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EP3580431B1 - Ring zur verminderung des überdrucks in der nähe der stromaufwärtigen dichtung eines lagergehäuses eines turbinen-strahltriebwerks - Google Patents

Ring zur verminderung des überdrucks in der nähe der stromaufwärtigen dichtung eines lagergehäuses eines turbinen-strahltriebwerks Download PDF

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Publication number
EP3580431B1
EP3580431B1 EP18706790.5A EP18706790A EP3580431B1 EP 3580431 B1 EP3580431 B1 EP 3580431B1 EP 18706790 A EP18706790 A EP 18706790A EP 3580431 B1 EP3580431 B1 EP 3580431B1
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EP
European Patent Office
Prior art keywords
shell
seal
envelope
upstream
cylindrical end
Prior art date
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EP18706790.5A
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English (en)
French (fr)
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EP3580431A1 (de
Inventor
Frédéric François Jean-Yves PATARD
Antoine Jean-Philippe Beaujard
Philippe Pierre Vincent Bouiller
Christophe CAPLAIN
Maxime Aurélien Rotenberg
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP3580431A1 publication Critical patent/EP3580431A1/de
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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
    • F01D25/183—Sealing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods

Definitions

  • the invention relates to the balancing of the pressure in the vicinity of an internal chamber enclosing a lubricated bearing in an aircraft engine of the turbojet type.
  • a turbojet typically comprises, from upstream to downstream in the direction of the air flow, a low pressure compressor, a high pressure compressor, a combustion chamber, followed by a high pressure turbine and a low turbine. pressure.
  • the high pressure compressor and the high pressure turbine form part of a so-called high pressure rotating body which surrounds a low pressure shaft while rotating at a speed different from the latter.
  • the low pressure shaft carries the low pressure compressor and the low pressure turbine.
  • the low pressure shaft and the high pressure body are carried upstream and downstream by bearings housed in enclosures isolating them from the rest of the engine.
  • Each enclosure contains a bearing in the form of one or more roller bearings interposed between a rotating element such as the shaft or the high pressure body, and a fixed element of the motor.
  • Each bearing is lubricated by oil circulating in the enclosure which surrounds it, this enclosure being delimited by fixed structural elements of the engine and by the rotating element which passes through it.
  • such an enclosure contains at least one bearing while being delimited by walls rotating with respect to one another with a seal between these walls, which limits the leakage section of the enclosure.
  • the oil is moved away from the seal by means of a stream of air entering continuously through this seal, from the outside to the inside of the enclosure.
  • an upstream seal is provided to form a barrier at the junction of the fixed parts delimiting the upstream enclosure with the rotating element
  • a downstream seal is provided to form another barrier at the junction of the downstream fixed parts of the enclosure with the rotating element.
  • the air is evacuated out of the enclosure via an oil recovery circuit which is controlled by a volumetric pump pumping both air and oil.
  • the pressure prevailing in the enclosure is lower than the pressure surrounding the enclosure, to prevent oil from leaking, because this oil is liable to ignite in hotter parts of the turbojet engine, which would lead to its deterioration. It is this pressure difference which ensures that air continuously enters the enclosure through the seals, and it is continuously evacuated by the pump which thus controls the flow of air passing through the enclosure.
  • the upstream seal has a significantly larger diameter than the downstream seal.
  • the air arriving in contact with the rotor in the vicinity of a seal is rotated by this rotor, it undergoes a so-called vortex effect which tends to establish a radial pressure gradient. It follows that the pressure upstream of the upstream seal is more greater than the pressure downstream of the downstream seal, the so-called vortex effect being less important around the downstream seal because its diameter is significantly smaller.
  • the object of the invention is to provide an arrangement making it possible to reduce the pressure in the immediate external environment of the upstream seal which is simple and precise to assemble.
  • the invention relates to a turbojet bearing enclosure according to claim 1, comprising in particular a fixed casing through which a rotor passes, this casing comprising a cylindrical end surrounding a seal ensuring the tightness of the cylindrical end with the rotor, this casing being equipped with a ferrule screwed onto its cylindrical end, this ferrule comprising radial channels opening out opposite the seal while being arranged so that a flow of air passing through the seal towards the enclosure originates mainly from these radial channels.
  • the mounting of the ferrule is carried out mainly by screwing around the end of the casing, that is to say by adding a limited number of components necessarily positioning themselves precisely with respect to the seal. .
  • the invention also relates to an enclosure thus defined, comprising a locking ring surrounding the ferrule and comprising on the one hand lugs engaging in corresponding notches in the casing and on the other hand
  • the invention also relates to an enclosure thus defined, in which the rotor comprises, in the vicinity of the seal, a drip lance located opposite an internal face of the ferrule for centrifuging the oil present on the rotor in the event of seal leakage.
  • the invention also relates to an enclosure thus defined, in which the ferrule comprises a drainage plate for collecting the oil centrifuged by the drip lance.
  • the invention also relates to an enclosure thus defined, in which the seal is kept locked axially in the cylindrical end of the casing by the ferrule.
  • the invention also relates to a turbomachine comprising a bearing enclosure thus defined.
  • the invention also relates to a turbojet comprising a turbomachine thus defined.
  • a rear portion 1 of a high pressure body comprises a rotor journal 2 which carries from upstream to downstream a high pressure turbine disc 3, a rotor element 4 inside the upstream seal, an inner ring 6 of a bearing with rollers 7, a wiper holder 8 and a terminal nut 9.
  • the terminal nut 9 maintains in position along the axis of rotation AX of this high pressure body, the rotor 4, the ring 6 and the wiper holder 8 which are thus clamped between an external shoulder 11 of the journal 2 located immediately downstream of the turbine disk 3, and this terminal nut 9 which is at the end of the high pressure body.
  • This rear portion 1 of the high pressure body is surrounded by a fixed casing 12, which is here a so-called inter-turbine casing, that is to say located along the axis AX between the high pressure turbine 3 and a turbine. low pressure not shown in the figure.
  • This casing 12 comprises a casing 13 which generally surrounds the inner element 4 of the upstream seal, the bearing 7 and the wiper holder 8, this casing 13 being connected by a radial structure 14 to a fixed structural element 16 of the engine.
  • This casing 13 receives a circumferential element 17 of the upstream seal which surrounds the inner element 4, to jointly constitute the upstream seal 18. It carries at its downstream end a ring 19 of abradable material which surrounds the wipers 21 of the wiper holder 8 to form therewith the downstream seal 22.
  • the upstream seal is a segmented radial seal
  • the downstream seal is a labyrinth-type seal, comprising circumferential wipers whose radial ends run along the internal face of the abradable ring 19.
  • segmented radial seal and the labyrinth seal can be reversed; a segmented radial seal or labyrinth seal mountable at each seal; at least one of the seals possibly being a floating ring seal.
  • the bearing also comprises, halfway between the ends of the casing, an internal structure 23 carrying an outer ring 24 of the roller bearing 7, this structure 23 extending radially towards the inside of the casing 13.
  • the casing 13 with its upstream and downstream seals 18 and 22 surrounds the journal 2 in order to define with the latter the enclosure 26 which surrounds the bearing 7 to ensure its lubrication.
  • the diameters of the rotor 2, 3 and of the casing 13 are increasing, here from downstream to upstream.
  • the diameters of the rotor and of the casing at the level of the upstream seal 18 are greater than the diameters of the rotor and of the casing at the level of the bearing 6, which are themselves greater than the diameters of the rotor and casing at the downstream seal 22.
  • This increase in diameters also called stepped dimensioning, allows the engagement of the rotor in the stator, as shown schematically in the figure. figure 2 .
  • the rotor is thus engaged in the stator by being moved from upstream to downstream, without interference thanks to the fact that the diameters are decreasing from upstream to downstream.
  • the upstream and downstream seals necessarily have significantly different diameters, so that the pressure around these seals is necessarily different taking into account the vortex effect.
  • the upstream seal 18 thus has a diameter much greater than the downstream seal 22, so that it is subjected to an external pressure greater than the external pressure of the downstream seal.
  • the upstream seal is here a segmented radial seal whose structure appears more clearly on the figure 3 , this upstream seal 18 corresponds to that described in the patent document EP1055848 . It comprises a ring of segments 27 held together by a circumferential spring 28 and surrounding an upstream end 29 of the inner element 4 of the rotor. The seal is formed at the rotary sliding contact being established between the external face of the rotating end 29, and the internal face of the ring of fixed segments 27 which surrounds this rotating end 29.
  • the ring 27 is held in a fixed support 31 which is nested and held in an upstream cylindrical end 32 of the casing 13.
  • This support 31 has a cylindrical internal face extended by an internal shoulder defining a flat face against which it bears. the ring 27.
  • a stop ring 33 forming an internal hoop is engaged and locked in an internal groove of the cylindrical face of the support 31, at a distance from its shoulder face.
  • the ring 27 carries an additional crown 34 to which it is linked by axial springs, to constitute an assembly extending along the axis AX between the stop ring 33 and the shoulder. Thanks to the axial springs, the segment 27 is kept pressed against the shoulder of the support 31, the additional ring 34 resting against the stop ring 33, as visible on the figures. figures 3 to 5 .
  • the upstream cylindrical end 32 of the casing 13 comprises on its outer face a thread marked 36, intended to receive a ferrule 37 having the general shape of a crown, as visible on the figure 6 .
  • This ferrule comprises 37, seen in section along a plane passing through its axis of revolution AX, comprises a body 38 extended along the axis AX by a threaded cylindrical ring 39, and extended internally by a conical wall 41.
  • the body 38 has a rectangular outline delimiting in particular a radially outer cylindrical face 42 which is extended by the ring 39, and a flat front face 43, of normal orientation to the axis AX, of which the wall 41 constitutes an extension.
  • This body also defines a planar downstream face 44 parallel to the front face 43, and a radially internal face 46.
  • the wall 41 starts from the edge joining the faces 43 and 46, it has a taper of the order of thirty degrees, and it extends opposite the internal face 46 to extend over approximately half. the length of this face 46 along the axis AX.
  • the crown-shaped body 38 is crossed by a series of radial channels, identified by 47 contiguous to each other, and each placing the external face 42 in communication with the internal face 46.
  • This ferrule 37 When mounted, this ferrule 37 is held tight on the end 32 by a sheet metal locking ring 48 which appears alone on the figure 7 .
  • This locking ring 48 has the general shape of a ring comprising an upstream edge 49 and a downstream edge 51, here with eight downstream tabs 52 projecting from its downstream edge, and six upstream tabs 53 projecting from its upstream edge, all of these tabs. being regularly spaced around the axis of revolution AX.
  • the ring comprises at least two downstream lugs and at least two upstream lugs.
  • the casing 13 has a circumferential edge 54 located opposite the ring 39 when the ferrule is mounted, that is to say set back from the end 32, and which has eight notches. not visible in the figures and each intended to receive one of the downstream tabs 52.
  • the ferrule 37 comprises at least two notches, here six notches identified by 56 which are each intended to receive one of the upstream tabs 53, the number of notches being identical to the number of tabs.
  • Each notch 56 is formed at the edge joining the front face 43 and the outer radial face 42 of this ferrule, each notch being located between two radial channels 47, and also allowing the tightening of the ferrule with a suitable tightening tool.
  • the locking ring 48 has an internal diameter corresponding to the diameter of the external radial face 42 of the ferrule, so as to surround it when the assembly is in place as in the figure 6 .
  • the assembly of the assembly may consist in installing the ring 48 in position at the level of the cylindrical end 32 of the casing 13, the tabs 53 then being flat.
  • the ferrule 37 is then docked between this ring 48 and the casing 13 by screwing the internal thread 40 of this ferrule around the external thread 36 of the end 32.
  • the tabs 53 can then be folded towards the axis AX to be folded into the notches 56, so as to completely block the ferrule 37 in rotation relative to the end 32 on which it is clamped, which corresponds to the situation of figures 6 and 9 .
  • This assembly requires mounting the ferrule 37 between the end 32 and the ring 48 with a small footprint and alignment tolerances, but the ring and the ferrule are mounted relative to the housing.
  • Another possibility is to mount the ring 48 around the ferrule 37, to screw the ferrule onto the end 32.
  • the ferrule is pressed, having its face 44 resting on an upstream end of the support 31, it is tightened until 'to put its front notches 56 vis-à-vis the upstream tabs 53.
  • the upstream tabs 53 can then be folded down to ensure complete locking.
  • This assembly requires the handling of a sub-assembly formed by the ferrule and the non-integral ring, but is simpler in docking.
  • the ferrule 37 covers the upstream edge of the end 32 extending radially towards the axis AX to radially cover the majority of the seal 18.
  • the internal diameter of this ferrule 37, corresponding to the internal diameter of the wall 41 is very slightly greater than the external diameter of the rotating end 29 in order to allow the mounting of this ferrule 37.
  • the rotary end 29 has a terminal edge 57 extending radially at a point, and the outer diameter of which is slightly less than the diameter of the free edge 58 of the wall 41, while being located at a short distance from this edge. free 58 along the axis AX.
  • the annular space located between the terminal edge 57 and the free edge 58 which constitutes an air passage towards the seal 18 is thus provided very small radially and axially, so as to limit the flow rate through this passage.
  • the radial channels 47 have large passage sections so that the passage of air towards the seal 18 occurs mainly via these radial channels, that is to say without undergoing a vortex effect and thereby even without increased pressure.
  • terminal edge 57 of the rotor ends in a point oriented radially outwards to constitute a drip lance making it possible to avoid dispersion of oil in the air flow, in the event of an oil leak from the air flow. enclosure 26 through the upstream seal 18.
  • the drop of oil can trickle down along the internal face 46 to reach the bottom of the ferrule and then a lower part of the engine, which allows it to be evacuated.
  • a drop of oil centrifuged in the upper part of the internal face 46 it can, if necessary, detach itself from this internal face towards the rotor in order to be centrifuged again, so that it ultimately reaches the lower part of the shell and of the engine to be evacuated there.
  • the drop lance 57 thus makes it possible to confine the oil generated by a leakage from the seal 18 in the region of the shell 37 to finally evacuate it, so as to avoid and at the very least limit a dispersion of this oil in the flow of water. air passing through the engine.
  • an additional casing carried by the rotor may be provided to frontally cover the ferrule 37 and the seal, extending to surround them, so as to further limit the risks of oil dispersion towards the air flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Claims (9)

  1. Gehäuse (26) eines Lagers eines Turbostrahltriebwerks, umfassend einen festen Mantel (13), der von einem Rotor (2, 4) durchgriffen ist, wobei dieser Mantel 13) ein zylindrisches Ende (32) mit einem Außengewinde aufweist und eine Dichtung (18) umgibt, welche die Dichtigkeit dieses zylindrischen Endes (32) mit dem Rotor (2, 4) sicherstellt, wobei dieser Mantel (13) mit einem Ring (37) ausgestattet ist, welcher ein Innengewinde aufweist, das auf das Außengewinde des zylindrischen Endes (32) geschraubt ist, wobei dieser Ring (37) radiale Kanäle (47) aufweist, die gegenüber der Dichtung (18) ausmünden und dabei so angeordnet sind, dass ein Luftstrom, der die Dichtung (18) in Richtung des Gehäuses durchströmt, hauptsächlich aus diesen radialen Kanälen (47) stammt.
  2. Gehäuse nach Anspruch 1, umfassend einen Blockierring (48), der den Ring (37) umgibt und einerseits Laschen (52), die in entsprechende Nuten des Mantels (13) eingreifen, sowie andererseits Laschen (53) aufweist, die in entsprechende Nuten (56) des Rings (37) umgeschlagen sind, um diesen Ring gegen ein Drehen gegenüber dem Mantel (13) festzulegen.
  3. Gehäuse nach Anspruch 1 oder 2, wobei der Rotor (2, 4) in der Nähe der Dichtung (18) einen Tropfenauswerfer (57) umfasst, der gegenüber einer Innenseite des Rings (37) gelegen ist, um im Falle einer Leckage der Dichtung (18) auf dem Rotor vorhandenes Öl wegzuschleudern.
  4. Gehäuse nach Anspruch 3, wobei der Ring (37) eine Drainageblech (41) umfasst, um das durch den Tropfenauswerfer (57) weggeschleuderte Öl zu sammeln.
  5. Gehäuse nach Anspruch 1 oder 2, wobei die Dichtung (18) durch den Ring (37) in dem zylindrischen Ende (32) des Mantels (13) axial blockiert gehalten wird.
  6. Verfahren zum Montieren eines Rings (37), mit dem ein Gehäuse nach Anspruch 2 ausgestattet ist, umfassend:
    - einen Schritt des Positionierens des Rings (48) im Bereich des zylindrischen Endes (32) des Mantels (13);
    - einen Schritt des Ankoppelns des Rings (37) zwischen diesem Ring (48) und dem zylindrischen Ende (32) des Mantels (13) durch Aufschrauben eines Innengewindes (40) des Rings (37) auf ein Außengewinde (36) des zylindrischen Endes (32);
    - einen Schritt des Festziehens des Rings (37) bis stirnseitige Nuten (56) dieses Rings (37) mit stromaufwärtigen Laschen (53) des Rings in Übereinstimmung gebracht sind;
    - einen Schritt des Umschlagens der stromaufwärtigen Laschen (53) in die stirnseitigen Nuten (56).
  7. Verfahren zum Montieren eines Rings (37), mit dem ein Gehäuse nach Anspruch 2 ausgestattet ist, umfassend:
    - einen Schritt des Ankoppelns des den Ring (48) tragenden Rings (37) durch Aufschrauben eines Innengewindes (40) des Rings (37) auf ein Außengewinde (36) des zylindrischen Endes (32);
    - einen Schritt des Festziehens des Rings (37) bis stirnseitige Nuten (56) dieses Rings (37) mit stromaufwärtigen Laschen (53) des Rings in Übereinstimmung gebracht sind;
    - einen Schritt des Umschlagens der stromaufwärtigen Laschen (53) in die stirnseitigen Nuten (56).
  8. Turbomaschine, die ein Lagergehäuse nach einem der Ansprüche 1 bis 5 umfasst.
  9. Turbostrahltriebwerk, das eine Turbomaschine nach Anspruch 8 umfasst.
EP18706790.5A 2017-02-07 2018-02-05 Ring zur verminderung des überdrucks in der nähe der stromaufwärtigen dichtung eines lagergehäuses eines turbinen-strahltriebwerks Active EP3580431B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1700127A FR3062679B1 (fr) 2017-02-07 2017-02-07 Virole de reduction de la surpression au voisinage du joint amont d'une enceinte de palier de turboreacteur
PCT/FR2018/050274 WO2018146404A1 (fr) 2017-02-07 2018-02-05 Virole de réduction de la surpression au voisinage du joint amont d'une enceinte de palier de turboreacteur

Publications (2)

Publication Number Publication Date
EP3580431A1 EP3580431A1 (de) 2019-12-18
EP3580431B1 true EP3580431B1 (de) 2020-12-16

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP18706790.5A Active EP3580431B1 (de) 2017-02-07 2018-02-05 Ring zur verminderung des überdrucks in der nähe der stromaufwärtigen dichtung eines lagergehäuses eines turbinen-strahltriebwerks

Country Status (5)

Country Link
US (1) US11261754B2 (de)
EP (1) EP3580431B1 (de)
CN (1) CN110268140B (de)
FR (1) FR3062679B1 (de)
WO (1) WO2018146404A1 (de)

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US11686218B2 (en) * 2020-08-21 2023-06-27 Pratt & Whitney Canada Corp. Pressure seal assembly

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Also Published As

Publication number Publication date
CN110268140B (zh) 2022-03-04
WO2018146404A1 (fr) 2018-08-16
FR3062679A1 (fr) 2018-08-10
EP3580431A1 (de) 2019-12-18
FR3062679B1 (fr) 2019-04-19
US20200032672A1 (en) 2020-01-30
CN110268140A (zh) 2019-09-20
US11261754B2 (en) 2022-03-01

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