Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B61—RAILWAYS
  • B61F—RAIL VEHICLE SUSPENSIONS, e.g. UNDERFRAMES, BOGIES OR ARRANGEMENTS OF WHEEL AXLES; RAIL VEHICLES FOR USE ON TRACKS OF DIFFERENT WIDTH; PREVENTING DERAILING OF RAIL VEHICLES; WHEEL GUARDS, OBSTRUCTION REMOVERS OR THE LIKE FOR RAIL VEHICLES
  • B61F15/00—Axle-boxes
  • B61F15/20—Details
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
  • G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
  • G01P3/42—Devices characterised by the use of electric or magnetic means
  • G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
  • G01P3/443—Devices characterised by the use of electric or magnetic means for measuring angular speed mounted in bearings
• • 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
  • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
  • F16C41/00—Other accessories, e.g. devices integrated in the bearing not relating to the bearing function as such
  • F16C41/007—Encoders, e.g. parts with a plurality of alternating magnetic poles
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
  • G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
  • G01P3/42—Devices characterised by the use of electric or magnetic means
  • G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
  • G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
  • G01P3/42—Devices characterised by the use of electric or magnetic means
  • G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
  • G01P3/48—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
  • G01P3/481—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals
  • G01P3/487—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by rotating magnets
• • 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
  • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
  • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
  • F16C19/22—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings
  • F16C19/34—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load
  • F16C19/38—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load with two or more rows of rollers
  • F16C19/383—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load with two or more rows of rollers with tapered rollers, i.e. rollers having essentially the shape of a truncated cone
  • F16C19/385—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load with two or more rows of rollers with tapered rollers, i.e. rollers having essentially the shape of a truncated cone with two rows, i.e. double-row tapered roller bearings
  • F16C19/386—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load with two or more rows of rollers with tapered rollers, i.e. rollers having essentially the shape of a truncated cone with two rows, i.e. double-row tapered roller bearings in O-arrangement
• • 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
  • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
  • F16C2226/00—Joining parts; Fastening; Assembling or mounting parts
  • F16C2226/50—Positive connections
  • F16C2226/60—Positive connections with threaded parts, e.g. bolt and nut connections
• • 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
  • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
  • F16C2326/00—Articles relating to transporting
  • F16C2326/10—Railway vehicles
• • 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
  • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
  • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
  • F16C33/72—Sealings
  • F16C33/723—Shaft end sealing means, e.g. cup-shaped caps or covers
• • 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
  • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
  • F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
  • F16C35/04—Rigid support of bearing units; Housings, e.g. caps, covers in the case of ball or roller bearings
  • F16C35/06—Mounting or dismounting of ball or roller bearings; Fixing them onto shaft or in housing
  • F16C35/063—Fixing them on the shaft

Definitions

• the invention relates to the field of shafts or axles with instrumented bearings. These bearings are large and support high loads.
• the instrumentation of such bearings consists in mounting speed and / or temperature and / or vibration sensors generally on the fixed part of the bearing; the mobile part of the instrumentation is mounted on the other ring of the bearing. More specifically, the present invention is an instrumented bearing assembly for axle and rocket cap and a lock washer for such an assembly.
• this assembly requires a deflector in several parts, which is complex and expensive. Parts of the deflector have areas of mechanical weakness, which is problematic because in the applications envisaged, significant mechanical loads are exerted on the bearings and associated parts.
• This assembly is very specific and it is not possible to mount it on other types of bearings than the one for which it is initially planned. In particular it is not possible to mount it on standard casing bearings.
• an instrumented assembly for an axle stub comprising:
• a rocket cap having a bottom provided with at least one through hole and a skirt defining a reference geometric axis, the skirt having a distal end opposite the bottom and constituting an axial bearing face, the rocket cap having a larger outer diameter D1, and
• a magnetic coding ring fixed either to a fixed support relative to the rocket cap having a diameter D3, in axial overlap with the skirt or the bottom of the rocket cap, or to the rocket cap, and has an outside diameter D2 less than D1 and / or D3.
• the rocket cap and / or the support protect the encoder ring against mechanical shocks, and this throughout its life: from storage before assembly, during assembly, during its use, then its eventual disassembly, renovation and subsequent reassembly.
• the solution without support offers the advantage of simplicity, the number of parts being reduced.
• the alternative with support however allows in some cases a better protection against shocks.
• the proposed solution fits all types of bearings; it allows to repair or renovate many existing assemblies by replacing parts, and this in a simple way.
• the encoder ring is overmoulded or mounted in force on the fixed support or the rocket cap, to ensure a good quality of fixation.
• the overmolding solution offers the advantage of avoiding encoder deformations, resulting in better signal quality.
• the encoder may be made of elasto-ferrite or plasto-ferrite, or a material doped with rare earths.
• the magnetic encoder ring is fixed radially outside the skirt of the rocket cap and covers at least partially the skirt of the rocket hat. Therefore, the skirt of the rocket cap is not likely to constitute a magnetic screen between the magnetic encoder ring and a sensor located opposite the encoder, radially outside the rocket cap.
• the encoder is either in abutment against the skirt of the rocket cap, or at a radial distance from the skirt of the rocket cap less than 0.5 mm and preferably less than 0. , 2 mm, so as to take advantage of a mirror effect caused by the rocket cap, which promotes the reading of the magnetic encoder by a sensor placed at a distance from air gap.
• the assembly further comprises a protection cap of the encoder ring, comprising a protective skirt covering the encoder ring.
• the skirt of the cover is made of non-magnetic material, so as not to constitute a screen between the encoder ring and a sensor located opposite the ring, radially outside the ring and the cover.
• the hood may have a bottom pinched between the rocket cap and the inner ring of the bearing.
• the hood skirt may have an end folded over the flare cap to lock the hood to the flare cap.
• the hood offers the advantage of protecting the encoder ring not only against shocks, but also against various pollutions.
• the cover can be shaped so as to define with the rocket cap and / or the support a closed annular housing volume of the encoder ring.
• the encoder ring may be attached to a face of the support rotated radially inward and facing the rocket cap.
• the encoder can be attached directly to the rocket cap; it can advantageously be fitted on the rocket cap.
• the encoder ring may in particular be fixed in an annular groove of the skirt of the rocket cap, the groove being open radially outwards. This configuration provides additional protection against shocks.
• the annular groove may have a dovetail section, the encoder ring having a complementary shape for optimum mechanical strength.
• the skirt of the rocket cap may comprise at least one indexing relief, cooperating with a corresponding relief of the encoder ring to lock in rotation the ring relative to the rocket cap.
• the encoder ring can be fixed on a wall of the skirt of the rocket cap turned radially inwardly.
• the encoder ring can also be fixed on the support facing an inner wall of the skirt of the rocket cap.
• the rocket cap is made of non-magnetic material.
• the support can be pinched axially between the rocket cap and the inner ring of the bearing.
• this relates to an instrumented assembly comprising:
• a rocket cap extending axially outside the inner ring, the rocket cap having a bottom provided with at least one through hole and a skirt provided with a distal end in direct or indirect axial bearing on the inner ring, the rocket cap having a larger outside diameter D1, and
• a magnetic coding ring fixed to the rocket cap or to a fixed support with respect to the rocket cap, axially outside the inner ring, in axial overlap with the rocket cap skirt, and has a smaller outer diameter D2 at D1.
• an instrumented assembly for an axle stub comprising: - A rocket cap having a bottom provided with at least one opening hole and a skirt defining a reference geometric axis, the skirt having a distal end opposite the bottom and constituting an axial bearing face,
• the instrumented assembly thus formed can then be mounted on an axle stub axle.
• the encoder ring may be located axially between the bottom and the distal end of the rocket cap.
• the encoder ring can then be in direct or indirect radial support on a cylindrical bearing surface of the rocket cap.
• the encoder ring may be in direct or indirect axial bearing against an axial annular shoulder of the rocket cap, which then constitutes all or part of the axial locking means.
• the encoder ring can be attached to an annular support fixed to the rocket cap. According to various variants:
• the support can be pinched axially between a shoulder of the rocket cap and a rim of the rocket cap folded down on the support;
• the support can be deformed to penetrate into a recess of the rocket cap
• the recess may have an opening turned radially outwardly or an axial opening facing away from the distal end of the spindle cap, this recess possibly being annular; the support is in axial support against a shoulder of the rocket cap.
• the axial locking means comprise an annular protective cap defining with the rocket cap a closed housing volume of the encoder ring.
• This hood can in particular be hooped or crimped on the rocket cap.
• the encoder ring is thus particularly well protected, both during the storage phases preceding assembly on the axle stub axle and during the subsequent life of the assembly.
• the encoder which is an integral part of the instrumented assembly previously assembled into a coherent subset, is protected from shocks.
• FIG. 1 a longitudinal section of an equipped railway axle journal an instrumented bearing assembly according to a first embodiment of the invention
• Figure 2 a detail of the instrumented assembly of the rocket of Figure 1;
• FIG. 1 illustrates an axle axle 10 of a railway vehicle mounted in rotation inside an axle box 12 by means of a bearing 14 comprising at least one inner ring 16A, less an outer ring 18 and rolling bodies 20A, 20B.
• the bearing is two rows of rolling bodies, the rolling bodies 20A, 20B being constituted by tapered rollers, these rollers rolling on the outer ring 18 with two races and on two inner rings 16A, 16B, one per row of rollers 20A, 20B, separated by a spacer 22.
• the axis of rotation ZZ of the axle stub constitutes a reference axis for the device.
• the inner rings 16A, 16B are fitted on a cylindrical bearing surface 10.1 of the axle journal.
• a spacer 24 may be interposed between the inner rings 16A, 16B and a shoulder 10.2 of the axle journal 10.
• a rocket cap 26 having a bottom 26.1 and a skirt 26. free end 10.3 of the rocket 10 by means of fixing means, in this case screws 28 passing through bores 26.3 machined in the bottom 26.1 of the rocket cap 26 and screwed into threaded holes 10.4 at the end 10.3 of the axle stub 10.
• One or more spacers 30 may be interposed between the free end 26.6 of the skirt of the rocket cap and the inner rings 16A, 16B of the bearing.
• the chain of dimensions is such that when screwing the fastening screws 28 to a predetermined pair of mounting, the rocket cap 26 comes axially constrain the inner rings 16A, 16B of the bearing towards the shoulder 10.2, through the spacers 22, 24, 30 if they are present.
• the outer ring 18 is mounted in a cylindrical housing 12.1 of the axle box 12, closed by a cover 12.2 which covers the rocket cap 26.
• the rings 16A, 16B and 18 delimit between them a volume 14.1 for the rolling bodies, which volume is closed axially by sealing systems 32A, 32B, constituted in this example by deflectors defining between them, without contact, a pressure drop or baffle limiting the penetration of pollutants into the bearing and the lubricant outlet. Also shown in Figure 1 a channel 34 for regularly reloading the bearing lubricant.
• the assembly is equipped with an instrumentation assembly consisting of an encoder ring 36 integral with the rotating part and a sensor 38 integral with the fixed part, namely the axle box casing.
• this instrumentation assembly is located axially outside the bearing, between it and the axial end of the cover of the axle box.
• the encoder 36 is constituted by a magnetized ring having a plurality of north and south poles succeeding one another along its circumference.
• the sensor 38 is located at a distance and facing the encoder ring, so as to read the variations of the electromagnetic field induced by the passage of the north and south poles during the rotation of the axle stub.
• the instrumentation assembly thus provides at least one information on the rotational speed of the axle, to which may be added other information, for example relating to the angular positioning of the axle or the axial displacement of the axle. .
• the encoder 36 is fixed on an annular support 40 fitted on an outer cylindrical surface 26.4 of the skirt 26.2 of the rocket cap, in a radial recess axially delimited on one side by a shoulder 26.5 of the rocket cap and the other by a shoulder 40.1 of the annular support.
• the largest outer diameter D1 of the rocket cap, at the level of the shoulder 26.5 is greater than the outside diameter D2 of the encoder ring.
• the largest outside diameter D3 of the annular support 40 measured at the shoulder 40.1, is greater than the outside diameter D2 of the encoder ring.
• a cover 42 comprising a cylindrical skirt 42.1 of small thickness of non-magnetic material covers the annular support 40 and the encoder 36 and closes the recess where the encoder 36 is located.
• the free end 26.6 of the skirt of the flare cap forms a face annular plane.
• the annular support 40 has a bottom 40.2 constituted by an annular flat wall which faces and in contact with the end plane face 26.6 of the skirt of the rocket cap.
• the cover has a bottom 42.2 constituted by a flat annular wall which covers the bottom 40.2 of the annular support.
• the cover 42 and the annular support 40 are pinched between the end plane face 26.6 of the skirt of the axle cap and the spacer 30, prohibiting any movement subsequent relative of these parts, even in case of strong vibrations.
• the annular support 40 also takes the place of hood.
• the annular support comprises a skirt 40.3 having a portion fitted on a cylindrical bearing surface 26.4 of the rocket cap and a second end portion of smaller thickness.
• a substantially enclosed protected space is thus delimited between the cylindrical bearing surface 26.4 of the rocket cap, the end portion of the skirt 40.3 of the annular support 40, the shoulder 26.5 of the rocket cap and a shoulder 40.1 of the support connecting the the two parts.
• the encoder ring 36 which is fixed, for example by overmolding, on the annular support.
• the encoder ring 36 of elasto-ferrite material or plasto-ferrite or rare earth-doped ceramic type magnetic material (NdFeB or SaCo), is overmolded on a plate 40A sheet metal pressed, itself force-fitted on an annular support 40 similar to that of Figure 2.
• the cup 40A is pinched axially between the shoulder 26.5 of the rocket cap and the skirt 40.3 of the annular support.
• a cover of non-magnetic material 42 is fitted onto the annular support and the end 42.3 of its skirt 42.1 is crimped onto the rocket cap.
• Figure 5 derives directly from that of Figure 3, which it differs only by; the shape of the annular support 40, whose skirt 40.3 is engulfed on the largest diameter of the rocket cap 26, to completely close the annular housing volume of the encoder ring 36.
• the encoder ring 36 is fixed to the annular support 40 and housed inside the skirt 26.2 of the rocket cap, which is in this case at least locally amagnetic material, not to screen the measurement.
• FIGS. 7 to 10 are distinguished from the previous ones by the fact that the encoder ring 36 is fixed directly on the rocket cap 26.
• the encoder ring 36 is housed in an annular groove 26.7 of the rocket cap, open radially outwardly and defined axially by two shoulders. This is achieved by minimizing number of pieces, satisfactory protection of the encoder against shocks during handling.
• an at least partially nonmagnetic cover 42 having a skirt 42.1 which comes to slip on the rocket cap and completely close the housing groove 26.7 of the encoder ring, as shown on FIG. 8.
• the skirt is provided to be extended by a flat wall 42.2 which, in the mounted position, is pinched between the rocket cap and the bearing. .
• the encoder 36 it is also possible to fix the encoder 36 to the outer surface 26.4 of the skirt, which may have grooves 26.8 or various reliefs on which is molded the encoder ring 36, so that to improve the solidarity.
• the protection of the encoder is provided by the larger diameter portion D1 of the fuse cap 26 forming the shoulder 26.5 and whose diameter must imperatively be larger than that D2 of the encoder ring.
• a cover 42 illustrated in FIG. 10, similar in structure and function to that of the variant of FIG. 7.
• the embodiment of Figure 11 is another variant of that of Figure 7, and potentially of Figure 8, which is distinguished by an annular groove 26.7 whose section is dovetail, the ring encoder 36 having a corresponding shape to improve attachment of the ring 36 in the groove 26.7.
• the combined shapes of the groove 26.7 and the encoder ring 36 make it possible to ensure axial and rotational locking of the encoder ring with respect to the rocket cap 26.
• the number of parts in this embodiment is particularly small, while ensuring a good protection of the encoder ring in the mounting phases of the instrumented subassembly constituted by the rocket cap equipped with its encoder on the axle stub. If necessary, a nonmagnetic cover can cover the encoder ring.
• groove 26.7 is preferably constituted in the thickness of the bottom 26.1 of the rocket cap rather than in the skirt 26.2, so as not to mechanically weaken the rocket cap, and not interfere with the passage of an electric current passing through the rocket cap between the rotating parts and the fixed parts of the axle box.
• Figures 12 and 13 illustrate an instrumented bearing assembly for axle and rocket cap according to another embodiment of the invention.
• a bearing comprising an inner ring 16A, rolling bodies 20A and an outer ring 18.
• deflectors 32A or other systems of sealing can be provided.
• a first deflector 321 A is connected to the fixed outer ring 18 while a second deflector 322A is connected to the inner rotating ring 16A.
• a rocket cap 26 is provided, disposed on the end of the axle stub 10.
• the rocket cap 26 is in indirect axial bearing on the inner ring 16A via the second deflector 322A, which is axially interposed between these two elements.
• the fastening of the rocket cap 26 on the rocket 10 is carried out by at least one screw 28, for example with a hexagonal head passing through a hole 26.3 made in the flat bottom 26.1 of the rocket cap 26 which caps the end of the rocket 10.
• a lock washer 50 is provided in particular and in known manner to lock in rotation the connecting screw 28.
• the lock washer 50 comprises an end disc 50.1 provided with orifices 50.2 for the passage of one or more connecting screws 28 and a central cutout 50.3 providing tabs 50.4 foldable on the screw head or heads 28 to prevent loosening of the screws 28.
• the lock washer 50 further comprises a skirt 50.5 intended to be mounted at the end of the rocket cap 26 and more specifically to cover all or part of its outer cylindrical wall.
• the distal portion 50.6 of the skirt 50.5 is intended to be fitted on a cylindrical seat 26.11 formed on the outer wall of the knuckle cap 26, as shown in FIG. 12.
• a closed cylindrical volume is thus formed between the skirt 50.5 and a face cylindrical 26.4 of rocket cap 26, located radially recessed with respect to the cylindrical bearing surface 26.11 and axially between the bearing surface 26.11 and the axial end of the rocket cap 26.
• the face of the skirt 50.5 facing the face 26.4 of the rocket cap is covered by an annular magnetic encoder 36, which can be fixed for example by overmoulding.
• the lock washer 50 or at least the skirt 50.5 is here made of a non-magnetic material for example based on aluminum, copper or some types of stainless steels.
• This arrangement advantageously protects the magnetic encoder 36, which is in a closed volume located radially between the rocket cap 26 and the lock washer 50.
• FIG 14. An alternative embodiment of the previous embodiment is shown in Figure 14.
• the encoder 36 is this time fitted on the outer wall of the rocket cap 26, near its axial end and covered by the non-magnetic skirt 50.5 of the lock washer 50.
• the encoder 36 may be fixed on a cup 36.1 entirely located in the volume defined by the skirt 50.5 of the lock washer 50 and the rocket cap 26.
• the cup 36.1 itself comprises a cylindrical skirt 36.2 which carries the encoder 36 and a bottom 36.3 pinched axially between the bottom 50.1 of the lock washer 50 and the rocket cap 26.
• the bottom 36.3 of the cup is advantageously traversed by the screw or screws fixing 28 which ensure the mechanical retention of the cup 36.1 and the encoder 36 with a very high reliability over time, even in case of significant vibration.
• the skirt 50.5 and the bottom 50.1 of the lock washer 50 are in one piece, made in one piece in a non-magnetic material.
• the lock washer 50 can then be provided with an indexing relief 50.7 of the angular position of the skirt 50.5.
• the two-part construction offers the advantage of optimizing the choice of materials for bottom and skirt to suit their respective functions.
• the bottom 50.1 of the washer is not necessarily of non-magnetic material.
• the skirt 50.5 equipped with the encoder, is preassembled on the bottom 50.1, before mounting of the lock washer 50 on the rocket cap 26.
• the skirt 50.5 can be preassembled on the rocket cap 26, and the lock washer mounted in a second time.
• FIG. 17 to 19 are shown different views of another embodiment of an axle box according to the invention. Reference is made to the description of the preceding embodiments for the common elements, which bear identical reference numbers.
• This embodiment differs from the previous ones by the presence of a specific mounting bracket 40 of the encoder 36, shown in detail in FIG. 18, and by the presence of a current collector 60 for producing a current feedback loop.
• the support 40 of the encoder 36 is constituted by a cylindrical skirt 40.3 integral with a bottom 40.2 having one or more lugs 40.4, provided with through holes 40.5 for fixing screws 28, the bottom 40.1 also having at least one opening 40.6, and in the exemplary embodiment illustrated, a number of openings 40.6 equal to the number of tabs 40.4, separating them.
• the encoder 36 is overmolded on the face of the skirt 40.3 turned radially outwardly.
• the assembly consisting of the support 40 and the encoder 36 is fitted on a cylindrical bearing surface 26.4 of the rocket cap, located between the axial end of the bottom 26.1 of the rocket cap and an intermediate shoulder 26.5.
• the cylindrical bearing surface 26.4 is preferably formed in the thickness of the bottom 26.1 of the rocket cap, so as not to mechanically weaken the skirt 26.2 and not to disturb the passage of an electric current between the rotating crew and the housing 12.1 of the axle box 12.
• annular protective cover 42 consisting of a thin sheet of non-magnetic material is crimped on the rocket cap, so as to define with the rocket cap 26 and the support 40 of the encoder an annular space closed for the encoder 36.
• the largest diameter D2 the encoder is smaller than the larger diameter D1 of the rocket cap, measured at the shoulder, and the larger diameter D3 'of the protective cap.
• the positioning and fixing of the support of the encoder 36 are provided by the fastening screws 28, which may if necessary also simultaneously ensure the attachment of the rocket cap 26 to the axle stub 10. This fixation guarantees a good mechanical resistance over time, even in a severe environment subject to strong vibrations.
• the support 40 of the encoder may also constitute a lock washer for the fixing screws, which then allow tabs 40.7 to be folded over the heads of the fixing screws.
• a current return plate 60.1 is fixed to the rocket cap 26 by means of a specific screw 60.2.
• This screw 60.2 is located at one of the openings 40.6 of the support 40 of the encoder, so that the current return plate 60.1 is in direct contact with the rocket cap 26.
• the screw 60.2 does not penetrate directly into the axle stub 10 and does not constitute a screw for fixing the rocket cap 26 to the axle stub axle 10.
• the brushes 60.3 of the current collector 60 integral with the cover 12.2 of the axle box, come into rubbing contact on the plate, which is part of the rotating assembly integral with the axle, to constitute an electrical path for the current electric circulating between the rails, and the electrical equipment of the vehicle.
• Figures 20 to 23 illustrate various variants for ensuring the mechanical strength of the encoder 36 for a long time in a severe environment from the point of view of shock and vibration.
• the encoder 36 is molded or fitted on a support 40, which is itself force-fitted on a cylindrical surface 26.4 of the rocket cap 26, limited by an end shoulder 26.5.
• the flange 26.9 of the flare cap is then folded by crimping to the support 40, so that the support 40 of the encoder is located trapped axially on either side by the shoulder 26.5 and the flap 26.9.
• the support 40 of the encoder itself comprises a shoulder 40.1, the largest diameter D3 is greater than the outer diameter D2 of the encoder, thus providing protection of the encoder in the mounting phase.
• This protection can be increased by optionally providing a cover 42 fixed, for example by crimping, to the support, and one end of which is pinched by the crimped flap of the rocket cap, and whose larger diameter D3 'is also larger. than D2.
• the support 40 of the encoder 36 is in axial abutment against a shoulder 26.5 end of the rocket cap, while it comes to deform the material of the plate of the support in a groove 26.12 ring of the rocket cap so as to achieve an axial stop by hooping. It is also possible in this variant to provide an additional protective cover 42, the cover 42 and the support 40 being shrunk simultaneously during the same operation using a wheel. According to a variant, it is possible to deform the material of the sheet locally in a non-annular groove 26.12, to form an axial and radial stop.
• the support 40 of the encoder is provided with a tongue 40.8 which is folded into an axial annular groove 26.10 made on the rocket cap, to ensure the axial stop of the support 40.
• an additional protective cover 42 can also provide in this variant an additional protective cover 42, the cover and the support being folded simultaneously in the groove 26.10.
• the groove 26.10 may not be annular, so as to constitute an axial and radial attachment.
• the rocket cap is provided with a cylindrical bearing 26.4 axially open on the side of the distal end 26.6 facing the bearing 14 and limited to the bottom side 26.1 of the rocket cap by a shoulder 26.5.
• the support 40 of the encoder is shrunk on this cylindrical bearing surface 26.4 of the rocket cap, axially recessed with respect to the end 26.6 of the rocket cap. The hooping ensures axial stop and rotation stop.
• a cover 42 may also be provided.
• the support 40 of the encoder ring 36 is at a distance from the spacer 30, the clearance between these parts is low after assembly, to limit the axial displacement of the encoder in the event of axial migration in a severe environment.
• Figure 24 is for the case of an encoder 36 attached to the inner cylindrical wall of the skirt 26.2 of the rocket cap 26, facing a spacer 30 which bears, directly or with interposition of a deflector 32A, on the inner ring 16A.
• the skirt 26.2 be made of a non-magnetic material, so that the encoder signal is readable by a sensor located radially outside the skirt 26.2.
• the spacer is advantageously made of a magnetic material, to favor an amplifying mirror effect of the electromagnetic signal seen by the sensor.
• spacer 30 is advantageous for the spacer 30 to be force-fitted onto the rocket cap 26 after assembly of the encoder 36, but before mounting this subassembly on the axle stub, so as to protect the encoder 36 during the first phase. 'assembly.

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• Engineering & Computer Science (AREA)
• General Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Vehicle Body Suspensions (AREA)
• Transmission And Conversion Of Sensor Element Output (AREA)

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• 2010
  • 2010-04-30 FR FR1001870A patent/FR2959541B1/fr active Active
• 2011
  • 2011-04-29 RU RU2012151276/11A patent/RU2012151276A/ru not_active Application Discontinuation
  • 2011-04-29 WO PCT/FR2011/000266 patent/WO2011135209A2/fr active Application Filing
  • 2011-04-29 EP EP11722848A patent/EP2564208A2/de not_active Withdrawn
  • 2011-04-29 CN CN201180021572.2A patent/CN102893163B/zh not_active Expired - Fee Related
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