WO2021148756A1 - Fluid recovery assembly - Google Patents

Fluid recovery assembly Download PDF

Info

Publication number
WO2021148756A1
WO2021148756A1 PCT/FR2021/050109 FR2021050109W WO2021148756A1 WO 2021148756 A1 WO2021148756 A1 WO 2021148756A1 FR 2021050109 W FR2021050109 W FR 2021050109W WO 2021148756 A1 WO2021148756 A1 WO 2021148756A1
Authority
WO
WIPO (PCT)
Prior art keywords
end piece
piece
assembly
annular wall
orifice
Prior art date
Application number
PCT/FR2021/050109
Other languages
French (fr)
Inventor
Yannick Durand
Vincent GOYON
Original Assignee
Safran Aircraft Engines
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines filed Critical Safran Aircraft Engines
Publication of WO2021148756A1 publication Critical patent/WO2021148756A1/en

Links

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
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L41/00—Branching pipes; Joining pipes to walls
    • F16L41/08—Joining pipes to walls or pipes, the joined pipe axis being perpendicular to the plane of the wall or to the axis of another pipe
    • F16L41/10—Joining pipes to walls or pipes, the joined pipe axis being perpendicular to the plane of the wall or to the axis of another pipe the extremity of the pipe being screwed into the wall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/602—Drainage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/609—Deoiling or demisting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/84—Redundancy
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B39/00—Locking of screws, bolts or nuts
    • F16B39/02—Locking of screws, bolts or nuts in which the locking takes place after screwing down
    • F16B39/10—Locking of screws, bolts or nuts in which the locking takes place after screwing down by a plate, spring, wire or ring immovable with regard to the bolt or object and mainly perpendicular to the axis of the bolt
    • F16B39/101—Locking of screws, bolts or nuts in which the locking takes place after screwing down by a plate, spring, wire or ring immovable with regard to the bolt or object and mainly perpendicular to the axis of the bolt with a plate, spring, wire or ring holding two or more nuts or bolt heads which are mainly in the same plane

Definitions

  • TITLE Fluid recuperator assembly.
  • This document relates to a fluid recovery assembly, preferably for a low pressure turbine of a turbomachine.
  • FIG. 1 conventionally represents a portion of a gas turbomachine for a known aircraft, comprising an exhaust casing 1.
  • the exhaust casing 1 is best seen in Figure 2.
  • the exhaust casing 1 is generally disposed at the outlet of a turbine 25, most often the low-pressure turbine, and before an ejection nozzle (not shown). ) where the gases exit the turbomachine, downstream.
  • Upstream (AM) and downstream (AV) are defined with respect to the direction of flow of the gas flow in the turbomachine 10, parallel to the X axis which is therefore the flow axis of the gas flow in the turbomachine, from upstream to downstream, and around which the rotating (rotor) elements rotate when the turbomachine is operating.
  • the direction of the gas flow from upstream to downstream in the turbomachine is represented by the arrow F in Figure 1.
  • the exhaust casing 1 is a structural part, which serves in particular to maintain the structure of the turbomachine.
  • the exhaust casing 1 is surrounded by a nacelle symbolized by the reference 4 in FIG. 1 which allows the turbomachine to be shrouded in order to protect it from the external environment.
  • the exhaust housing 1 comprises a hub 2 having the shape of a crown which is arranged inside an outer crown 3 or ferrule. Between the hub 2 and the outer ring 3 are arranged a plurality of structural arms 10. These structural arms 10, which may in particular be radial or tangential, are arranged circumferentially (therefore around the X axis) and connect the hub 2 to the outer ring 3.
  • Structural arms can be predominantly radial or predominantly tangential (tending towards the Y axis).
  • An arm which extends predominantly radially / tangentially with respect to hub 2 extends predominantly in the radial / tangential direction.
  • the arms 10 in Figures 1-2 are mainly radial but could be mainly tangential.
  • the spaces between the arms 10 define exhaust openings 5, in which circulates the primary air flow of the turbomachine coming from the combustion chamber.
  • the outer ring 3 has, in particular at the upstream end, at least one flange 11.
  • the flange 11 extends over all or part of the outer circumference of the ring. external 3. It is generally a radial flange extending outwardly from the circumference of the external crown 3.
  • the exhaust casing may include a groove which is formed downstream and close to the upstream fixing flange of this casing and which constitutes a dead zone, that is to say sheltered from the flow. primary. It is common for fluids, such as water, fuel and / or oil, to be trapped in an area at 6 o'clock, that is, at a low point, in this groove. In fact, when the engine is restarted following an aborted start, for example, fuel is found in the groove. To prevent such fluids from stagnating in the low pressure turbine, these fluids must therefore be able to be drained from the engine without impacting the nacelle surrounding the engine.
  • the low pressure turbine In order to provide drainage, the low pressure turbine must have one or more exhaust ducts at the lowest possible point. This discharge duct evacuates the fluids that may be in the groove of the low pressure turbine to a collecting bowl.
  • the low pressure turbine has a fluid recovery assembly 40 comprising two discharge conduits 42 which are screwed to the end pieces 44 as shown in Figure 3.
  • the end pieces 44 which are welded to the housing and connected to the exhaust duct 42 can be damaged or even broken.
  • the replacement of said end pieces 44 requires disassembly of the casing 1 of the turbomachine.
  • the welding of the end pieces 44 on the exhaust casing 1 is a difficult operation to perform and a source of nonconformities of the exhaust casing 1 which can lead to maintenance operations and re-welding.
  • the present document aims to remedy these drawbacks in a simple, reliable and inexpensive manner.
  • the present document relates to a fluid recovery assembly for a turbomachine turbine, such as a low pressure turbine, extending around an axis and comprising an annular wall comprising a first orifice and a second orifice spaced apart.
  • first tubular end piece having an end portion inserted in the first hole of the annular wall and a second tubular end piece having an end portion inserted in the second hole of the annular wall, a connecting piece between the first end piece and the second end piece, the end portion of the first end piece being screwed into a first hole of the connecting piece and the end portion of the second end piece being screwed into a second orifice of the connecting piece, the connecting piece being arranged on one side of the annular wall and the first and second end pieces comprising end piece portions arranged on the other side opposite wall se annular, means for locking the first end piece and the second end piece in rotation about their respective longitudinal axis.
  • the means for locking in rotation may comprise a wire fixed to the first end piece and to the second end piece.
  • the wire may be attached in tension to the first end piece and to the second end piece so that said tension on the wire exerts a clamping force of each of the first end piece and of the second end piece on said part.
  • the first end piece and the second end piece can be screwed in the same direction of rotation in said part.
  • Said part may be a bar comprising at a first end the first orifice of the connecting part and at a second end opposite to the first end, the second orifice of the connecting part.
  • the bar can, for example, be flat.
  • the first nozzle and the second nozzle can each be connected downstream to a fluid discharge conduit.
  • the exhaust duct can be carried by the annular wall.
  • a spacer can be mounted between each end piece and one face of the annular wall.
  • Each tip may include at the downstream end a head capable of cooperating with a screwing tool.
  • turbomachine exhaust casing comprising a fluid recovery assembly as described above, the casing possibly comprising an internal hub, an external annular ferrule and structural arms connecting said hub to said annular ferrule, said annular shell comprising an upstream annular portion formed by said annular wall.
  • This document also relates to a method of mounting a fluid recovery assembly as mentioned above, said assembly comprising the steps:
  • FIG. 1 is a representation of the upper part of a turbomachine portion (6 o'clock azimuthal angle, at the low point) comprising an exhaust casing according to the prior art
  • FIG. 2 is a perspective representation seen from upstream to downstream of an exhaust housing, see area II of Figure 1, according to the prior art,
  • FIG. 3 is a solution of the prior art with a tip welded to the housing, located in zone III of Figures 1-2;
  • FIG. 4 is an embodiment of a fluid recovery assembly according to this document mounted on an exhaust housing
  • FIG. 5 is a representation seen from downstream of the embodiment shown in Figure 4 according to the invention.
  • FIG. 6 is a representation seen from upstream of the embodiment shown in Figure 4,
  • FIG. 7 is an exploded view of the fixing system according to the invention.
  • FIGs 4, 5, 6, 7 illustrate an embodiment according to the present document of a fluid recuperator assembly 40 for a low pressure turbine 25 of a turbomachine.
  • This fluid collection assembly 40 extends around an axis and includes an annular wall 46 having a first port 48 and a second port 50 angularly spaced from each other (spaced circumferentially about the X axis).
  • the annular wall has a curved shape in section and is connected to the upstream end of an outer ring 3 of a casing 1 of the turbomachine as described above.
  • the upstream end of the annular wall 46 is connected to a radial annular flange 52 for attaching the exhaust casing 1 to the low pressure turbine 25.
  • the ring 54 is hooked by a hook 55 of the casing 1.
  • This abradable ring 54 is arranged radially vis-à-vis the radially outer ends of the last annular row annular row of mobile vanes 56 of the low pressure turbine.
  • the annular wall 46 comprises a first orifice 48 in which is mounted from downstream a first end piece 44a and a second orifice 50 angularly spaced from the first orifice 48 and in which is mounted from downstream a second end piece 44b.
  • the first end piece 44a and the second end piece 44b each comprise an end portion provided with a thread screwed into a corresponding thread of the same part 58 having the shape of a bar (FIG. 7).
  • each end piece 44a, 44b comprises at the downstream end a head 61, 63 able to cooperate with a tool for screwing each end piece into an orifice of the connecting piece.
  • the bar 58 which is flat here but could have another shape, is arranged with respect to the annular wall 46 on the side opposite the first 44a and second end pieces 44b, that is to say upstream of the annular wall. 46.
  • This bar 58 has at each of its ends a first 57 and second 59 orifice.
  • a spacer 60a, 60b is mounted between each end piece 44a, 44b and the downstream face of the annular wall 46.
  • Means for locking the first end piece 44a and the second end piece 44b in rotation about their respective axes are used.
  • This is a wire 62 attached to the first end piece 44a and the second end piece 44b.
  • Wire 62 is tensioned to first end 44a and second end 44b so that said tension on wire 62 exerts a clamping force of each of first end 44a and second end 44b on flat bar 58. More particularly, in the case where the screwing direction of the first end piece 44a is the same as that of the second end piece 44b, the wire 62 will be fixed at a first end to an upper part of the first end piece 44a and at a second end 44b to a part lower end of the second end piece 44b.
  • the wire 62 forms an angle with a non-zero axis passing the axis of the two end pieces 44a, 44b and perpendicular to these two axes.
  • the two ends of the wire 62 will be fixed to the upper part or to the lower part of the end pieces 44a, 44b in a radial direction with respect to the X axis.
  • first end piece 44a is screwed into a first orifice of said flat bar 58 and that the second end piece is screwed in the same direction of rotation into a second orifice of said flat bar 58.
  • the first end piece and the second end piece are each connected downstream to an evacuation duct 42 of fluid carried by the annular wall 46.
  • This evacuation duct 42 comprises downstream a collar 64 to which is screwed a bent plate 66 at the bottom. by means of a screw-nut system 67.
  • This bent plate 66 is itself screwed to the exhaust casing 1 by means of the same screw-nut system 68.
  • the evacuation duct 42 allows oil to circulate from the outlet. casing up to recovery scoops arranged at the outlet of said ducts 42.
  • the scoops have a flared shape making it possible to facilitate the flow of oil from the ducts 42 to the scoops.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Exhaust Silencers (AREA)

Abstract

The present invention relates to a fluid recovery assembly (40) for a turbine (25), such as a low-pressure turbine, of a turbine engine comprising an annular wall (46) comprising a first opening and a second opening spaced apart angularly from one another, a first tubular end piece (44a) inserted into the first opening and a second tubular end piece (44b) inserted into the second opening, the first end piece (44a) and the second end piece (44b) being screwed into a same part (58) arranged relative to the annular wall (46) on the side opposite the first (44a) and second (44b) end pieces, means (62) for preventing the first end piece (44a) and the second end piece (44b) from rotating about their respective axis. This facilitates the removal of the recovery assembly (40).

Description

DESCRIPTION DESCRIPTION
TITRE : Ensemble récupérateur de fluide. TITLE: Fluid recuperator assembly.
Domaine technique de l’invention Technical field of the invention
Le présent document concerne un ensemble récupérateur de fluide, de préférence, pour une turbine basse pression d’une turbomachine. This document relates to a fluid recovery assembly, preferably for a low pressure turbine of a turbomachine.
Etat de la technique antérieure State of the prior art
La Figure 1 représente classiquement une portion de turbomachine à gaz pour aéronef connu, comprenant un carter 1 d'échappement. Le carter d'échappement 1 est mieux visible en Figure 2. Le carter 1 d'échappement est en général disposé en sortie d'une turbine 25, le plus souvent la turbine basse-pression, et avant une tuyère d'éjection (non représentée) où les gaz sortent de la turbomachine, vers l’aval. FIG. 1 conventionally represents a portion of a gas turbomachine for a known aircraft, comprising an exhaust casing 1. The exhaust casing 1 is best seen in Figure 2. The exhaust casing 1 is generally disposed at the outlet of a turbine 25, most often the low-pressure turbine, and before an ejection nozzle (not shown). ) where the gases exit the turbomachine, downstream.
L'amont (AM) et l'aval (AV) sont définis par rapport au sens d'écoulement du flux gazeux dans la turbomachine 10, parallèlement à l’axe X qui est donc l'axe d'écoulement des flux gazeux dans la turbomachine, d'amont en aval, et autour duquel les éléments tournants (de rotor) tournent lorsque la turbomachine fonctionne. Le sens du flux gazeux d'amont vers l’aval dans la turbomachine est représenté par la flèche F de la figure 1. Upstream (AM) and downstream (AV) are defined with respect to the direction of flow of the gas flow in the turbomachine 10, parallel to the X axis which is therefore the flow axis of the gas flow in the turbomachine, from upstream to downstream, and around which the rotating (rotor) elements rotate when the turbomachine is operating. The direction of the gas flow from upstream to downstream in the turbomachine is represented by the arrow F in Figure 1.
Le carter 1 d'échappement est une pièce structurale, qui sert notamment à maintenir la structure de la turbomachine. The exhaust casing 1 is a structural part, which serves in particular to maintain the structure of the turbomachine.
De façon conventionnelle, le carter 1 d'échappement est entouré par une nacelle symbolisée par la référence 4 sur la figure 1 qui permet de caréner la turbomachine pour la protéger de l’environnement extérieur. Conventionally, the exhaust casing 1 is surrounded by a nacelle symbolized by the reference 4 in FIG. 1 which allows the turbomachine to be shrouded in order to protect it from the external environment.
Le carter 1 d'échappement comprend un moyeu 2 présentant la forme d’une couronne qui est agencé à l’intérieur d’une couronne 3 externe ou virole. Entre le moyeu 2 et la couronne 3 externe sont disposés une pluralité de bras 10 structurels. Ces bras 10 structurels, qui peuvent notamment être radiaux ou tangentiels, sont disposés de manière circonférentielle (donc autour de l’axe X) et relient le moyeu 2 à la couronne 3 externe. The exhaust housing 1 comprises a hub 2 having the shape of a crown which is arranged inside an outer crown 3 or ferrule. Between the hub 2 and the outer ring 3 are arranged a plurality of structural arms 10. These structural arms 10, which may in particular be radial or tangential, are arranged circumferentially (therefore around the X axis) and connect the hub 2 to the outer ring 3.
Est radial (axe Z) tout élément s’étendant perpendiculairement à l'axe X et à l’axe Y (voir figure 2). Les bras structurels peuvent être principalement radiaux ou principalement tangentiels (tendant vers l’axe Y). Un bras qui s’étend principalement radialement/tangentiellement par rapport au moyeu 2, s’étend majoritairement dans la direction radiale/tangentielle. Les bras 10 figures 1-2 sont principalement radiaux mais ils pourraient être principalement tangentiels.Any element extending perpendicular to the X axis and the Y axis is radial (Z axis) (see Figure 2). Structural arms can be predominantly radial or predominantly tangential (tending towards the Y axis). An arm which extends predominantly radially / tangentially with respect to hub 2, extends predominantly in the radial / tangential direction. The arms 10 in Figures 1-2 are mainly radial but could be mainly tangential.
Les espaces entre les bras 10 définissent des ouvertures 5 d'échappement, dans lesquelles circule le flux d’air primaire de la turbomachine provenant de chambre de combustion. Afin de fixer la couronne externe 3, celle-ci présente, notamment en extrémité amont, au moins une bride 11. La bride 11 s'étend sur tout ou partie de la circonférence externe de la couronne externe 3. Il s'agit en général d'une collerette radiale s'étendant vers l’extérieur à partir de la circonférence de la couronne externe 3. The spaces between the arms 10 define exhaust openings 5, in which circulates the primary air flow of the turbomachine coming from the combustion chamber. In order to fix the outer ring 3, the latter has, in particular at the upstream end, at least one flange 11. The flange 11 extends over all or part of the outer circumference of the ring. external 3. It is generally a radial flange extending outwardly from the circumference of the external crown 3.
Il est connu que le carter d’échappement peut comporter une rainure qui est formée en aval et à proximité de la bride de fixation amont de ce carter et qui constitue une zone morte, c’est- à-dire à l’abri du flux primaire. Il est fréquent que des fluides, tel que de l’eau, du carburant et/ou de l’huile, soient retenus dans une zone située à 6 heures, c’est-à-dire à un point bas, dans cette rainure. En effet, lors d’un re-démarrage du moteur suite à un démarrage avorté, par exemple, du carburant se retrouve au niveau de la rainure. Pour éviter que de tels fluides puissent stagner dans la turbine basse pression, ces fluides doivent donc pouvoir être drainés hors du moteur sans impacter la nacelle enveloppant le moteur. It is known that the exhaust casing may include a groove which is formed downstream and close to the upstream fixing flange of this casing and which constitutes a dead zone, that is to say sheltered from the flow. primary. It is common for fluids, such as water, fuel and / or oil, to be trapped in an area at 6 o'clock, that is, at a low point, in this groove. In fact, when the engine is restarted following an aborted start, for example, fuel is found in the groove. To prevent such fluids from stagnating in the low pressure turbine, these fluids must therefore be able to be drained from the engine without impacting the nacelle surrounding the engine.
Afin d’assurer le drainage, la turbine basse pression doit avoir un ou plusieurs conduits d’évacuation au point le plus bas possible. Ce conduit d’évacuation évacue les fluides pouvant se trouver dans la rainure de la turbine basse pression vers un bol récupérateur. In order to provide drainage, the low pressure turbine must have one or more exhaust ducts at the lowest possible point. This discharge duct evacuates the fluids that may be in the groove of the low pressure turbine to a collecting bowl.
A l’heure actuelle, la turbine basse pression possède un ensemble récupérateur de fluide 40 comprenant deux conduits d’évacuation 42 qui sont vissés aux embouts 44 comme illustré en Figure 3. Currently, the low pressure turbine has a fluid recovery assembly 40 comprising two discharge conduits 42 which are screwed to the end pieces 44 as shown in Figure 3.
Cependant, après un certain temps d’usage, les embouts 44 qui sont soudés au carter et reliés au conduit d’évacuation 42 peuvent s’endommager, voir se casser. Actuellement, le remplacement desdits embouts 44 nécessite un démontage du carter 1 de la turbomachine. En outre, la soudure des embouts 44 sur le carter 1 d’échappement est une opération difficile à réaliser et source de non conformités du carter 1 d’échappement pouvant conduire à des opérations de maintenances de reprise de soudure. However, after a certain period of use, the end pieces 44 which are welded to the housing and connected to the exhaust duct 42 can be damaged or even broken. Currently, the replacement of said end pieces 44 requires disassembly of the casing 1 of the turbomachine. In addition, the welding of the end pieces 44 on the exhaust casing 1 is a difficult operation to perform and a source of nonconformities of the exhaust casing 1 which can lead to maintenance operations and re-welding.
Le présent document vise à remédier à ces inconvénients, de manière simple, fiable et peu onéreuse. The present document aims to remedy these drawbacks in a simple, reliable and inexpensive manner.
Présentation de l’invention Presentation of the invention
A cet effet, le présent document concerne un ensemble récupérateur de fluide pour turbine de turbomachine, telle qu’une turbine basse pression, s’étendant autour d’un axe et comprenant une paroi annulaire comportant un premier orifice et un second orifice espacés l’un de l’autre selon la direction circonférentielle autour de l’axe, un premier embout tubulaire présentant une portion d’extrémité insérée dans le premier orifice de la paroi annulaire et un second embout tubulaire présentant une portion d’extrémité insérée dans le second orifice de la paroi annulaire, une pièce de liaison entre le premier embout et le second embout, la portion d’extrémité du premier embout étant vissée dans un premier orifice de la pièce de liaison et la portion d’extrémité du second embout étant vissée dans un second orifice de la pièce de liaison, la pièce de liaison étant agencée d’un côté de la paroi annulaire et le premier et second embouts comprenant des portions d’embout agencées de l’autre côté opposé de la paroi annulaire, des moyens de blocage en rotation du premier embout et du second embout autour de leur axe longitudinal respectif. To this end, the present document relates to a fluid recovery assembly for a turbomachine turbine, such as a low pressure turbine, extending around an axis and comprising an annular wall comprising a first orifice and a second orifice spaced apart. one from the other in the circumferential direction around the axis, a first tubular end piece having an end portion inserted in the first hole of the annular wall and a second tubular end piece having an end portion inserted in the second hole of the annular wall, a connecting piece between the first end piece and the second end piece, the end portion of the first end piece being screwed into a first hole of the connecting piece and the end portion of the second end piece being screwed into a second orifice of the connecting piece, the connecting piece being arranged on one side of the annular wall and the first and second end pieces comprising end piece portions arranged on the other side opposite wall se annular, means for locking the first end piece and the second end piece in rotation about their respective longitudinal axis.
Ce système autorise une réparation de l’embout tubulaire sans avoir à démonter le carter d’échappement, cette opération peut ainsi être effectuée sous l’aile d’un avion. En outre, la liaison vissée à la place d’une liaison soudée offre la possibilité de pouvoir être montée ou remplacée par des outils standards et sans utiliser de méthode contraignante telle que la soudure. Par ailleurs, la combinaison d’une pièce de vissage des embouts et de moyens de blocage desdits embouts permet de bloquer en rotation ces derniers en rotation de manière simple et rapide. This system allows repair of the tubular nozzle without having to dismantle the exhaust housing, so this operation can be performed under the wing of an airplane. In addition, the screw connection instead of a welded connection offers the possibility of being able to be mounted or replaced by standard tools and without using a restrictive method such as welding. Furthermore, the combination of a part for screwing the end pieces and means for blocking said end pieces makes it possible to block the latter in rotation in a simple and rapid manner.
Les moyens de blocage en rotation peuvent comprendre un fil fixé au premier embout et au second embout. The means for locking in rotation may comprise a wire fixed to the first end piece and to the second end piece.
Le fil peut être fixé en tension au premier embout et au second embout de manière à ce que ladite tension sur le fil exerce une force de serrage de chacun du premier embout et du second embout sur ladite pièce. Ainsi, le dévissage du premier embout induit un serrage du second embout empêchant dès lors le dévissage plus avant du premier embout. The wire may be attached in tension to the first end piece and to the second end piece so that said tension on the wire exerts a clamping force of each of the first end piece and of the second end piece on said part. Thus, unscrewing the first end piece induces tightening of the second end piece therefore preventing further unscrewing of the first end piece.
Le premier embout et le second embout peuvent être vissés selon un même sens de rotation dans ladite pièce. The first end piece and the second end piece can be screwed in the same direction of rotation in said part.
Ladite pièce peut être une barre comportant à une première extrémité le premier orifice de la pièce de liaison et à une seconde extrémité opposée à la première extrémité, le second orifice de la pièce de liaison. La barre peut, par exemple, être plane. Said part may be a bar comprising at a first end the first orifice of the connecting part and at a second end opposite to the first end, the second orifice of the connecting part. The bar can, for example, be flat.
Le premier embout et le second embout peuvent être chacun reliés en aval à un conduit d’évacuation de fluide. The first nozzle and the second nozzle can each be connected downstream to a fluid discharge conduit.
Le conduit d’évacuation peut être porté par la paroi annulaire. The exhaust duct can be carried by the annular wall.
Une entretoise peut être montée entre chaque embout et une face de la paroi annulaire. Chaque embout peut comporter à l’extrémité aval une tête apte à coopérer avec un outil de vissage. A spacer can be mounted between each end piece and one face of the annular wall. Each tip may include at the downstream end a head capable of cooperating with a screwing tool.
Le présent document concerne également un carter d’échappement de turbomachine comportant un ensemble récupérateur de fluide tel que décrit ci-dessus, le carter pouvant comprendre un moyeu interne, une virole annulaire externe et des bras structurels reliant ladite le moyeu à ladite virole annulaire, ladite virole annulaire comportant une portion annulaire amont formée par ladite paroi annulaire. This document also relates to a turbomachine exhaust casing comprising a fluid recovery assembly as described above, the casing possibly comprising an internal hub, an external annular ferrule and structural arms connecting said hub to said annular ferrule, said annular shell comprising an upstream annular portion formed by said annular wall.
Le présent document concerne encore un procédé de montage d’un ensemble récupérateur de fluide comme précité, ledit ensemble comprenant les étapes : This document also relates to a method of mounting a fluid recovery assembly as mentioned above, said assembly comprising the steps:
- placer et maintenir la pièce de liaison sur une face amont de la paroi annulaire,- place and maintain the connecting piece on an upstream face of the annular wall,
- insérer le premier embout tubulaire et le second embout tubulaire dans un premier orifice et un second orifice de la paroi annulaire et les visser dans la pièce, - bloquer en rotation le premier embout et le second embout autour de leur axe de rotation respectif à l’aide moyens de blocage en rotation. - insert the first tubular end piece and the second tubular end piece into a first hole and a second hole in the annular wall and screw them into the part, - Lock in rotation the first end piece and the second end piece about their respective axis of rotation using means for blocking in rotation.
Brève description des figures Brief description of the figures
[Fig. 1 ] est une représentation de la partie haute d’une portion de turbomachine (angle azimutal de 6 heures, au point bas) comprenant un carter d’échappement selon l’art antérieur,[Fig. 1] is a representation of the upper part of a turbomachine portion (6 o'clock azimuthal angle, at the low point) comprising an exhaust casing according to the prior art,
[Fig. 2] est une représentation en perspective vue de l’amont vers l’aval d’un carter d’échappement, voir zone II de la Figure 1 , selon l’art antérieur, [Fig. 2] is a perspective representation seen from upstream to downstream of an exhaust housing, see area II of Figure 1, according to the prior art,
[Fig. 3] est une solution de l’art antérieur à embout soudé sur le carter, situé en zone III des Figures 1-2 ; [Fig. 3] is a solution of the prior art with a tip welded to the housing, located in zone III of Figures 1-2;
[Fig. 4] est un mode de réalisation d’un ensemble récupérateur de fluide selon le présent document monté sur un carter d’échappement ; [Fig. 4] is an embodiment of a fluid recovery assembly according to this document mounted on an exhaust housing;
[Fig. 5] est une représentation vue depuis l’aval du mode de réalisation représenté en Figure 4 selon l’invention, [Fig. 5] is a representation seen from downstream of the embodiment shown in Figure 4 according to the invention,
[Fig. 6] est une représentation vue depuis l’amont du mode de réalisation représenté en Figure 4, [Fig. 6] is a representation seen from upstream of the embodiment shown in Figure 4,
[Fig. 7] est une vue éclatée du système de fixation selon l’invention. [Fig. 7] is an exploded view of the fixing system according to the invention.
Description détaillée de l’invention Detailed description of the invention
Les figures 4, 5, 6, 7 illustrent un mode de réalisation selon le présent document d’un ensemble récupérateur de fluide 40 pour turbine 25 basse pression d’une turbomachine. Cet ensemble récupérateur de fluide 40 s’étend autour d’un axe et comprend une paroi annulaire 46 comportant un premier orifice 48 et un second orifice 50 espacés angulairement l’un de l’autre (espacés circonférentiellement autour de l’axe X). La paroi annulaire présente en section une forme incurvée et est reliée à l’extrémité amont d’une couronne externe 3 d’un carter 1 de la turbomachine comme décrit précédemment. L’extrémité amont de la paroi annulaire 46 est reliée à une bride 52 annulaire radiale d’accrochage du carter d’échappement 1 à la turbine 25 basse pression. L’anneau 54 est accroché par un crochet 55 du carter 1. Cet anneau 54 abradable est agencé en vis-à-vis radial des extrémités radialement externes de la dernière rangée annulaire rangée annulaire d’aubes mobiles 56 de la turbine basse pression. Figures 4, 5, 6, 7 illustrate an embodiment according to the present document of a fluid recuperator assembly 40 for a low pressure turbine 25 of a turbomachine. This fluid collection assembly 40 extends around an axis and includes an annular wall 46 having a first port 48 and a second port 50 angularly spaced from each other (spaced circumferentially about the X axis). The annular wall has a curved shape in section and is connected to the upstream end of an outer ring 3 of a casing 1 of the turbomachine as described above. The upstream end of the annular wall 46 is connected to a radial annular flange 52 for attaching the exhaust casing 1 to the low pressure turbine 25. The ring 54 is hooked by a hook 55 of the casing 1. This abradable ring 54 is arranged radially vis-à-vis the radially outer ends of the last annular row annular row of mobile vanes 56 of the low pressure turbine.
La paroi annulaire 46 comprend un premier orifice 48 dans lequel est monté depuis l’aval un premier embout 44a et un second orifice 50 angulairement espacé du premier orifice 48 et dans lequel est monté depuis l’aval un second embout 44b. Le premier embout 44a et le second embout 44b comprennent chacun une portion d’extrémité pourvu d’un filetage vissé dans un filetage correspondant d’une même pièce 58 présentant la forme d’une barre (figure 7). Afin de pouvoir visser le premier embout 44a et le second embout 44b, chaque embout 44a, 44b comporte à l’extrémité aval une tête 61 , 63 apte à coopérer avec un outil pour le vissage de chaque embout dans un orifice de la pièce de liaison. The annular wall 46 comprises a first orifice 48 in which is mounted from downstream a first end piece 44a and a second orifice 50 angularly spaced from the first orifice 48 and in which is mounted from downstream a second end piece 44b. The first end piece 44a and the second end piece 44b each comprise an end portion provided with a thread screwed into a corresponding thread of the same part 58 having the shape of a bar (FIG. 7). In order to be able to screw the first end piece 44a and the second end piece 44b, each end piece 44a, 44b comprises at the downstream end a head 61, 63 able to cooperate with a tool for screwing each end piece into an orifice of the connecting piece.
La barre 58, qui est ici plane mais pourrait avoir une autre forme, est agencée par rapport à la paroi annulaire 46 du côté opposé aux premier 44a et second embouts 44b, c’est-à-dire à l’amont de la paroi annulaire 46. Cette barre 58 comporte à chacune de ses extrémités un premier 57 et second 59 orifice. Une entretoise 60a, 60b est montée entre chaque embout 44a, 44b et la face aval de la paroi annulaire 46. The bar 58, which is flat here but could have another shape, is arranged with respect to the annular wall 46 on the side opposite the first 44a and second end pieces 44b, that is to say upstream of the annular wall. 46. This bar 58 has at each of its ends a first 57 and second 59 orifice. A spacer 60a, 60b is mounted between each end piece 44a, 44b and the downstream face of the annular wall 46.
Des moyens de blocage en rotation du premier embout 44a et du second embout 44b autour de leur axe respectif sont employés. Il s’agit d’un fil 62 fixé au premier embout 44a et au second embout 44b. Le fil 62 est fixé en tension au premier embout 44a et au second embout 44b de manière à ce que ladite tension sur le fil 62 exerce une force de serrage de chacun du premier embout 44a et du second embout 44b sur la barre plane 58. Plus particulièrement, dans le cas où le sens de vissage du premier embout 44a est le même que celui du second embout 44b, le fil 62 sera fixé à une première extrémité à une partie supérieure de premier embout 44a et à une seconde extrémité 44b à une partie inférieure du second embout 44b. Ainsi, le fil 62 forme un angle avec un axe non nul passant l’axe des deux embouts 44a, 44b et perpendiculaires à ces deux axes. Dans le cas où les embouts 44a, 44b présentent des sens de vissage opposés, les deux extrémités du fil 62 seront fixées à la partie supérieure ou à la partie inférieure des embouts 44a, 44b selon une direction radiale vis-à-vis de l’axe X. Means for locking the first end piece 44a and the second end piece 44b in rotation about their respective axes are used. This is a wire 62 attached to the first end piece 44a and the second end piece 44b. Wire 62 is tensioned to first end 44a and second end 44b so that said tension on wire 62 exerts a clamping force of each of first end 44a and second end 44b on flat bar 58. More particularly, in the case where the screwing direction of the first end piece 44a is the same as that of the second end piece 44b, the wire 62 will be fixed at a first end to an upper part of the first end piece 44a and at a second end 44b to a part lower end of the second end piece 44b. Thus, the wire 62 forms an angle with a non-zero axis passing the axis of the two end pieces 44a, 44b and perpendicular to these two axes. In the case where the end pieces 44a, 44b have opposite screwing directions, the two ends of the wire 62 will be fixed to the upper part or to the lower part of the end pieces 44a, 44b in a radial direction with respect to the X axis.
Il est à noter que le premier embout 44a est vissé dans un premier orifice de ladite barre 58 plane et que le second embout est vissé selon un même sens de rotation dans un second orifice de ladite barre 58 plane. Le premier embout et le second embout sont chacun reliés en aval à un conduit d’évacuation 42 de fluide porté par la paroi annulaire 46. Ce conduit d’évacuation 42 comprend à l’aval un collier 64 auquel est vissé une plaque coudée 66 au moyen d’un système vis-écrou 67. Cette plaque coudée 66 est elle-même vissée au carter 1 d’échappement grâce à un même système de vis-écrou 68. Le conduit d’évacuation 42 permet une circulation d’huile depuis le carter jusqu’à des écopes de récupération agencées en sortie desdits conduits 42. Les écopes présentent une forme évasée permettant de faciliter l’écoulement d’huile depuis les conduits 42 vers les écopes. It should be noted that the first end piece 44a is screwed into a first orifice of said flat bar 58 and that the second end piece is screwed in the same direction of rotation into a second orifice of said flat bar 58. The first end piece and the second end piece are each connected downstream to an evacuation duct 42 of fluid carried by the annular wall 46. This evacuation duct 42 comprises downstream a collar 64 to which is screwed a bent plate 66 at the bottom. by means of a screw-nut system 67. This bent plate 66 is itself screwed to the exhaust casing 1 by means of the same screw-nut system 68. The evacuation duct 42 allows oil to circulate from the outlet. casing up to recovery scoops arranged at the outlet of said ducts 42. The scoops have a flared shape making it possible to facilitate the flow of oil from the ducts 42 to the scoops.
Ce système permet de pouvoir réparer l’embout 44a, 44b tubulaire sans avoir à démonter le carter 1 d’échappement. En outre, la liaison vissée à la place d’une liaison soudée offre la possibilité de pouvoir être montée ou remplacée par des outils standards et sans utiliser de méthode contraignante telle que la soudure. Par ailleurs, les moyens de blocage en rotation permettent d’éviter le dévissement desdits embouts 44a, 44b. This system makes it possible to repair the tubular nozzle 44a, 44b without having to dismantle the exhaust housing 1. In addition, the screw connection instead of a welded connection offers the possibility of being able to be mounted or replaced by standard tools and without using a restrictive method such as welding. Furthermore, the means for locking in rotation make it possible to avoid the unscrewing of said end pieces 44a, 44b.
En préalable au montage des deux embouts 44a, 44b tubulaires espacés angulairement l’un de l’autre et soudés à ladite paroi annulaire 46, il est nécessaire de procéder aux étapes suivantes : - démonter les éléments d’arrière corps nécessaires pour accéder au carter 1 d’échappement, Prior to mounting the two tubular end pieces 44a, 44b spaced angularly from one another and welded to said annular wall 46, it is necessary to carry out the following steps: - remove the rear body parts necessary to access the exhaust housing 1,
- démonter les conduits d’évacuation 42, les colliers 64 et les plaques coudés 66,- remove the exhaust ducts 42, the clamps 64 and the elbow plates 66,
- découper lesdits embouts 44a, 44b tubulaires soudés au niveau de l’extrémité de jonction desdits embouts 44a, 44b tubulaires soudés avec la paroi annulaire 46,- cut out said tubular end pieces 44a, 44b welded at the junction end of said tubular end pieces 44a, 44b welded to the annular wall 46,
- percer la virole du carter 1 d’échappement pour agrandir les orifices 48, 50 d’insertion desdits embouts 44a, 44b tubulaire, - Drill the ferrule of the exhaust housing 1 to enlarge the holes 48, 50 for inserting said tubular end pieces 44a, 44b,
- insérer le premier embout 44a tubulaire et le second embout 44b tubulaire dans un premier orifice 48 et un second orifice 50 de la paroi annulaire 46 et les visser dans la barre 58 comportant à ses extrémités le premier orifice 57 et le second orifice 59,- insert the first tubular end piece 44a and the second tubular end piece 44b into a first orifice 48 and a second orifice 50 of the annular wall 46 and screw them into the bar 58 having at its ends the first orifice 57 and the second orifice 59,
- bloquer en rotation le premier embout 44a et le second embout 44b autour de leur axe de rotation respectif à l’aide desdits moyens de blocage en rotation 62. - block the first end piece 44a and the second end piece 44b in rotation around their respective axes of rotation using said means for blocking in rotation 62.

Claims

REVENDICATIONS
1. Ensemble récupérateur de fluide (40) pour turbine (25) de turbomachine, telle qu’une turbine basse pression, s’étendant autour d’un axe (X) et comprenant : 1. Fluid recuperator assembly (40) for a turbomachine turbine (25), such as a low pressure turbine, extending around an axis (X) and comprising:
- une paroi annulaire (46) comportant un premier orifice (48) et un second orifice (50) espacés l’un de l’autre selon la direction circonférentielle autour de l’axe (X), - an annular wall (46) comprising a first orifice (48) and a second orifice (50) spaced from each other in the circumferential direction around the axis (X),
- un premier embout (44a) tubulaire présentant une portion d’extrémité insérée dans le premier orifice (48) de la paroi annulaire (46) et un second embout (44b) tubulaire présentant une portion d’extrémité insérée dans le second orifice (50) de la paroi annulaire (46), - a first tubular end piece (44a) having an end portion inserted into the first orifice (48) of the annular wall (46) and a second tubular end piece (44b) having an end portion inserted into the second orifice (50 ) of the annular wall (46),
- une pièce (58) de liaison entre le premier embout (44a) et le second embout (44b), la portion d’extrémité du premier embout (44a) étant vissée dans un premier orifice (57) de la pièce (58) de liaison et la portion d’extrémité du second embout (44b) étant vissée dans un second orifice (59) de la pièce (58) de liaison, la pièce (58) de liaison étant agencée d’un côté de la paroi annulaire (46) et le premier (44a) et second (44b) embouts comprenant des portions d’embout agencées de l’autre côté opposé de la paroi annulaire (46), - a connecting piece (58) between the first end piece (44a) and the second end piece (44b), the end portion of the first end piece (44a) being screwed into a first hole (57) of the part (58) of connection and the end portion of the second end piece (44b) being screwed into a second hole (59) of the connecting part (58), the connecting part (58) being arranged on one side of the annular wall (46 ) and the first (44a) and second (44b) end pieces comprising end piece portions arranged on the other opposite side of the annular wall (46),
- des moyens de blocage en rotation (62) du premier embout (44a) et du second embout (44b) autour de leur axe longitudinal respectif. - Rotational locking means (62) of the first end piece (44a) and of the second end piece (44b) about their respective longitudinal axis.
2. Ensemble (40) selon la revendication 1 , dans lequel les moyens de blocage en rotation (62) comprennent un fil (62) fixé au premier embout (44a) et au second embout (44b). 2. An assembly (40) according to claim 1, wherein the rotation locking means (62) comprise a wire (62) fixed to the first end piece (44a) and to the second end piece (44b).
3. Ensemble (40) selon la revendication 2, dans lequel le fil (62) est fixé en tension au premier embout (44a) et au second embout (44b) de manière à ce que ladite tension sur le fil (62) exerce une force de serrage de chacun du premier embout (44a) et du second embout (44b) sur ladite pièce (58). 3. An assembly (40) according to claim 2, wherein the wire (62) is attached in tension to the first end piece (44a) and to the second end piece (44b) so that said tension on the wire (62) exerts a clamping force of each of the first end piece (44a) and the second end piece (44b) on said part (58).
4. Ensemble (40) selon la revendication 3, dans lequel le premier embout (44a) et le second embout (44b) sont vissés selon un même sens de rotation dans ladite pièce (58) de liaison. 4. The assembly (40) of claim 3, wherein the first end piece (44a) and the second end piece (44b) are screwed in the same direction of rotation into said connecting piece (58).
5. Ensemble (40) selon l’une des revendications 1 à 4, dans lequel ladite pièce (58) est une barre (58) comportant à une première extrémité le premier orifice (57) de la pièce (58) de liaison et à une seconde extrémité opposée à la première extrémité, le second orifice (59) de la pièce (58) de liaison. 5. Assembly (40) according to one of claims 1 to 4, wherein said part (58) is a bar (58) having at a first end the first orifice (57) of the connecting part (58) and at a second end opposite the first end, the second orifice (59) of the connecting piece (58).
6. Ensemble (40) selon l’une des revendications précédentes, dans lequel le premier embout (44a) et le second embout (44b) sont chacun reliés en aval à un conduit d’évacuation (42) respectif de fluide. 6. Assembly (40) according to one of the preceding claims, wherein the first end piece (44a) and the second end piece (44b) are each connected downstream to a respective discharge duct (42) of the fluid.
7. Ensemble (40) selon la revendication 6, dans lequel le conduit d’évacuation (42) est porté par la paroi annulaire (46). 7. The assembly (40) of claim 6, wherein the discharge duct (42) is carried by the annular wall (46).
8. Ensemble (40) selon l’une des revendications précédentes, dans lequel une entretoise (60a, 60b) est montée entre chaque embout (44a, 44b) et une face de la paroi annulaire (46). 8. Assembly (40) according to one of the preceding claims, wherein a spacer (60a, 60b) is mounted between each end piece (44a, 44b) and one face of the annular wall (46).
9. Ensemble (40) selon l’une des revendications précédentes, dans lequel chaque embout (44a, 44b) comporte à une extrémité libre aval une tête (61, 63) apte à coopérer avec un outil de vissage. 9. Assembly (40) according to one of the preceding claims, wherein each tip (44a, 44b) has at a free downstream end a head (61, 63) adapted to cooperate with a screwing tool.
10. Carter d’échappement de turbomachine comportant un ensemble récupérateur de fluide selon l’une des revendications précédentes, comprenant un moyeu (2) interne, une virole annulaire (3) externe et des bras structurels (10) reliant le moyeu (2) à ladite virole annulaire (3), ladite virole annulaire (3) comportant une portion annulaire amont formée par ladite paroi annulaire (46). 10. Turbomachine exhaust casing comprising a fluid recuperator assembly according to one of the preceding claims, comprising an internal hub (2), an external annular shell (3) and structural arms (10) connecting the hub (2). to said annular shell (3), said annular shell (3) comprising an upstream annular portion formed by said annular wall (46).
11. Procédé de montage d’un ensemble récupérateur de fluide selon l’une des revendications 1 à 9, ledit ensemble (40) comprenant les étapes : 11. A method of mounting a fluid recovery assembly according to one of claims 1 to 9, said assembly (40) comprising the steps:
- placer et maintenir la pièce (58) de liaison sur une face amont de la paroi annulaire (46), - insérer le premier embout (44a) tubulaire et le second embout (44b) tubulaire dans un premier orifice (48) et un second orifice (50) de la paroi annulaire (46) et les visser dans la pièce (58) de liaison, - place and maintain the connecting piece (58) on an upstream face of the annular wall (46), - insert the first tubular end piece (44a) and the second tubular end piece (44b) in a first orifice (48) and a second orifice (50) in the annular wall (46) and screw them into the connecting piece (58),
- bloquer en rotation le premier embout (44a) et le second embout (44b) autour de leur axe de rotation respectif à l’aide de moyens de blocage en rotation (62). - block in rotation the first end piece (44a) and the second end piece (44b) around their respective axis of rotation using rotation locking means (62).
PCT/FR2021/050109 2020-01-23 2021-01-21 Fluid recovery assembly WO2021148756A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2000665A FR3106613B1 (en) 2020-01-23 2020-01-23 Fluid recovery assembly.
FRFR2000665 2020-01-23

Publications (1)

Publication Number Publication Date
WO2021148756A1 true WO2021148756A1 (en) 2021-07-29

Family

ID=71784121

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2021/050109 WO2021148756A1 (en) 2020-01-23 2021-01-21 Fluid recovery assembly

Country Status (2)

Country Link
FR (1) FR3106613B1 (en)
WO (1) WO2021148756A1 (en)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070031207A1 (en) * 2005-08-04 2007-02-08 Amir Rosenbaum Lockwire header bolts
CN201843888U (en) * 2010-10-12 2011-05-25 湖南天雁机械有限责任公司 Locking washer for preventing looseness of thermal-insulation screws connecting booster turbine box with bearing body
FR3037614A1 (en) * 2015-06-22 2016-12-23 Snecma DRAIN FOR TURBOMACHINE EXHAUST CASE

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070031207A1 (en) * 2005-08-04 2007-02-08 Amir Rosenbaum Lockwire header bolts
CN201843888U (en) * 2010-10-12 2011-05-25 湖南天雁机械有限责任公司 Locking washer for preventing looseness of thermal-insulation screws connecting booster turbine box with bearing body
FR3037614A1 (en) * 2015-06-22 2016-12-23 Snecma DRAIN FOR TURBOMACHINE EXHAUST CASE

Also Published As

Publication number Publication date
FR3106613B1 (en) 2022-01-28
FR3106613A1 (en) 2021-07-30

Similar Documents

Publication Publication Date Title
EP1862644B1 (en) Air-flow guiding device for a turbomachine, and corresponding turbomachine and diffuser
CA2726016C (en) Assembly including a turbine disc for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disc of such an assembly
EP3234311B1 (en) System for repairing a fastener equipping a reactor wall
CA2740660A1 (en) Oil separator rotor for turbomachine
FR2897144A1 (en) Turbine engine annular combustion chamber with one-piece fairing has fixings associated with tangential slits in flanges to avoid stress crack formation
FR3043138B1 (en) DEGASSING TUBE AND EJECTION CONE FOR A TURBOMACHINE, AND THEIR ASSEMBLY TOOLS
WO2013093337A1 (en) Turbomachine compressor guide vanes assembly
FR2952402A1 (en) Turbo machine e.g. turbojet, of airplane, has air evacuation openings formed in wall of tubular shaft, and stop unit provided on wall and resistant to centrifugal loads under operation and provided at internal radial end of tube
EP0321344B1 (en) Bolt-retaining device for a turbo machine
FR2991386A1 (en) TURBOMACHINE COMPRISING FASTENING MEANS BEFORE A DEHUILING TUBE
FR3099801A1 (en) Set for a turbomachine turbine
EP4168658A1 (en) Recovered-cycle aircraft turbomachine
WO2021148756A1 (en) Fluid recovery assembly
FR3005693A1 (en) DOUBLE-FLOW AIRCRAFT TURBOMACHINE COMPRISING AN INTER-VEIN VIOLINE WITH SIMPLIFIED HOLD
EP3928034B1 (en) Combustion chamber for a turbomachine
EP4090833A1 (en) Assembly for a turbine engine
FR3094398A1 (en) TURBOMACHINE ROTOR SET
FR2979665A1 (en) Clamping device for clamping e.g. nose bullet of propeller of ducted-fan turbine engine of aircraft, has radial deployment unit making groove to extend from retracted position, which allows passage of flange, to deployed tightening position
EP4034752B1 (en) Assembly for a turbine engine
FR3037998B1 (en) AIRCRAFT TURBOMACHINE ASSEMBLY COMPRISING A TURBINE HOUSING AND AN AIR COOLING DEVICE, AND METHOD OF ASSEMBLING SUCH ASSEMBLY
EP3568638B1 (en) Turbine engine combustion chamber
WO2022106779A1 (en) Turbine engine rotor element assembly equipped with a sealing device
FR3131753A1 (en) Improved tie rod turbine rotor and rotor assembly method
FR3115819A1 (en) Aircraft turbomachine stator assembly, comprising an external structure formed of two annular sections surrounding a bladed stator crown
FR3073559A1 (en) ROTOR ASSEMBLY COMPRISING A ROTOR DISC SUPPORTING A CENTRIFIC AIR-LEANING MEMBER

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 21706017

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 21706017

Country of ref document: EP

Kind code of ref document: A1