical when the sheath and the trunnion are counter-rotating, because in this case the oil passes through a point zero radial velocity.
La lubrification du palier étant effectuée intérieurement, et le flux d'air ne traversant pas le palier, il n'est pas possible d'orienter les orifices d'huile du fourreau de manière que l'huile soit entraînée vers le roulement par le flux d'air, comme cela a été décrit dans le document FR-2524064. EXPOSÉ DE L'INVENTION The lubrication of the bearing being performed internally, and the air flow does not pass through the bearing, it is not possible to orient the oil holes of the sleeve so that the oil is driven to the bearing by the flow of air, as described in FR-2524064. STATEMENT OF THE INVENTION
L'invention a donc pour but de limiter l'effet précédemment évoqué en proposant un fourreau tubulaire qui est configuré pour favoriser le passage du flux d'air entre les orifices traversants dudit fourreau, afin que ledit flux d'air ne dévie pas ou peu le flux d'huile, une enceinte d'huile comportant un tel fourreau et une turbomachine comportant une telle enceinte d'huile. Un tel fourreau est nécessairement tubulaire et ne peut présenter de paroi d'épaulement ayant un encombrement élevé dans laquelle seraient ménagés des passages séparés pour l'huile et l'air. Une telle conception, qui est relative à des tourillons s'étendant dans un plan transversal à l'axe de la turbomachine et comportant des passages d'huile et d'air séparés, a déjà été proposée dans les documents FR-2878287 et FR-2992680, mais n'est pas transposable à un fourreau. The invention therefore aims to limit the previously mentioned effect by providing a tubular sheath which is configured to promote the passage of the air flow between the through holes of said sheath, so that said air flow does not deviate or little the oil flow, an oil chamber comprising such a sleeve and a turbomachine comprising such an oil chamber. Such a sleeve is necessarily tubular and can not have a shoulder wall having a large footprint in which there would be separate passages for oil and air. Such a design, which relates to journals extending in a plane transverse to the axis of the turbomachine and having separate oil and air passages, has already been proposed in documents FR-2878287 and FR- 2992680, but is not transferable to a sheath.
Ainsi, plus généralement, l'invention propose un élément tubulaire de rotor pour une turbomachine, comportant un premier tronçon d'axe longitudinal comprenant une rangée annulaire de premiers orifices radiaux traversants de passage d'huile configurée pour favoriser le passage d'un flux d'air entre lesdits orifices. Thus, more generally, the invention proposes a tubular rotor element for a turbomachine, comprising a first section of longitudinal axis comprising an annular row of first radial through-holes of oil passage configured to facilitate the passage of a flow of oil. air between said orifices.
Il sera compris que l'invention n'entend pas se limiter à un fourreau solidaire d'un arbre basse-pression et à son interaction avec un tourillon haute-pression dans le cadre d'une enceinte d'huile d'une turbomachine, mais trouve à s'appliquer à tout élément tubulaire de rotor destiné à permettre l'acheminement d'un flux d'huile radial dans un environnement traversé par un flux d'air. It will be understood that the invention does not intend to be limited to a sleeve secured to a low-pressure shaft and to its interaction with a high-pressure journal in the context of an oil chamber of a turbomachine, but is applicable to any tubular rotor element intended to allow the routing of a radial oil flow in an environment traversed by a flow of air.
L'invention propose aussi une turbomachine comportant un tel élément tubulaire. Dans ce but, l'invention propose un élément tubulaire de rotor pour une turbomachine, comportant un premier tronçon d'axe longitudinal A comprenant des premiers moyens d'étanchéité et un second tronçon d'axe longitudinal A adjacent comprenant une rangée annulaire de premiers orifices radiaux traversants de passage d'huile, caractérisé en ce que ledit second tronçon présente en section transversale une alternance de premiers secteurs angulaires de passage d'huile, comprenant les premiers orifices radiaux traversants, qui présentent un premier encombrement diamétral D1 autour dudit axe longitudinal, et de seconds secteurs angulaires de guidage d'air qui présentent un second encombrement diamétral D2 autour dudit axe longitudinal, lesdits premier et second encombrements diamétraux D1 et D2 étant différents. The invention also proposes a turbomachine comprising such a tubular element. For this purpose, the invention proposes a tubular rotor element for a turbomachine, comprising a first section of longitudinal axis A comprising first sealing means and a second section of adjacent longitudinal axis A comprising an annular row of first orifices. radial oil passing through, characterized in that said second section has in cross section an alternation of first angular sectors of oil passage, comprising the first through radial orifices, which have a first diametral space D1 around said longitudinal axis, and second angular air guide sectors which have a second diametral bulk D2 about said longitudinal axis, said first and second diametral bulk D1 and D2 being different.
Selon d'autres caractéristiques de l'élément : According to other characteristics of the element:
- le premier encombrement diamétral D1 est supérieur au second encombrement diamétral D2,  the first diameter space D1 is greater than the second diameter space D2,
- le second tronçon présente une section transversale de forme sensiblement ondulée ou en étoile,  the second section has a cross section of substantially corrugated or star shape,
- le second tronçon comporte une paroi d'épaisseur sensiblement constante.  the second section comprises a wall of substantially constant thickness.
L'invention concerne aussi une enceinte d'huile annulaire de turbomachine, délimitée par : The invention also relates to an annular turbomachine oil enclosure, defined by:
- un premier organe tubulaire comportant des première et deuxième parois tubulaires coaxiales reliées l'une à l'autre par au moins une paroi transversale,  a first tubular member comprising first and second coaxial tubular walls connected to one another by at least one transverse wall,
- un élément d'étanchéité, qui est interposé entre ladite troisième paroi dudit second organe tubulaire et une troisième paroi tubulaire coaxiale dudit premier organe, qui ferme ladite enceinte d'huile, un palier étant logé dans ladite enceinte d'huile, et étant interposé entre la troisième paroi du second organe tubulaire et la deuxième paroi du premier organe. Cette enceinte d'huile est caractérisée en ce que la première paroi comporte au moins un élément tubulaire du type précédemment décrit, ledit élément étant logé dans un alésage de la troisième paroi du second organe, ledit alésage comportant un premier tronçon comportant des seconds moyens d'étanchéité s'étendant sensiblement autour desdits premiers moyens d'étanchéité de l'élément tubulaire et un second tronçon comportant une rangée annulaire de deuxièmes orifices radiaux de passage d'huile situés sensiblement au droit desdits premiers orifices radiaux traversants de l'élément tubulaire. Selon d'autres caractéristiques de l'enceinte d'huile : a sealing element, which is interposed between said third wall of said second tubular member and a third coaxial tubular wall of said first member, which closes said oil chamber; a bearing being housed in said oil chamber, and being interposed between the third wall of the second tubular member and the second wall of the first member. This oil chamber is characterized in that the first wall comprises at least one tubular element of the type previously described, said element being housed in a bore of the third wall of the second member, said bore comprising a first section comprising second means of sealing substantially extending around said first sealing means of the tubular element and a second section comprising an annular row of second radial oil passage orifices situated substantially in line with said first radial orifices passing through the tubular element. According to other characteristics of the oil enclosure:
- ledit élément et la troisième paroi du second organe définissent entre eux une cavité longitudinale dans laquelle débouchent les premiers et deuxièmes orifices, ladite cavité étant traversée par un flux d'air provenant des premier et second moyens d'étanchéité configurés en moyens d'étanchéité de type à labyrinthe et traversée par le flux d'huile circulant entre les premiers et deuxièmes orifices,  said element and the third wall of the second member define between them a longitudinal cavity into which the first and second orifices open, said cavity being traversed by a flow of air coming from the first and second sealing means configured as sealing means; of labyrinth type and traversed by the flow of oil circulating between the first and second orifices,
- les premier organe et second organe sont en rotation l'un par rapport à l'autre,  the first member and the second member are rotated relative to one another,
- la première paroi du premier organe est montée sur un arbre intérieur et est solidaire en rotation dudit arbre, ledit élément de la première paroi et ledit arbre définissant entre eux une cavité longitudinale dans laquelle débouchent les premiers orifices et une rangée annulaire de troisièmes orifices radiaux traversants de passage d'huile formés dans ledit arbre,  the first wall of the first member is mounted on an inner shaft and is integral in rotation with said shaft, said element of the first wall and said shaft defining between them a longitudinal cavity into which the first orifices open and an annular row of third radial orifices; oil passagethroughs formed in said shaft,
- les deuxièmes orifices traversent la troisième paroi du second organe et sont configurés pour alimenter en huile le palier. L'invention concerne aussi une turbomachine comportant une enceinte d'huile du type précédemment décrit, caractérisée en ce que la première paroi est un fourreau d'un corps basse-pression de la turbomachine, en ce que l'arbre intérieur est un arbre intérieur basse-pression de la turbomachine, en ce que la deuxième paroi est fixée à ladite première paroi et audit arbre intérieur, et en ce que le second organe est un tourillon d'un arbre extérieur haute-pression de la turbomachine. the second orifices pass through the third wall of the second member and are configured to supply the bearing with oil. The invention also relates to a turbomachine comprising an oil chamber of the type previously described, characterized in that the first wall is a sleeve of a low-pressure body of the turbomachine, in that the inner shaft is an inner shaft low-pressure of the turbomachine, in that the second wall is fixed to said first wall and to said inner shaft, and in that the second member is a journal of a high-pressure outer shaft of the turbomachine.
L'invention sera mieux comprise et d'autres détails, caractéristiques et avantages de la présente invention apparaîtront plus clairement à la lecture de la description qui suit faite à titre d'exemple non limitatif et en référence aux dessins annexés, dans lesquels : The invention will be better understood and other details, characteristics and advantages of the present invention will appear more clearly on reading the following description given by way of nonlimiting example and with reference to the accompanying drawings, in which:
- la figure 1 est une demi-vue en coupe axiale d'une turbomachine ; - Figure 1 is a half-view in axial section of a turbomachine;
- la figure 2 est une vue de détail en coupe axiale d'une enceinte d'huile selon un état antérieur de la technique formée dans une partie aval de la turbomachine de la figure 1 , au voisinage de son palier inter-arbres ; - Figure 2 is a detail view in axial section of an oil chamber according to a prior art formed in a downstream portion of the turbomachine of Figure 1, in the vicinity of its inter-shaft bearing;
- la figure 3 est une vue de détail de la figure 2 ;  - Figure 3 is a detail view of Figure 2;
- la figure 4 est une vue en coupe transversale d'un élément tubulaire selon un état antérieur de la technique ;  - Figure 4 is a cross-sectional view of a tubular element according to a prior art;
- la figure 5 est une vue en coupe transversale d'un élément tubulaire selon l'invention ;  FIG. 5 is a cross-sectional view of a tubular element according to the invention;
- les figures 6A et 6B sont des vues de détail en coupe axiale de parties aval d'une enceinte d'huile selon l'invention formée dans une partie aval d'une turbomachine, au voisinage de son palier inter-arbres, selon deux positions angulaires de l'élément angulaire.  FIGS. 6A and 6B are detailed views in axial section of downstream parts of an oil enclosure according to the invention formed in a downstream part of a turbomachine, in the vicinity of its inter-shaft bearing, in two positions. angles of the angular element.
Dans la description qui va suivre, des chiffres de référence identiques désignent des pièces identiques ou ayant des fonctions similaires. On a représenté à la figure 1 de manière schématique et à titre d'exemple une turbomachine 10 de type à double corps et à double flux. Une telle turbomachine, ici un turboréacteur 10 à double flux, comporte, de manière connue, une soufflante 12, un compresseur basse-pression 14, un compresseur haute-pression 1 6, une chambre de combustion 18, une turbine haute-pression 20, une turbine basse-pression 22, et une tuyère d'échappement 24. Le rotor du compresseur haute-pression HP 1 6 et le rotor de la turbine haute-pression 20 sont reliés par un arbre haute-pression HP 26 et forment avec lui un corps haute-pression. Le rotor du compresseur basse-pression BP 14 et le rotor de la turbine basse- pression BP 22 sont reliés par un arbre basse-pression BP 28 et forment avec lui un corps basse-pression. Chaque compresseur 14, 1 6 ou turbine 20, 22 peut être constitué(e) de plusieurs étages de compresseur ou turbine en série. In the following description, like reference numerals designate like parts or having similar functions. FIG. 1 shows diagrammatically and by way of example a turbomachine 10 of double-body and double-flow type. Such a turbomachine, here a turbojet engine 10, comprises, in known manner, a fan 12, a low-pressure compressor 14, a high-pressure compressor 1 6, a combustion chamber 18, a high-pressure turbine 20, a low-pressure turbine 22, and an exhaust nozzle 24. The rotor of the HP high-pressure compressor 1 6 and the rotor of the high-pressure turbine 20 are connected by an HP high-pressure shaft 26 and form with it a high-pressure body. The rotor of the LP low pressure compressor 14 and the rotor of the LP low pressure turbine 22 are connected by a LP low pressure shaft 28 and form with it a low-pressure body. Each compressor 14, 1 6 or turbine 20, 22 may consist of several stages of compressor or turbine in series.
L'arbre HP 26 et l'arbre BP 28 s'étendent suivant un axe A qui est l'axe global du turboréacteur 10. Dans la suite de la description, les notions de longitudinal ou radial sont relatives à cet axe A. Chacun des arbres basse-pression BP 28 et haute-pression HP 26 sont montés tournants dans un carter 30 du turboréacteur, l'arbre BP 28 étant coaxial et monté intérieurement à l'arbre HP 26. The HP shaft 26 and the LP shaft 28 extend along an axis A which is the global axis of the turbojet engine 10. In the remainder of the description, the notions of longitudinal or radial are relative to this axis A. Each of the Low-pressure BP 28 and high-pressure HP 26 trees are rotatably mounted in a housing 30 of the turbojet engine, the LP shaft 28 being coaxial and mounted internally to the HP shaft 26.
Les corps haute-pression et basse-pression sont traversés par un flux d'air primaire P et la soufflante 12 produit un flux d'air secondaire S qui circule dans le turboréacteur 10, entre le carter 30 et une enveloppe externe 32 du turboréacteur. En sortie de la turbine BP 22, les gaz issus du flux primaire P sont mélangés au flux secondaire S pour produire une force de propulsion, le flux secondaire S fournissant la majorité de la poussée. The high-pressure and low-pressure bodies are traversed by a primary air flow P and the fan 12 produces a secondary air flow S which circulates in the turbojet engine 10, between the casing 30 and an outer casing 32 of the turbojet engine. At the outlet of the LP turbine 22, the gases from the primary flow P are mixed with the secondary flow S to produce a propulsive force, the secondary flow S providing the majority of the thrust.
Le turboréacteur 10 présente, sensiblement au niveau de l'extrémité amont du corps haute-pression, une enceinte dite "amont" 34 contenant des organes de type paliers engrenages et, sensiblement au niveau de l'extrémité aval du corps haute-pression, une enceinte dite "aval" 36 contenant des organes de type paliers, notamment des roulements. En particulier, les arbres BP 28 et HP 26 sont montés tournant l'un par rapport à l'autre par l'intermédiaire d'un palier inter-arbres 52. Les figures 2 et 3 représentent un tel palier inter-arbres 52 au sein de l'enceinte aval 36 de la turbomachine. Comme l'illustre la figure 2, l'enceinte aval 36 de la turbomachine comporte une enceinte d'huile annulaire 38. The turbojet engine 10 has, substantially at the upstream end of the high-pressure body, a so-called "upstream" chamber 34 containing gears bearings and, substantially at the downstream end of the high-pressure body, a so-called "downstream" chamber 36 containing bearing members, including bearings. In particular, the BP 28 and HP 26 trees are mounted rotating relative to each other via an inter-shaft bearing 52. FIGS. 2 and 3 show such an inter-shaft bearing 52 within of the downstream chamber 36 of the turbomachine. As illustrated in FIG. 2, the downstream chamber 36 of the turbomachine comprises an annular oil enclosure 38.
D'une manière générale, cette enceinte d'huile 38 est délimitée, en premier lieu, par un premier organe tubulaire 37 comportant une première paroi tubulaire 39 et une deuxième paroi tubulaire 54 coaxiale.  In general, this oil enclosure 38 is delimited, first, by a first tubular member 37 having a first tubular wall 39 and a second coaxial tubular wall 54.
Les première et deuxième parois tubulaires coaxiales 39, 54 sont reliées l'une à l'autre par au moins une paroi transversale 63.  The first and second coaxial tubular walls 39, 54 are connected to one another by at least one transverse wall 63.
L'enceinte d'huile 38 est délimitée, en second lieu, par un second organe tubulaire 40 d'axe A, qui est reçu au moins en partie dans le premier organe 37 et qui comporte une troisième paroi tubulaire 41 qui reçoit intérieurement au moins en partie ladite première paroi tubulaire 39 du premier organe annulaire 37. De manière connue, des moyens d'étanchéité 48, 49 sont interposés entre les première et troisième parois tubulaires 39, 54.  The oil enclosure 38 is delimited, secondly, by a second tubular member 40 of axis A, which is received at least partly in the first member 37 and which comprises a third tubular wall 41 which receives internally at least in part said first tubular wall 39 of the first annular member 37. In known manner, sealing means 48, 49 are interposed between the first and third tubular walls 39, 54.
L'enceinte d'huile 38 est délimitée, en troisième lieu, par un élément d'étanchéité 51 , par exemple un joint à labyrinthe 51 qui est interposé entre la troisième paroi 41 du second organe 40 tubulaire et une troisième paroi coaxiale 55 du premier organe 37. L'élément d'étanchéité 51 ferme ainsi sensiblement l'enceinte d'huile 38.  The oil enclosure 38 is delimited, thirdly, by a sealing element 51, for example a labyrinth seal 51 which is interposed between the third wall 41 of the second tubular member 40 and a third coaxial wall 55 of the first member 37. The sealing member 51 thus substantially closes the oil chamber 38.
Un palier 52 est logé dans l'enceinte d'huile 38 et est plus particulièrement interposé entre la troisième paroi 41 du second organe 40 tubulaire et la deuxième paroi 54 du premier organe 37. Dans le cas particulier de la turbomachine 10 qui a été ici représentée, la première paroi 39 est un fourreau d'un corps basse-pression BP et elle reçoit une extrémité aval de l'arbre BP basse- pression 28 de la turbomachine 10, à laquelle elle est fixée. A bearing 52 is housed in the oil enclosure 38 and is more particularly interposed between the third wall 41 of the second tubular member 40 and the second wall 54 of the first member 37. In the particular case of the turbomachine 10 which has been shown here, the first wall 39 is a sleeve of a low-pressure body LP and it receives a downstream end of the LP low pressure shaft 28 of the turbomachine 10, which it is fixed.
La deuxième paroi 54 est fixée à ladite première paroi et audit arbre intérieur 28.  The second wall 54 is fixed to said first wall and to said inner shaft 28.
Le second organe 40, d'axe A et coaxial extérieurement à l'arbre BP 28, est constitué d'un tourillon haute-pression HP qui forme une extrémité aval terminale de l'arbre HP 26. La troisième paroi tubulaire 41 de ce second organe 40 reçoit dans un alésage 44 l'élément tubulaire 42 de la première paroi 39.  The second member 40, with axis A and coaxial with the BP shaft 28, consists of an HP high-pressure journal which forms a terminal downstream end of the HP shaft 26. The third tubular wall 41 of this second member 40 receives in a bore 44 the tubular element 42 of the first wall 39.
S'agissant des moyens d'étanchéité 48, 49 interposés entre les première et troisième parois tubulaires 39, 54, l'élément tubulaire 42 comporte un premier tronçon 46 d'axe longitudinal A comprenant des premiers moyens d'étanchéité 48, qui sont entourés par des seconds moyens d'étanchéité 49 portés par un premier tronçon 43 de l'alésage 44. Les seconds moyens d'étanchéité 49 du premier tronçon 43 du second organe 40 sont préférentiellement constitués d'un matériau abradable coopérant avec des léchettes formant les premiers moyens d'étanchéité 48. Les léchettes forment avec le matériau abradable un joint à labyrinthe. En fonctionnement, un flux d'air pressurisé F, représenté par des flèches sur les figures 2 et 3, est susceptible de traverser le joint à labyrinthe et une cavité 50 longitudinale définie entre l'élément 42 et la troisième paroi 41 du second organe 40.  Regarding the sealing means 48, 49 interposed between the first and third tubular walls 39, 54, the tubular element 42 comprises a first section 46 of longitudinal axis A comprising first sealing means 48, which are surrounded by second sealing means 49 carried by a first section 43 of the bore 44. The second sealing means 49 of the first section 43 of the second member 40 are preferably made of an abradable material cooperating with wipers forming the first sealing means 48. The wipers form with the abradable material a labyrinth seal. In operation, a pressurized air flow F, represented by arrows in FIGS. 2 and 3, is able to pass through the labyrinth seal and a longitudinal cavity 50 defined between the element 42 and the third wall 41 of the second member 40 .
Le second organe 40 porte extérieurement le palier 52, interposé entre la troisième paroi 41 et la deuxième paroi 54 du premier organe 37, pour permettre le guidage en rotation de l'arbre HP 26 par rapport à l'arbre BP 28. Dans le mode de réalisation qui a été présenté sur les figures 2 et 3 à titre d'exemple, la deuxième paroi 54 et la première paroi 39 sont des pièces distinctes, liées ensemble par une liaison boulonnée. Plus particulièrement, l'élément tubulaire 42 ou fourreau est lié à la fois à l'arbre BP 28 et à la pièce tubulaire 54 par l'intermédiaire d'une liaison boulonnée 56 dont une vis 58 traverse un épaulement 60 de l'arbre BP 28, un épaulement 62 de la deuxième paroi 54, et un épaulement 64 de l'élément tubulaire 42. The second member 40 externally carries the bearing 52, interposed between the third wall 41 and the second wall 54 of the first member 37, to allow the rotational guidance of the HP shaft 26 relative to the BP shaft 28. In the embodiment which has been shown in Figures 2 and 3 by way of example, the second wall 54 and the first wall 39 are separate parts, joined together by a bolted connection. More particularly, the tubular element 42 or sheath is bonded to both the shaft BP 28 and the tubular part 54 by means of a bolted connection 56, a screw 58 passes through a shoulder 60 of the BP shaft 28, a shoulder 62 of the second wall 54, and a shoulder 64 of the element tubular 42.
Le palier inter-arbres 52 doit être lubrifié à l'aide d'huile provenant de l'enceinte aval 36. A cet effet, un chemin d'huile H, représenté par des flèches, est ménagé entre l'enceinte aval 36 et ce palier 52. Le chemin de l'huile H doit par exemple traverser, successivement et radialement de l'intérieur vers l'extérieur, l'arbre BP 28, l'élément tubulaire 42 ou fourreau BP, et la troisième paroi 41 du second organe 40 ou tourillon HP, qui porte le palier 52. A cet effet, le chemin d'huile H comporte généralement une canne 66 d'alimentation en huile qui est logée à l'intérieur de l'arbre BP 28, des orifices radiaux 68, 70, 72, 74 disposés sous forme de rangées annulaires et agencés sensiblement axialement au droit les uns des autres, qui traversent respectivement la canne 66, l'arbre BP 28, l'élément tubulaire 42 ou fourreau BP, et un second tronçon 45 de la troisième paroi 41 du second organe 40 ou tourillon BP.  The inter-shaft bearing 52 must be lubricated with oil coming from the downstream enclosure 36. For this purpose, an oil path H, represented by arrows, is provided between the downstream enclosure 36 and this Bearing 52. The path of the oil H must for example cross, successively and radially from the inside to the outside, the LP shaft 28, the tubular element 42 or sleeve BP, and the third wall 41 of the second member 40 or HP journal, which carries the bearing 52. For this purpose, the oil path H generally comprises an oil supply rod 66 which is housed inside the LP shaft 28, radial orifices 68, 70, 72, 74 arranged in the form of annular rows and arranged substantially axially to the right of each other, which respectively pass through the rod 66, the LP shaft 28, the tubular element 42 or sleeve BP, and a second section 45 of the third wall 41 of the second member 40 or LP trunnion.
Dans la suite de la présente description, les orifices radiaux 72,74 et 70 seront respectivement désignés premiers orifices radiaux 72, deuxièmes orifices radiaux 74, et troisièmes orifices radiaux 70.  In the remainder of the present description, the radial orifices 72, 74 and 70 will respectively be designated first radial orifices 72, second radial orifices 74, and third radial orifices 70.
Entre la canne 66, l'arbre BP 28, l'élément tubulaire 42 ou fourreau BP, le second organe 40 ou tourillon HP, et notamment entre leurs orifices radiaux 68, 70, 72, 74, le chemin d'huile traverse des cavités 50, 76, 78. En particulier, une cavité 76 est agencée entre la canne d'alimentation 66 et l'arbre BP 28, une cavité 78 est agencée entre l'arbre BP 28 et l'élément tubulaire 42 ou fourreau BP, et la cavité 50 est agencée entre l'élément tubulaire 42 et la troisième paroi 41 du second organe 40 ou tourillon HP. Les premiers orifices traversants 72 et les troisièmes orifices traversants 70 débouchent donc dans la cavité 78, tandis que les premiers orifices traversants 72 et les deuxièmes orifices traversants 74 débouchent dans la cavité 50. Between the rod 66, the LP shaft 28, the tubular element 42 or sheath BP, the second member 40 or pin HP, and especially between their radial orifices 68, 70, 72, 74, the oil path passes through cavities 50, 76, 78. In particular, a cavity 76 is arranged between the supply rod 66 and the LP shaft 28, a cavity 78 is arranged between the LP shaft 28 and the tubular element 42 or sleeve BP, and the cavity 50 is arranged between the tubular element 42 and the third wall 41 of the second member 40 or HP trunnion. The first through orifices 72 and the third through orifices 70 thus open into the cavity 78, while the first orifices through-holes 72 and the second through-holes 74 open into the cavity 50.
Un problème se pose particulièrement en ce qui concerne la cavité 50 qui est agencée entre l'élément tubulaire 42 ou fourreau BP et la troisième paroi 41 . En effet, comme on l'a vu, cette cavité 50 est soumise au flux d'air F sous pression se déplaçant sensiblement longitudinalement entre l'élément 42 et la troisième paroi 41 . Le flux d'air F sous pression coupe par conséquent le flux d'huile H qui circule des premiers orifices radiaux 72 débouchant de l'élément 42 vers les deuxièmes orifices 74 de la troisième paroi 41 . A problem arises particularly with regard to the cavity 50 which is arranged between the tubular element 42 or sheath BP and the third wall 41. Indeed, as we have seen, this cavity 50 is subjected to the flow of air F under pressure moving substantially longitudinally between the element 42 and the third wall 41. The flow of air F under pressure consequently cuts the flow of oil H which circulates from the first radial orifices 72 opening out from the element 42 to the second orifices 74 of the third wall 41.
Le flux d'air F est donc susceptible d'interférer avec le flux d'huile H et de le dévier, ce qui peut conduire à une mauvaise lubrification du palier ou roulement 52.  The air flow F is therefore likely to interfere with the flow of oil H and to deflect it, which can lead to poor lubrication of the bearing or bearing 52.
Ce problème est d'autant plus sensible que le premier organe 37, qui est lié à l'arbre BP 28, d'une part et la troisième paroi 41 , qui fait partie du second organe 40 et est donc liée à l'arbre HP 26, d'autre part, tournent l'un par rapport à l'autre. L'élément 42, qui fait partie du premier organe 37, tourne donc par rapport à la troisième paroi 41 . Ainsi, le flux d'huile H ne bénéficie pas d'un effet de centrifugation optimal, ce qui le rend susceptible d'être plus facilement dévié par le flux d'air F.  This problem is more sensitive than the first member 37, which is connected to the BP shaft 28, on the one hand and the third wall 41, which is part of the second member 40 and is therefore linked to the HP shaft 26, on the other hand, rotate relative to each other. The element 42, which is part of the first member 37, thus rotates relative to the third wall 41. Thus, the oil flow H does not benefit from an optimal centrifugation effect, which makes it likely to be more easily deflected by the air flow F.
De plus, lorsque le fourreau et le tourillon sont contra-rotatifs, l'huile passant dans la cavité 50 passe par un point de vitesse nulle, et est donc à même d'être encore plus facilement déviée.  In addition, when the sheath and the trunnion are counter-rotating, the oil passing through the cavity 50 passes through a point of zero velocity, and is therefore able to be more easily deflected.
La zone de croisement du flux d'huile H et du flux d'air F dans la cavité 50 est en tout état de cause une zone critique, que l'élément 42 et la troisième paroi 41 soient co-rotatifs ou contra-rotatifs.  The crossing zone of the oil flow H and the air flow F in the cavity 50 is in any case a critical zone, the element 42 and the third wall 41 are co-rotating or counter-rotating.
Pour limiter cet effet, l'invention propose un élément tubulaire 42 qui est configuré pour favoriser le passage du flux d'air entre ses orifices traversants 72, afin que ledit flux d'air F baignant ledit élément 42 ne dévie pas ou peu le flux d'huile H. L'invention propose aussi une cavité d'huile 38 comportant un tel élément 42, et une turbomachine 10 comportant une telle cavité d'huile 38. L'élément tubulaire 42 comprend le premier tronçon 46 d'axe longitudinal A comprenant les premiers moyens d'étanchéité 48, et un second tronçon 80 d'axe longitudinal A adjacent qui comprend la rangée annulaire des premiers orifices radiaux 72 traversants de passage d'huile. Dans une configuration conventionnelle de l'enceinte d'huile, comme l'illustre la figure 4, le second tronçon 80 de l'élément 42 est d'un diamètre D constant, de sorte que le jeu J, correspondant à la cavité 50, entre le second tronçon 80 et le second organe 40, est identique suivant toute la périphérie dudit second tronçon 80. To limit this effect, the invention proposes a tubular element 42 which is configured to promote the passage of air flow between its through holes 72, so that said air flow F bathing said element 42 does not deviate The invention also proposes an oil cavity 38 comprising such an element 42, and a turbomachine 10 comprising such an oil cavity 38. The tubular element 42 comprises the first section 46. longitudinal axis A comprising the first sealing means 48, and a second section 80 of adjacent longitudinal axis A which comprises the annular row of the first radial orifices 72 passing through oil. In a conventional configuration of the oil chamber, as illustrated in FIG. 4, the second section 80 of the element 42 has a constant diameter D, so that the clearance J corresponding to the cavity 50, between the second section 80 and the second member 40, is identical along the entire periphery of said second section 80.
Dans la configuration de l'enceinte d'huile selon l'invention, comme l'illustre la figure 5, le second tronçon 80 présente en section transversale une alternance de premiers secteurs angulaires 82 de passage d'huile, comprenant les premiers orifices radiaux traversants 72, qui présentent un premier encombrement diamétral D1 autour de l'axe longitudinal A, et de seconds secteurs angulaires 84 de guidage d'air qui présentent un second encombrement diamétral D2 autour dudit axe longitudinal A. Le premier encombrement diamétral D1 est configuré pour que les premiers orifices radiaux traversants 72 soient au plus près de l'alésage 44 de la troisième paroi 41 du tourillon HP 40, et le second encombrement diamétral D2 est configuré pour que, dans les seconds secteurs angulaires 84, la paroi du second tronçon 80 soit au plus loin de l'alésage 44 de la troisième paroi 41 du tourillon HP 40. Ceci permet de définir une section importante pour le passage du flux d'air F, lesdits premier et second encombrements diamétraux D1 et D2 étant différents.  In the configuration of the oil chamber according to the invention, as illustrated in FIG. 5, the second section 80 has in cross-section an alternation of first angular sectors 82 of oil passage, comprising the first radial orifices passing through. 72, which have a first diametral space D1 around the longitudinal axis A, and second angular sectors 84 of air guide which have a second diameter space D2 around said longitudinal axis A. The first diameter space D1 is configured so that the first radial through-holes 72 are as close as the bore 44 of the third wall 41 of the HP trunnion 40, and the second diametrical space D2 is configured so that, in the second angular sectors 84, the wall of the second segment 80 is further away from the bore 44 of the third wall 41 of the HP 40 trunnion. This makes it possible to define an important section for the passage of the air flow F, said p first and second dimensional diameters D1 and D2 being different.
S'agissant d'un élément tubulaire 42 qui est reçu intérieurement à la troisième paroi 41 , le premier encombrement diamétral D1 est supérieur au second encombrement diamétral D2. Il sera compris qu'une configuration inverse serait à prévoir dans le cas d'un élément tubulaire 42 entourant au contraire un organe coaxial 40 qu'il doit alimenter en huile, par exemple un tube coaxial d'amenée d'huile. Ainsi, en ce cas, dans le cas d'un élément tubulaire 42 entourant au contraire un organe coaxial 40 qu'il devrait alimenter en huile, le second tronçon 80 présenterait en section transversale une alternance de premiers secteurs angulaires de passage d'huile, comprenant les premiers orifices radiaux traversants qui présenteraient un premier encombrement diamétral réduit autour de l'axe longitudinal A, inférieur à celui de seconds secteurs angulaires de guidage d'air qui quant à eux présenteraient un second encombrement diamétral autour dudit axe longitudinal A. Le second tronçon 80 présenterait ainsi une forme lobée. Being a tubular element 42 which is received internally at the third wall 41, the first diametral space D1 is greater than second diameter space D2. It will be understood that an opposite configuration would be expected in the case of a tubular element 42 surrounding on the contrary a coaxial member 40 that must supply oil, for example a coaxial tube for supplying oil. Thus, in this case, in the case of a tubular element 42 surrounding on the contrary a coaxial member 40 that it should supply oil, the second section 80 would have in cross section an alternation of first angular sectors of oil passage, comprising the first radial orifices through which would have a first reduced diametral space around the longitudinal axis A, less than that of second angular sectors of air guide which in turn have a second diameter space around said longitudinal axis A. The second section 80 would thus have a lobed shape.
Dans cette configuration, on comprend que la différence des encombrements diamétraux D1 et D2 entre les secteurs angulaires 82 et 84 conduisent lesdits secteurs angulaires 82, 84 du second tronçon 80 de l'élément tubulaire 42 à former des jeux différents J1 , J2 avec la troisième paroi 41 du second organe 40, c'est dire avec les bords de la cavité 50.  In this configuration, it is understood that the difference in diametral bulk D1 and D2 between the angular sectors 82 and 84 lead said angular sectors 82, 84 of the second section 80 of the tubular element 42 to form different games J1, J2 with the third wall 41 of the second member 40, ie with the edges of the cavity 50.
Ainsi, chaque secteur angulaire 82, qui comprend les premiers orifices 72, forme avec la troisième paroi 41 du second organe 40 un jeu J1 qui est inférieur à un jeu J2 formé entre le secteur angulaire adjacent 84 et cette même troisième paroi 41 . Ce jeu supérieur J2 est donc à même de permettre au secteur angulaire 84 de former un passage privilégié de section de passage élevée pour le flux d'air sous pression F, qui passe donc dans chaque secteur angulaire 84 entre deux secteurs angulaires 82, plutôt qu'au-dessus des premiers orifices 72. Cette configuration permet ainsi d'éviter en grande partie la déviation du flux d'huile H par le flux d'air F. De ce fait, le flux d'huile H peut passer pratiquement sans être dévié des premiers orifices radiaux 72 traversants de l'élément tubulaire 42 à la rangée annulaire de deuxièmes orifices radiaux 74 de passage d'huile formés dans le second tronçon 45 de la troisième paroi 41 . A titre d'exemple, et pour fournir un ordre de grandeur, le jeu J1 peut correspondre à environ 3% du diamètre du second organe 40 ou tourillon, tandis que le jeu J2 peut correspondre à environ 8% du diamètre de l'organe 40 ou tourillon. Thus, each angular sector 82, which comprises the first orifices 72, forms with the third wall 41 of the second member 40 a clearance J1 which is smaller than a clearance J2 formed between the adjacent angular sector 84 and the same third wall 41. This upper clearance J2 is thus able to allow the angular sector 84 to form a preferred passage of high passage section for the flow of pressurized air F, which therefore passes in each angular sector 84 between two angular sectors 82, rather than above the first orifices 72. This configuration thus makes it possible to largely avoid the deflection of the flow of oil H by the flow of air F. As a result, the flow of oil H can pass virtually without being deviated from the first radial orifices 72 passing through the tubular element 42 to the annular row of second radial oil passage orifices 74 formed in the second section 45 of the third wall 41. By way of example, and to provide an order of magnitude, the clearance J1 can correspond to approximately 3% of the diameter of the second member 40 or trunnion, while the clearance J2 can correspond to approximately 8% of the diameter of the member 40. or trunnion.
Dans le mode de réalisation préféré de l'invention, comme représenté à la figure 5, le second tronçon 80 présente une section transversale de forme sensiblement ondulée ou en étoile. Cette section peut être obtenue par tout procédé connu de l'état de la technique permettant la réalisation de cette section.  In the preferred embodiment of the invention, as shown in Figure 5, the second section 80 has a substantially corrugated cross section or star. This section can be obtained by any known method of the state of the art for carrying out this section.
L'élément tubulaire 42 peut ainsi être le résultat d'opérations de moulage et d'usinage. Il peut aussi être réalisé sous la forme d'un assemblage de tronçons axiaux obtenus par des techniques différentes. On pourrait ainsi envisager de réaliser le second tronçon 82 sous la forme d'un profilé obtenu par passage dans une filière.  The tubular element 42 may thus be the result of molding and machining operations. It can also be realized in the form of an assembly of axial sections obtained by different techniques. One could thus consider making the second section 82 in the form of a profile obtained by passing through a die.
Dans le mode de réalisation préféré de l'invention, le second tronçon In the preferred embodiment of the invention, the second section
80 de l'élément 42 comporte une paroi 86 d'épaisseur E sensiblement constante. Cette configuration permet d'homogénéiser les contraintes dans le second tronçon 80 et est par ailleurs particulièrement adaptée à la réalisation de ce second tronçon par passage dans une filière. 80 of the element 42 has a wall 86 of substantially constant thickness E. This configuration makes it possible to homogenize the stresses in the second section 80 and is also particularly suitable for producing this second section by passing through a die.
Avantageusement, la paroi 85 est continue, c'est-à-dire qu'il n'y pas de discontinuité de cette paroi entre un premier secteur 82 et un second secteur 84 adjacent.  Advantageously, the wall 85 is continuous, that is to say there is no discontinuity of this wall between a first sector 82 and a second sector 84 adjacent.
Comme l'illustre la figure 5, la section ondulée ou configurée en étoile du second tronçon présente ainsi des bras 88 qui délimitent les premiers secteurs angulaires 82 de passage d'huile et dont les parois de liaison 90, agencées entre deux bras consécutifs 88 constituent les seconds secteurs angulaires 84 de guidage d'air. As illustrated in FIG. 5, the corrugated or star-shaped section of the second section thus has arms 88 which delimit the first angular sectors 82 of oil passage and whose connecting walls 90, arranged between two consecutive arms 88 constitute the second angular sectors 84 of air guidance.
Comme l'illustre les figures 6A et 6B qui représentent l'agencement d'un élément 42 selon l'invention dans l'enceinte aval 36 d'une turbomachine selon deux positions angulaires de l'élément 42, on remarque que le second tronçon 80 s'étend de préférence axialement sur l'arbre BP 28 depuis les premiers orifices 72 jusqu'à au moins une partie 92 de l'arbre BP 28 qui est agencée hors de l'organe 40. Cette configuration permet d'assurer le passage de l'air le long des secteurs angulaires 84 jusqu'à une partie de l'arbre BP 28 où ils débouchent librement, et d'éviter ainsi toute restriction du débit d'air. As illustrated in FIGS. 6A and 6B, which represent the arrangement of an element 42 according to the invention in the downstream enclosure 36 of a turbomachine according to two angular positions of the element 42, one note that the second section 80 preferably extends axially on the LP shaft 28 from the first orifices 72 to at least a portion 92 of the LP shaft 28 which is arranged outside the member 40. to ensure the passage of air along the angular sectors 84 to a portion of the BP shaft 28 where they open freely, and thus avoid any restriction of the air flow.
On remarquera que les axes des premiers orifices 72 de l'élément tubulaire des deuxièmes orifices 74 sont de préférence proches, afin de limiter les dispersions du flux d'huile H. Sur les figures 6A et 6B, les axes des premiers orifices 72 de l'élément 42 et des deuxièmes orifices 74 de l'organe 40 se coupent sensiblement dans la cavité 50, sans que cette configuration soit limitative de l'invention.  It will be noted that the axes of the first orifices 72 of the tubular element of the second orifices 74 are preferably close, in order to limit the dispersions of the oil flow H. In FIGS. 6A and 6B, the axes of the first orifices 72 of the element 42 and second orifices 74 of the member 40 intersect substantially in the cavity 50, without this configuration being limiting of the invention.
On constate donc, dans la position angulaire de la coupe de la figure 6B, que les seconds secteurs angulaires 84 permettent de dégager un passage conséquent pour le flux d'air F, qui n'interfère que pas ou peu avec le flux d'huile H.  Thus, in the angular position of the section of FIG. 6B, it can be seen that the second angular sectors 84 make it possible to disengage a substantial passage for the flow of air F, which interferes only slightly or little with the flow of oil. H.
L'invention a été décrite en relation avec une enceinte d'huile 38 recevant un palier inter-arbres 52 agencé entre un arbre BP 28 et HP 26 et délimitant entre ces arbres une cavité 50. Il sera compris que l'invention peut également s'appliquer à une cavité agencée entre un arbre et un carter fixe sans changer la nature de l'invention.  The invention has been described in relation to an oil chamber 38 receiving an inter-shaft bearing 52 arranged between a BP 28 and HP 26 shaft and delimiting between these trees a cavity 50. It will be understood that the invention can also be to apply to a cavity arranged between a shaft and a fixed casing without changing the nature of the invention.
L'invention trouve donc à s'appliquer à tout élément tubulaire rotatif monté dans un organe qu'il doit alimenter par des séries d'orifices traversants agencés les uns au droit des autres.  The invention therefore applies to any rotatable tubular element mounted in an organ that it must feed through a series of through holes arranged one to the right of the others.

Claims

REVENDICATIONS
1 . Elément (42) tubulaire de rotor pour une turbomachine, comportant un premier tronçon (46) d'axe longitudinal A comprenant des premiers moyens d'étanchéité (48) et un second tronçon (80) d'axe longitudinal A adjacent comprenant une rangée annulaire de premiers orifices radiaux (72) traversants de passage d'huile, 1. Tubular rotor element (42) for a turbomachine, comprising a first section (46) of longitudinal axis A comprising first sealing means (48) and a second section (80) of adjacent longitudinal axis A comprising an annular row first radial orifices (72) through which oil passes through,
caractérisé en ce que ledit second tronçon (80) présente en section transversale une alternance de premiers secteurs angulaires (82) de passage d'huile, comprenant les premiers orifices radiaux (72) traversants, qui présentent un premier encombrement diamétral (D1 ) autour dudit axe A longitudinal, et de seconds secteurs angulaires (84) de guidage d'air qui présentent un second encombrement diamétral (D2) autour dudit axe longitudinal (A), lesdits premier et second encombrements diamétraux (D1 ) et (D2) étant différents. characterized in that said second section (80) has in cross section an alternation of first angular sectors (82) for oil passage, comprising the first through radial orifices (72), which have a first diametrical bulk (D1) around said longitudinal axis A, and second angular air guide sectors (84) which have a second diametrical footprint (D2) around said longitudinal axis (A), said first and second diametrical dimensions (D1) and (D2) being different.
2. Elément tubulaire (42) selon la revendication précédente, caractérisé en ce que le premier encombrement diamétral (D1 ) est supérieur au second encombrement diamétral (D2). 2. Tubular element (42) according to the preceding claim, characterized in that the first diametrical bulk (D1) is greater than the second diametrical bulk (D2).
3. Elément tubulaire (42) selon la revendication précédente, caractérisé ce que le second tronçon (80) présente une section transversale de forme sensiblement ondulée ou en étoile. 3. Tubular element (42) according to the preceding claim, characterized in that the second section (80) has a cross section of substantially wavy or star shape.
4. Elément tubulaire (42) selon l'une des revendications précédentes, caractérisé en ce que ledit second tronçon (80) comporte une paroi (86) d'épaisseur (E) sensiblement constante. 4. Tubular element (42) according to one of the preceding claims, characterized in that said second section (80) comprises a wall (86) of substantially constant thickness (E).
5. Enceinte d'huile annulaire (38) de turbomachine (10), délimitée par : 5. Annular oil enclosure (38) of turbomachine (10), delimited by:
- un premier organe tubulaire (37) comportant des première et deuxième parois tubulaires coaxiales (39, 54) reliées l'une à l'autre par au moins une paroi transversale (63), - a first tubular member (37) comprising first and second coaxial tubular walls (39, 54) connected to each other by at least one transverse wall (63),
- un second organe tubulaire (40) d'axe (A), qui est reçu au moins en partie dans le premier organe (37) et qui comporte une troisième paroi tubulaire (41 ) qui reçoit intérieurement au moins en partie ladite première paroi tubulaire (39) du premier organe annulaire (37), des moyens d'étanchéité (48, 49) étant interposés entre lesdites première et troisième parois tubulaires (37, 41 ), et - a second tubular member (40) of axis (A), which is received at least partly in the first member (37) and which comprises a third wall tubular (41) which internally receives at least in part said first tubular wall (39) of the first annular member (37), sealing means (48, 49) being interposed between said first and third tubular walls (37, 41) , And
- un élément d'étanchéité (51 ), qui est interposé entre ladite troisième paroi (41 ) dudit second organe (40) tubulaire et une troisième paroi tubulaire coaxiale (55) dudit premier organe (37), qui ferme ladite enceinte d'huile (38), - a sealing element (51), which is interposed between said third wall (41) of said second tubular member (40) and a third coaxial tubular wall (55) of said first member (37), which closes said oil enclosure (38),
un palier (52) étant logé dans ladite enceinte d'huile (38), et étant interposé entre la troisième paroi (41 ) du second organe tubulaire (40) et la deuxième paroi (54) du premier organe (37), a bearing (52) being housed in said oil enclosure (38), and being interposed between the third wall (41) of the second tubular member (40) and the second wall (54) of the first member (37),
caractérisée en ce que la première paroi (39) comporte au moins un élément tubulaire (42) selon l'une des revendications précédentes, ledit élément (42) étant logé dans un alésage (44) de la troisième paroi (41 ) du deuxième organe (40), characterized in that the first wall (39) comprises at least one tubular element (42) according to one of the preceding claims, said element (42) being housed in a bore (44) of the third wall (41) of the second member (40),
ledit alésage (44) de ladite troisième paroi (41 ) comportant un premier tronçon (43) comportant des seconds moyens d'étanchéité (49) s'étendant sensiblement autour desdits premiers moyens d'étanchéité (48) de l'élément tubulaire (42) et un second tronçon (45) comportant une rangée annulaire de deuxièmes orifices radiaux (74) de passage d'huile situés sensiblement au droit desdits premiers orifices radiaux (72) traversants de l'élément tubulaire (42). said bore (44) of said third wall (41) comprising a first section (43) comprising second sealing means (49) extending substantially around said first sealing means (48) of the tubular element (42 ) and a second section (45) comprising an annular row of second radial orifices (74) for oil passage located substantially in line with said first radial orifices (72) passing through the tubular element (42).
6. Enceinte d'huile (38) selon la revendication précédente, caractérisée en ce que ledit élément (42) et la troisième paroi (41 ) du deuxième organe (40) définissent entre eux une cavité longitudinale (50) dans laquelle débouchent les premiers et deuxièmes orifices (72, 74), ladite cavité (50) étant traversée par un flux d'air (F) provenant des premier et second moyens d'étanchéité (48, 49) configurés en moyens d'étanchéité de type à labyrinthe, et traversée par le flux d'huile (H) circulant entre les premiers et deuxièmes orifices (72, 74). 6. Oil enclosure (38) according to the preceding claim, characterized in that said element (42) and the third wall (41) of the second member (40) define between them a longitudinal cavity (50) into which the first ones open and second orifices (72, 74), said cavity (50) being crossed by a flow of air (F) coming from the first and second sealing means (48, 49) configured as labyrinth type sealing means, and crossed by the flow of oil (H) circulating between the first and second orifices (72, 74).
7. Enceinte d'huile (38) selon la revendication précédente, caractérisée en ce que les premier organe (37) et deuxième organe (40) sont en rotation l'un par rapport à l'autre. 7. Oil enclosure (38) according to the preceding claim, characterized in that the first member (37) and second member (40) rotate relative to each other.
8. Enceinte d'huile (38) selon l'une des revendications 5 à 7, caractérisée en ce que la première paroi (39) du premier organe (37) est montée sur un arbre intérieur (28) et est solidaire en rotation dudit arbre (28), ledit élément (42) de la première paroi (39) et ledit arbre (28) définissant entre eux une cavité longitudinale (78) dans laquelle débouchent les premiers orifices (72) et une rangée annulaire de troisièmes orifices radiaux traversants (70) de passage d'huile formés dans ledit arbre (28). 8. Oil enclosure (38) according to one of claims 5 to 7, characterized in that the first wall (39) of the first member (37) is mounted on an internal shaft (28) and is integral in rotation with said shaft (28), said element (42) of the first wall (39) and said shaft (28) defining between them a longitudinal cavity (78) into which the first orifices (72) open and an annular row of third radial through orifices (70) of oil passage formed in said shaft (28).
9. Enceinte d'huile (38) selon l'une des revendications 5 à 8, caractérisée en ce que les deuxièmes orifices (74) traversent la troisième paroi (41 ) du second organe (40) et sont configurés pour alimenter en huile le palier (52). 9. Oil enclosure (38) according to one of claims 5 to 8, characterized in that the second orifices (74) pass through the third wall (41) of the second member (40) and are configured to supply oil to the bearing (52).
10. Turbomachine (10) comportant une enceinte d'huile selon l'une des revendications 5 à 9, caractérisée en ce que la première paroi (39) est un fourreau d'un corps basse-pression de la turbomachine, en ce que l'arbre intérieur (28) est un arbre intérieur basse-pression de la turbomachine (10), en ce que la deuxième paroi (54) est fixée à ladite première paroi (39) et audit arbre intérieur (28) et en ce que le second organe (40) est un tourillon d'un arbre extérieur haute-pression (26) de ladite turbomachine (10). 10. Turbomachine (10) comprising an oil enclosure according to one of claims 5 to 9, characterized in that the first wall (39) is a sheath of a low-pressure body of the turbomachine, in that the the inner shaft (28) is a low-pressure inner shaft of the turbomachine (10), in that the second wall (54) is fixed to said first wall (39) and to said inner shaft (28) and in that the second member (40) is a journal of a high-pressure external shaft (26) of said turbomachine (10).
PCT/FR2017/051476 2016-06-10 2017-06-09 Tubular rotor element for a turbomachine, having a star-shaped cross-section WO2017212196A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1655382A FR3052487B1 (en) 2016-06-10 2016-06-10 ROTOR TUBULAR ELEMENT WITH ETOILEE SECTION FOR TURBOMACHINE
FR1655382 2016-06-10

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WO2017212196A1 true WO2017212196A1 (en) 2017-12-14

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3065755A1 (en) * 2017-04-27 2018-11-02 Safran Aircraft Engines OIL RECOVERY IN A TURBOMACHINE

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2524064A1 (en) 1982-03-26 1983-09-30 Snecma LUBRICATION AND COOLING DEVICE FOR INTER-SHAFT BEARING OF A TURBOMACHINE
FR2878287A1 (en) 2004-11-25 2006-05-26 Snecma Moteurs Sa Two flow twin-spool jet engine for e.g. jumbo jet, has electric current generator connected to rear end, of low pressure rotor, extending downstream from air duct tube and enclosure connecting unit
WO2010119115A1 (en) * 2009-04-17 2010-10-21 Snecma Double-body gas turbine engine provided with an inter-shaft bearing
FR2974143A1 (en) * 2011-04-18 2012-10-19 Snecma Turboshaft engine i.e. turbojet, for propelling aircraft, has high pressure shaft comprising distribution openings that distribute oil from space to bearing and extend obliquely relative to radial direction defined by axis of engine
FR2992680A1 (en) 2012-06-28 2014-01-03 Snecma TURBOMACHINE TOURILLON COMPRISING A CROWN FOR RECOVERING A FLOW OF LUBRICATING OIL WITH A PLURALITY OF ORIFICES

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2524064A1 (en) 1982-03-26 1983-09-30 Snecma LUBRICATION AND COOLING DEVICE FOR INTER-SHAFT BEARING OF A TURBOMACHINE
FR2878287A1 (en) 2004-11-25 2006-05-26 Snecma Moteurs Sa Two flow twin-spool jet engine for e.g. jumbo jet, has electric current generator connected to rear end, of low pressure rotor, extending downstream from air duct tube and enclosure connecting unit
WO2010119115A1 (en) * 2009-04-17 2010-10-21 Snecma Double-body gas turbine engine provided with an inter-shaft bearing
FR2974143A1 (en) * 2011-04-18 2012-10-19 Snecma Turboshaft engine i.e. turbojet, for propelling aircraft, has high pressure shaft comprising distribution openings that distribute oil from space to bearing and extend obliquely relative to radial direction defined by axis of engine
FR2992680A1 (en) 2012-06-28 2014-01-03 Snecma TURBOMACHINE TOURILLON COMPRISING A CROWN FOR RECOVERING A FLOW OF LUBRICATING OIL WITH A PLURALITY OF ORIFICES

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3065755A1 (en) * 2017-04-27 2018-11-02 Safran Aircraft Engines OIL RECOVERY IN A TURBOMACHINE

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FR3052487A1 (en) 2017-12-15

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