• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a method for ventilating discs (11) of a brake (10) fitted to an aircraft wheel (1) having a rim (2) mounted for rotation on an axle (4) of a landing gear the aircraft, the brake disks being threaded onto a torsion tube (12) of the brake which extends around the axle, the method comprising the step of integrating a compressor (20; 30; 40) into a space extending inside the torsion tube to draw air under the torsion tube, and to return air thus sucked by the compressor over the torsion tube to the brake discs.
    公开号:FR3040454A1
    申请号:FR1557958
    申请日:2015-08-27
    公开日:2017-03-03
    发明作者:Vincent Gonzalez；Arnaud Gapin
    申请人:Messier Bugatti Dowty SA；
    IPC主号:
    专利说明:

    The invention relates to a method for ventilating brake discs of an aircraft wheel.
    BACKGROUND OF THE INVENTION
    Aircraft are known whose wheels equipped with a brake are provided with a controllable fan to cool the brake discs, in order to lower their temperature rapidly and thus avoid delaying the departure of the aircraft for a new rotation. In general, the fan body is engaged inside the axle carrying the wheel, and its turbine sucks air through openings in the rim of the wheel. However, the fan thus disposed occupies an important place in the axle so that the axis of the tachometer for measuring the speed of rotation of the wheel is lengthened to cross the fan and reach the wheel. This therefore reduces the measurements made by the tachometer.
    Also known, especially in the automotive field, turbines secured to the rim of the wheel to suck air through the rim of the wheel. These turbines are for example integrated into a cap mounted on the rim.
    OBJECT OF THE INVENTION The object of the invention is to propose a method for ventilating brake disks of an aircraft wheel without monopolizing the inside of the axle, nor hiding the jaw.
    PRESENTATION OF THE INVENTION
    In order to achieve this goal, a method is proposed for ventilating the disks of a brake fitted to an aircraft wheel having a rim mounted to rotate on an axle of a landing gear of the aircraft, the brake disks being threaded onto a torsion tube of the brake which extends around the axle, the method comprising the step of integrating a compressor into a space extending inside the torsion tube for sucking air under the torsion tube, and to return the air thus sucked by the compressor over the torsion tube to the brake discs.
    Thus, the compressor is completely integrated in the wheel, extending into a space between the torsion tube and the axle, and therefore does not occupy the interior of the axle which is therefore free to receive a tachometer, and let the rim free for its visual inspection and access to the inflation valve. Advantageously, the tachometer can have an axis of relatively small size which improves the quality of its measurements.
    DESCRIPTION OF THE FIGURES The invention will be better understood in the light of the following description with reference to the figures of the accompanying drawings, in which: FIG. 1 is a view in axial section of a wheel rim mounted on an axle; aircraft landing gear and equipped according to a first embodiment of the invention of an axial compressor installed between the torsion tube and the axle; - Figure 2 is a partial section in another plane of the rim of Figure 1, showing the air passages feeding the compressor; - Figure 3 is a view similar to that of Figure 1 of a first variant of the first implementation, wherein the rim has plugged openings; - Figure 4 is a view similar to that of Figure 1 of a second variant of the first implementation, wherein the rim has unobstructed openings; - Figure 5 is a view similar to that of Figure 1 of a second embodiment in which an axial compressor is installed between the torsion tube and a hub portion of the rim; - Figure 6 is a view similar to that of Figure 1 of a third embodiment of the invention, implementing a centrifugal compressor installed between the torsion tube and the axle; FIG. 7 is a perspective view of the impeller of the compressor of FIG. 6; - Figure 8 is a view similar to that of Figure 4 of a fourth embodiment of the invention using a volute; FIG. 9 is a perspective view of the volute and the impeller of FIG. 8; - Figure 10 is a view similar to that of Figure 1 of a variant of the fourth embodiment of the invention, wherein the web of the half-rim is closed.
    DETAILED DESCRIPTION OF MODES OF IMPLEMENTATION OF THE INVENTION The invention applies to an aircraft wheel 1 comprising a rim 2, here comprising two half-rims 2a, 2b assembled by bolts 3, and mounted to turn on an axle 4 by means of bearings 5 carried by a hub 6 of the rim 2. The wheel 1 is equipped with a brake 10 comprising brake disks 11, including stator disks 11a and rotor disks 11b, which are threaded on a torsion tube 12 fixed to an axle hand 13 by bolts 14. The brake 10 comprises a support 15 of braking actuators 16 adapted to selectively apply a braking force on the disk stack 11.
    According to a first mode of implementation of the invention illustrated in FIG. 1, an axial compressor 20 is provided inside the torsion tube 12 comprising rotating vanes 21 mounted on a ring 22 integral with the rim 2. and thus rotating with the wheel, and fixed straightening vanes 23 secured to the torsion tube. The air is sucked by the compressor 20 through the spaces between the torsion tube 12 and the axle hand 13 (visible in FIG. 2), pushed back inside the rim and pushed over the torsion tube. 12 between the brake discs 11 and the rim 2 to emerge over the brake actuators 16. The air thus travels a circuit inside the half-rim 2a on either side of the torsion tube 12 , as indicated by the arrows in the figure.
    It will be noted that the web 7 of the half-rim 2a which extends to connect the hub 6 to the remainder of the rim is closed and does not have ventilation openings which would allow the air flows to be evacuated. through the rim to the outside. This absence of cells simplifies the design of the rim. The half-rim 2a then acts as a deflector which forces the flow of air from the compressor 20 to the brake discs 11.
    Referring to Figure 3, according to a first variant of the first embodiment, the rim 2 here comprises ventilation openings 60 at the level of the web 7 of the half-rim 2a also called ventilation cells. These ventilation openings 60 here comprise covers 61 able to plug the openings. In this way, despite the presence of the ventilation openings 60, the air flow can not escape through the rim to the outside. The air thus traverses a circuit inside the half-rim 2a on either side of the torsion tube 12 as indicated by the arrows in FIG.
    Referring to Figure 4, according to a second variant of the first embodiment, the rim 2 here comprises ventilation openings 60 at the web 7 of the half-rim 2a.
    The ventilation openings 60 here have no cover so that a part of the flow is discharged through the rim to the outside, the other part of the air flow being pushed between the brake discs 11 and the rim 2 to come out over the brake actuators 16.
    According to a second mode of implementation of the invention illustrated in FIG. 5, the axial compressor 30 is always installed inside the torsion tube 12, but here it extends more precisely between the torsion tube 12 and the hub 6 of the rim 2. The turbine 30 here comprises three successive stages each comprising rotating blades 31 followed by fixed straightening vanes 32. The operation of the axial compressor 30 is identical to that of the axial compressor 20.
    As for the variants of the first embodiment, the web 7 of the half-rim 2a may, in a variant, have obstructed openings or not.
    According to a third mode of implementation illustrated in FIGS. 6 and 7, the wheel is now equipped with a centrifugal compressor 40 (or radial compressor), which still extends inside the torsion tube 12. The compressor 40 here is a compressor comprising a impeller 41 (a single blade is referenced here) which is integral in rotation with the wheel. The paddle wheel draws air through 360 degrees of the inside diameter of the paddle wheel 41. The compressed air is then ejected by the compressor 40 over the 360 degrees of the outer diameter of the compressor and thus in part toward the tube. twist 12, the air then escaping passing over the torsion tube 12 between the rim and the brake discs, as before.
    As for the variants of the first embodiment, the web 7 of the half-rim 2a may, in a variant, have obstructed openings or not.
    According to a fourth mode of implementation illustrated in FIGS. 8, 9, the compressor 50 is still of the centrifugal type, but now comprises a paddle wheel 51 and a volute 52, the paddle wheel 51 rotating inside the volute 52. The volute 52 is here off-axis relative to the impeller 51. The volute 52 here comprises air inlets 53 in its widest part.
    It is found here that the web 7 of the half-rim 2a has ventilation openings 50 which are unobstructed.
    Due to the centrifugal action of the compressor 50, the air is sucked by the lower part of the compressor 50 at the openings 53 of the volute 52 and rejected over the 360 degrees of the outer diameter of the compressor 50 so as to be forced back towards the compressor. inside the rim. The air is then: - in a minority manner, pushed over the torsion tube 12 between the brake discs and the rim 2 to emerge over the braking actuators 16, - and in a majority manner, pushed towards the outside air through the ventilation openings 60. The air thus travels a circuit inside the half-rim 2a on either side of the axle 4 and then on either side of the torsion tube, as indicated by the arrows in Figure 8.
    Alternatively, as shown in Figure 10, the web 7 of the half-rim 2a is closed so that the air is discharged at the level of the brake actuators. Alternatively, the veil may include ventilation openings obstructed in whole or in part by covers. The invention is not limited to what has just been described, but on the contrary covers any variant within the scope defined by the claims.
    In particular, although here the moving parts of the compressors rotate with the wheel, they can be motorized to turn independently of the wheel.
    Although the return of the air sucked by the compressor over the torsion tube is provided by the closed web of the wheel, it is possible to use wheels whose rims have openings (ventilation cells), possibly adapting a light cover adapted to plug these openings.
    Although the rotating blades here are followed by straightening vanes, we can dispense with the latter, the compressor then having only rotating blades.
    In the case where the compressor will have blades they may equally well be straight blades that curved vanes preferentially in the preferred direction of rotation of the wheel.
    Similarly, in the case where the compressor will have blades they can be indifferently short or long regardless of the compressor used.
    In the case of a radial compressor, it may be shaped so that air is sucked 360 ° from its inlet or so that air is sucked in an angular sector only of its inlet port. Preferably, the angular sector will be arranged so that the compressor sucks the air from its lower portion.
    Moreover, in the case of a radial compressor, it may be shaped so that the compressed air is rejected in 360 ° of its outlet or so that the compressed air is rejected in an angular sector only of its outlet. Preferably, the angular sector will be arranged so that the compressor rejects the compressed air from its upper portion to the top of the torsion tube and the upper web of the rim.
    In the case of a radial compressor such as an axial compressor, the method may comprise the additional step of associating a multiplier with the compressor, for example by arranging the multiplier between the wheel and the compressor.
    1. A method of ventilating discs (11) of a brake (10) fitted to an aircraft wheel (1) having a rim (2) mounted to rotate on an axle (4) of a propeller aircraft, the brake disks being threaded onto a torsion tube (12) of the brake which extends around the axle, the method comprising the step of integrating a compressor (20; 30; 40) into a space extending inside the torsion tube to draw air under the torsion tube, and to return air thus sucked by the compressor over the torsion tube to the brake discs. 2. The method of claim 1, wherein the compressor is of the axial type and comprises at least one stage comprising rotating blades (21; 31) followed by fixed rectifying vanes (22; 32). 3. The method of claim 2, wherein the rotating vanes are not followed by fixed straightening vanes. The method of claim 1, wherein the compressor is of the centrifugal type (40, 50). 5. The method of claim 4, wherein the compressor (40, 50) is shaped so that it has worse air only at its lower portion. 6. Method according to one of claims 4 to 5, wherein the compressor (40, 50) is shaped so that it ejects compressed air only at its upper part over the torsion tube. 7. Method according to one of claims 4 to 6, wherein the compressor comprises a bladed wheel (51) associated with a volute (52) of the compressor. 8. Method according to one of claims 1 to 7, wherein the rim comprises a closed web (7) adapted to return a flow of air generated by the compressor to the brake discs. 9. Method according to one of claims 1 to 7, wherein the rim comprises openings (60) at the web (7). 10. The method of claim 9, wherein the openings (60) comprise covers (61) adapted to close at least partly said openings. 11. Method according to one of claims 1 to 10, wherein the compressor (40, 50) comprises straight vanes. 12. Method according to one of claims 1 to 11, wherein the compressor (40, 50) comprises curved vanes.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. A method of ventilating disks (11) of a brake (10) fitted to an aircraft wheel (1) having a rim (2) mounted for rotation on an axle (4) of an aircraft propulsion device aircraft, the brake disks being threaded onto a torsion tube (12) of the brake which extends around the axle, the method comprising the step of integrating a compressor (20; 30; 40) in a space s extending inside the torsion tube to draw air under the torsion tube, and to return air thus sucked by the compressor over the torsion tube to the brake discs.
    [2" id="c-fr-0002]
    2. The method of claim 1, wherein the compressor is of the axial type and comprises at least one stage comprising rotating blades (21; 31) followed by fixed rectifying vanes (22; 32).
    [3" id="c-fr-0003]
    3. The method of claim 2, wherein the rotating vanes are not followed by fixed straightening vanes.
    [4" id="c-fr-0004]
    The method of claim 1, wherein the compressor is of the centrifugal type (40, 50).
    [5" id="c-fr-0005]
    5. The method of claim 4, wherein the compressor (40, 50) is shaped so that it has worse air only at its lower portion.
    [6" id="c-fr-0006]
    6. Method according to one of claims 4 to 5, wherein the compressor (40, 50) is shaped so that it ejects compressed air only at its upper part over the torsion tube.
    [7" id="c-fr-0007]
    7. Method according to one of claims 4 to 6, wherein the compressor comprises a bladed wheel (51) associated with a volute (52) of the compressor.
    [8" id="c-fr-0008]
    8. Method according to one of claims 1 to 7, wherein the rim comprises a closed web (7) adapted to return a flow of air generated by the compressor to the brake discs.
    [9" id="c-fr-0009]
    9. Method according to one of claims 1 to 7, wherein the rim comprises openings (60) at the web (7).
    [10" id="c-fr-0010]
    10. The method of claim 9, wherein the openings (60) comprise covers (61) adapted to close at least partly said openings.
    [11" id="c-fr-0011]
    11. Method according to one of claims 1 to 10, wherein the compressor (40, 50) comprises straight vanes.
    [12" id="c-fr-0012]
    12. Method according to one of claims 1 to 11, wherein the compressor (40, 50) comprises curved vanes.
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    同族专利:
    公开号 | 公开日
    US10203010B2|2019-02-12|
    EP3144555B1|2017-11-01|
    CN106477029A|2017-03-08|
    FR3040454B1|2017-09-01|
    US20170058981A1|2017-03-02|
    CN106477029B|2019-12-10|
    EP3144555A1|2017-03-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE1113149B|1957-06-25|1961-08-24|Klaue Hermann|Disc brakes, especially for motor vehicles|
    FR1439992A|1964-04-13|1966-05-27|Bendix Corp|Forced air cooled disc brakes|
    US3664467A|1968-08-07|1972-05-23|Meisser|Disc brake cooling device|
    EP0483719A1|1990-10-30|1992-05-06|Gec Alsthom Sa|Brake system for railway vehicle|
    US3142360A|1962-01-08|1964-07-28|Goodyear Tire & Rubber|Turbo-brake|
    GB1490743A|1974-02-08|1977-11-02|Dunlop Ltd|Wheel and disc brake assembly|
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    US6698557B2|2001-09-10|2004-03-02|Arvinmeritor Technology, Llc|Brake drum cooling apparatus|
    US8528856B2|2010-10-29|2013-09-10|Honeywell International, Inc.|Compact electric taxi assembly for installation on an aircraft|
    CN104159821A|2012-02-23|2014-11-19|L-3通信磁电机股份有限公司|Drive unit for aircraft landing gear with integrated cooling|
    US9708056B2|2012-12-14|2017-07-18|L-3 Communications Magnet-Motor Gmbh|Wheel drive unit for attachment to an aircraft running gear|FR3035937B1|2015-05-06|2018-10-05|Commissariat A L'energie Atomique Et Aux Energies Alternatives|BRAKE SYSTEM|
    US10473171B2|2017-05-15|2019-11-12|Goodrich Corporation|Extended torque tube|
    FR3083271B1|2018-06-27|2020-09-04|Safran Landing Systems|CONTROL PROCEDURE FOR A THREE-POSITION DRAWER DISPENSER|
    US11156092B2|2019-02-07|2021-10-26|Honeywell International Inc.|Multistage axial-centrifugal compressor systems and methods for manufacture|
    CN112849103A|2021-01-25|2021-05-28|中国商用飞机有限责任公司|Cooling mechanism for airplane wheel and brake device|
    法律状态:
    2016-08-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-03| PLSC| Search report ready|Effective date: 20170303 |
    2017-08-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-07-20| CD| Change of name or company name|Owner name: SAFRAN LANDING SYSTEMS, FR Effective date: 20180618 |
    2018-08-27| PLFP| Fee payment|Year of fee payment: 4 |
    2019-07-23| PLFP| Fee payment|Year of fee payment: 5 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1557958A|FR3040454B1|2015-08-27|2015-08-27|METHOD FOR VENTILING BRAKE DISCS OF AN AIRCRAFT WHEEL|FR1557958A| FR3040454B1|2015-08-27|2015-08-27|METHOD FOR VENTILING BRAKE DISCS OF AN AIRCRAFT WHEEL|
    EP16185030.0A| EP3144555B1|2015-08-27|2016-08-19|Method for ventilating brake discs of an aircraft wheel|
    US15/248,331| US10203010B2|2015-08-27|2016-08-26|Method for ventilating brake discs of an aircraft wheel|
    CN201610922573.9A| CN106477029B|2015-08-27|2016-08-29|Method for ventilating a brake disc of an aircraft wheel|
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