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 enclosure containing a lubricated bearing in a turbojet type aircraft engine.
• a turbojet engine typically comprises, upstream to downstream in the direction of airflow, 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 are part of a so-called high-pressure rotary body which surrounds a low-pressure shaft rotating at a different speed from it.
• 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 engine.
• Each bearing is lubricated by oil circulating in the enclosure that surrounds it, this enclosure being delimited by fixed structural elements of the engine and by the rotating element which passes through it.
• such a housing encloses at least one bearing being delimited by walls rotating relative to each other with a seal between these walls, which limits the leakage section of the enclosure.
• the oil is removed from the joint at means of a stream of air constantly entering through this seal, from the outside to the inside of the enclosure.
• an upstream seal is provided to constitute a barrier at the junction of the fixed parts delimiting the enclosure upstream with the rotary element, and a downstream seal is provided to form another barrier at the junction of the downstream fixed parts. of the enclosure with the rotating element. Thanks to the continuous stream of air entering each joint, the enclosure allows to circumscribe the oil so that it remains in the vicinity of the bearing without risk that it pollutes the rest of the engine.
• the air is discharged from the enclosure via an oil recovery circuit which is controlled by a volume pump pumping both air and oil.
• the pressure in the chamber is lower than the pressure surrounding the enclosure, to prevent oil can leak, because this oil is likely to ignite in hotter parts of the turbojet, which would lead to its deterioration. It is this pressure difference which ensures that air continuously enters the enclosure through the seals, and is continuously discharged by the pump which thereby controls the flow of air passing through the enclosure.
• the upstream gasket has a significantly larger diameter than the downstream gasket.
• the air arriving at the rotor contact 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 joint is more It is important that the pressure downstream of the downstream joint, the so-called vortex effect being less important around the downstream joint because its diameter is significantly lower.
• the object of the invention is to provide an arrangement for reducing the pressure in the immediate external environment of the simple and precise assembly upstream gasket.
• the subject of the invention is a turbojet bearing housing comprising a fixed envelope traversed by a rotor, this envelope comprising a cylindrical end surrounding a seal ensuring the sealing of the cylindrical end with the rotor, this envelope being equipped with a ferrule screwed on its cylindrical end, this ferrule comprising radial channels opening towards the seal being arranged so that a flow of air passing through the seal towards the enclosure comes mainly from these radial channels .
• the mounting of the ferrule is made mainly by screwing around the end of the envelope, that is to say by adding a limited number of components necessarily positioning precisely relative to the joint .
• the invention also relates to an enclosure thus defined, comprising a locking ring surrounding the ferrule and comprising on the one hand tabs engaging in corresponding notches of the casing and on the other hand tabs falling in corresponding notches the ferrule to block the ferrule in rotation relative to the envelope.
• the invention also relates to an enclosure thus defined, in which the rotor comprises, in the vicinity of the seal, a dropper located opposite an inner face of the shell for centrifuging oil on the rotor in case seal leakage.
• the invention also relates to an enclosure thus defined, wherein the shell comprises a drainage sheet for collecting the centrifuged oil by the dropper.
• the invention also relates to an enclosure thus defined, wherein the seal is maintained axially locked in the cylindrical end of the casing by the ferrule.
• the invention also relates to a method of mounting a ferrule equipping an enclosure thus defined, comprising:
• the invention also relates to a method of mounting a ferrule equipping an enclosure thus defined, comprising: - a step of docking the ferrule carrying the ring by screwing an internal thread of the shell on an external thread of the cylindrical end ;
• the invention also relates to a turbomachine comprising a bearing chamber thus defined.
• the invention also relates to a turbojet comprising a turbomachine thus defined.
• FIG. 1 is a schematic sectional half-view showing the assembled rotor and stator elements of a turbojet engine at a rear high pressure body bearing with its lubrication chamber;
• FIG. 2 is a schematic half-sectional view showing the rotor and stator elements during assembly of a turbojet engine at a rear high pressure body bearing with its lubrication chamber;
• Figure 3 is a half-sectional view of an upstream seal of a lubrication chamber
• Figure 4 is a sectional view showing in detail the shape of the section of the ferrule according to the invention.
• Figure 5 is a half-sectional view of an upstream seal of a lubrication chamber during assembly of a ferrule according to the invention
• Figure 6 is a half-sectional view of an upstream seal of a lubrication chamber equipped with a ferrule according to the invention
• Figure 7 is a perspective view of a locking ring shown alone for the ferrule according to the invention.
• Figure 8 is a perspective view of a ferrule shown alone according to the invention.
• Figure 9 is a partial view showing a ring equipped with its locking ring according to the invention. DETAILED PRESENTATION OF PARTICULAR EMBODIMENTS
• a rear portion 1 of a high-pressure body comprises a rotor spigot 2 which carries a high-pressure turbine disk 3 upstream to downstream, a rotor element 4 inside the upstream gasket, an inner ring 6 of a roller bearing 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 door wipers 8 which are thus sandwiched between an outer shoulder 11 of the pin 2 located immediately downstream turbine disc 3, and the end nut 9 which is at the end of the high pressure body.
• This rear portion 1 of high pressure body is surrounded by a fixed housing 12, which is here a so-called inter-turbine housing, that is to say situated 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 motor.
• This envelope 13 receives a circumferential element 17 of the upstream gasket which surrounds the inner element 4, to constitute together the upstream gasket 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 gasket is a segmented radial gasket
• the downstream gasket is a labyrinth type gasket, comprising circumferential wipers whose radial ends run along the internal face of the abradable ring 19.
• the bearing further comprises, at mid-distance 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 inwardly of the casing 13.
• the casing 13 with its upstream and downstream seals 18 and 22 surrounds the pin 2 to define therewith the enclosure 26 which surrounds the bearing 7 to ensure its lubrication.
• the diameters of the rotor 2, 3 and the casing 13 are increasing, here from the downstream to the upstream.
• the diameters of the rotor and the casing at the upstream seal 18 are greater than the diameters of the rotor and the casing at the level of the bearing 6, which are themselves greater than the diameters of the rotor and envelope at the downstream joint 22.
• This increase in diameters also called staircase dimensioning, allows the engagement of the rotor in the stator, as shown schematically in FIG. 2.
• the rotor is thus engaged in the stator while being moved from upstream to downstream, without interference due to the fact that 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 in view of the vortex effect.
• the upstream seal 18 thus has a diameter much greater than the downstream seal 22, so that it undergoes 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 in FIG. 3, this upstream seal 18 corresponds to that described in 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 rotating sliding contact between the outer face of the rotatable end 29 and the inner face of the fixed segment ring 27 which surrounds this rotatable 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 inner face extended by an internal shoulder delimiting a flat face against which is supported the ring 27.
• a stop ring 33 forming an inner ring 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 ring 34 to which it is connected by axial springs to form an assembly extending along the axis AX between the stop ring 33 and the shoulder. Thanks to the axial springs, the segment 27 is held pressed against the shoulder of the support 31, the additional ring 34 being in abutment against the stop ring 33, as can be seen in FIGS. 3 to 5.
• the upstream cylindrical end 32 of the casing 13 has on its outer face a thread marked by 36 intended to receive a ferrule 37 having a generally crown shape, as can be seen in FIG.
• This shell 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 contour delimiting in particular a radially external cylindrical face 42 which is extended by the ring 39, and a flat front face 43, of normal orientation to the axis AX, whose wall 41 constitutes an extension.
• This body also delimits a flat downstream face 44 parallel to the end face 43, and a radially inner face 46.
• the wall 41 leaves from the edge joining the faces 43 and 46, it has a conicity of the order of thirty degrees, and it extends vis-à-vis the inner face 46 to extend over about half the length of this face 46 along the axis AX.
• the body 38 in the form of a ring is traversed by a series of radial channels, identified by 47 contiguous with each other, and each putting in communication the external face 42 with the internal face 46.
• this ferrule 37 is held tight on the end 32 by a sheet metal locking ring 48 which appears alone in FIG. 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 tabs 52 downstream protruding from its downstream edge, and six upstream tabs 53 protruding from its upstream edge, all these tabs being regularly spaced around the axis of revolution AX.
• the ring comprises at least two downstream tabs and at least two upstream tabs.
• the envelope 13 has a circumferential edge 54 located opposite the ring 39 when the ferrule is mounted, that is to say recessed relative to the end 32, and which has eight notches not visible in the figures and each intended to receive one of the downstream legs 52.
• the ferrule 37 comprises at least two notches, here six notches marked 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 end face 43 and the outer radial face 42 of the ferrule, each notch being located between two radial channels 47, and also allowing the clamping of the ferrule with a suitable clamping tool.
• the locking ring 48 has an internal diameter corresponding to the diameter of the outer radial face 42 of the shell, so as to surround it when the assembly is in place as in FIG.
• the mounting of the assembly may consist in installing the ring 48 in position at the cylindrical end 32 of the casing 13, the legs 53 then being flat.
• the ferrule 37 is then approached 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, 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 overall size 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 shell 37, to screw the shell on the end 32.
• the shell is plated, 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 legs 53.
• the upstream legs 53 can then be folded to ensure complete blocking.
• This assembly requires the manipulation 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 rotatable end 29 in order to allow the mounting of this ferrule 37.
• the rotatable end 29 has a terminal edge 57 extending radially in a point, and whose outer diameter is slightly smaller 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 AX axis.
• the annular space between the end edge 57 and the free edge 58 which constitutes an air passage to 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 for the air passage to the seal 18 to occur mainly via these radial channels, that is to say without undergoing a vortex effect and thereby even without increasing pressure.
• the end edge 57 of the rotor terminates in a point oriented radially outwards to form a dropper to prevent oil dispersion in the air flow, in case of oil leakage since the enclosure 26 through the upstream gasket 18. More specifically, in the event of total or partial failure of the seal 18, a drop of oil along the outer face of the rotor towards the end 29 of this rotor meets the drop lance 57 which constitutes a radial protuberance in its path. Given the high rotational speed of the rotor, this drop is then centrifuged by the lance drops 57, so that it leaves the rotor to join the inner face 46 of the ferrule 37 and the conical wall 41 which constitutes a drainage sheet who are motionless with the stator.
• the drop of oil can flow along the inner face 46 to reach the bottom of the shell and then a lower part of the engine which allows to evacuate.
• a drop of oil centrifuged in the upper part of the inner face 46 it can optionally be detached from this inner face to the rotor to be centrifuged again, so that it ultimately reaches the lower part of the shell and the engine to be evacuated.
• the drop lance 57 thus makes it possible to confine oil generated by leakage of the seal 18 in the region of the ferrule 37 in order finally to evacuate it, so as to avoid and at least limit a dispersion of this oil in the flow. air passing through the engine.
• an additional casing carried by the rotor may be provided to cover frontally ferrule 37 and the seal, extending to surround them, so as to further limit the risk of oil dispersion to the air flow.

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• 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)

Applications Claiming Priority (2)

Publications (2)

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Country Status (5)

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Family Cites Families (28)

• 2017
  • 2017-02-07 FR FR1700127A patent/FR3062679B1/fr active Active
• 2018
  • 2018-02-05 EP EP18706790.5A patent/EP3580431B1/de active Active
  • 2018-02-05 CN CN201880010305.7A patent/CN110268140B/zh active Active
  • 2018-02-05 WO PCT/FR2018/050274 patent/WO2018146404A1/fr unknown
  • 2018-02-05 US US16/483,464 patent/US11261754B2/en active Active

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