• 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:
    Rotor drum (10) for an aircraft turbomachine, comprising an annular wall (12) in one piece extending around a longitudinal axis (A), the wall carrying rotor blades (20) and comprising at least one device purge valve configured to allow at least one liquid to pass through said wall, characterized in that the device comprises a series of three adjacent circular orifices (30, 32, 34), these three orifices being aligned along a line and comprising a central orifice (30) of larger diameter D1 and two lateral orifices (32, 34) of smaller diameter D2 diametrically opposed with respect to the central orifice.
    公开号:BE1027233B1
    申请号:E20205297
    申请日:2020-05-05
    公开日:2021-06-01
    发明作者:Sami Kelim Benichou；Arnaud Michel Marie Accary；Grégoire Decock；Guillaume Lescurat；Ludovic Pericaud
    申请人:Safran Aero Boosters；Safran Aircraft Engines；
    IPC主号:
    专利说明:

    ROTOR DRUM FOR A TURBOMACHINE Technical Field of the Invention The present invention relates to a rotor drum for an aircraft turbomachine, as well as to a turbomachine comprising such a drum.
    Technical background The technical background includes in particular document EP-A1- 3 192 966. An aircraft turbomachine can comprise several rotating bodies or rotors which rotate inside stators.
    A turbomachine rotor, such as a compressor or turbine rotor, comprises several rotor blades which are intended to be interposed between stator blades.
    In the present application, a blade is defined as comprising an annular row of blades.
    A turbomachine rotor can be produced by assembling several coaxial discs, each disc carrying an annular row of rotor blades and being fixed by screw-nut type fastening means to adjacent discs.
    The blades can be attached and fixed to a rotor disc or else be formed integrally with the latter (in the case of a one-piece bladed disc or DAM). It is also known practice to produce a turbomachine rotor by means of a drum which comprises a one-piece wall of revolution extending around a longitudinal axis and capable of carrying several rotor blades.
    FIG. 1 shows an exemplary embodiment of a drum 10 of a turbomachine.
    The wall 12 of the drum 10 can be more or less convex and have the shape of a barrel.
    Its external diameter
    ; BE2020 / 5297 therefore varies between its axial ends and is the largest in a transverse plane denoted P.
    Figure 1 shows only a lower half section of the drum and therefore only the lower part of this drum.
    The point X is a low point or the lowest point of the drum and is located in the plane P of greatest diameter of the drum 10. The drum is mobile in rotation therefore the point X moves on the drum.
    The wall 12 comprises annular thicknesses 14 in which annular grooves 16 are formed which open out radially outwards with respect to the axis A.
    These grooves 16 have in section a shape suitable for retaining the feet 18 of the rotor blades 20. The technique for mounting and retaining the feet 18 of the blades 20 in the grooves 16 is known to those skilled in the art.
    All the blades 20 mounted in the same groove 16 form a rotor blade.
    The radially outer tops or ends of the vanes 20, opposite the feet 18, are surrounded by layers 22 of abradable material carried by a stator casing 24. The casing 24 further carries stator vanes 26 interposed between the rotor vanes.
    The barrel shape of the drum 10 depends on and is a function of the shape of the flow path of the gas flow and in the case of the presence of liquid in the drum 10, the bulge thus created generates an annular liquid retention zone (s) 28, as illustrated in Figure 1. In fact, in operation, oil, fuel or water can accumulate in the drum.
    It is important to remove these fluids to avoid their retention.
    A solution to this problem could consist in equipping the drum with a purge device configured to allow at least one liquid to pass through the wall 12. However, the proposals made so far are not satisfactory and the present invention provides a solution. simple, efficient and economical if necessary mentioned above. Summary of the Invention The present invention relates to a rotor drum for an aircraft turbomachine, comprising an annular wall extending around a longitudinal axis, the wall carrying rotor vanes and comprising at least one purge device configured to allow at least one liquid to pass through said wall, characterized in that the device comprises a series of three adjacent circular orifices, these three orifices being aligned along a line and comprising a central orifice of larger diameter D1 and two Lateral orifices of smaller diameter D2 diametrically opposed with respect to the central orifice.
    The inventors have thus developed a purge device optimized for the flow and discharge of liquids, such as oil, fuel or water, through the wall of the drum. This solution is advantageous compared to a single orifice which could weaken and therefore further reduce the mechanical strength of the part. In the present case, the orifices can have cumulative passage sections equivalent to that of a single orifice while controlling and limiting the impact on the mechanical strength of the drum. This solution is also advantageous compared to a non-circular orifice and for example oblong or ellipse because these types of orifices are complex and expensive to produce because they generally require a specific machining machine, increased mastery of tool paths and a more precise dimensional control in order to be able to properly characterize these complex shapes.
    The diameters of the orifices can be chosen as a function of the volume of liquids to be purged per minute and in accordance with the number of devices of the drum and their respective locations. The diameters and the locations of the orifices must in particular take into account the dimensional constraints of manufacture and of resistance of the drum, in particular when the latter must undergo a treatment subsequent to the making of the orifices, for example shot blasting.
    The drum according to the invention can comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another: - the side openings have the same diameter D2 to within 10%, - D2 <D1 <1 , 5.D2, - D1 is between 3 and 10mm and D2 is between 2 and 8mm, - the centers of the side holes are located at the same distance L from the center of the main hole, - Di <L <2. D1, - L is between 5 and 15mm, - the orifices are aligned on a circumference centered on said longitudinal axis, - the wall of the drum is made of a metal alloy, - the orifices are made by machining, - the annular wall is in one piece or sectorized. The present invention also relates to an aircraft turbomachine, comprising a drum as described above. Preferably, the drum comprises several bleeding devices distributed over the same circumference centered on the longitudinal axis. Alternatively, the drum could include several devices distributed over several circumferences centered on the axis. The present invention also relates to an aircraft comprising a turbomachine of the type described above.
    Brief description of the figures Other characteristics and advantages of the invention will become apparent on reading the detailed description which follows for
    ° BE2020 / 5297 the understanding of which reference is made to the appended drawings in which:
    [Fig. 1] FIG. 1 is a schematic half view in axial section of an aircraft turbomachine, and shows a rotor drum in particular, [Fig. 2] Figure 2 is a schematic perspective view of a purging device according to the invention, of the wall of a rotor drum, and [Fig. 3] FIG. 3 is a very schematic view of the orifices of the device of FIG. 2. Detailed description of the invention FIG. 1 has been described in the foregoing.
    The invention provides a purging device for a turbomachine drum 10, such as that shown in FIG. 1. The drum 10 can comprise one or more devices and for example a device at point X, that is to say in a lower part or in the lower part of the drum when the drum is stationary in the turbomachine.
    Figures 2 and 3 show a preferred embodiment of the device which comprises a series of three circular orifices 30, 32, 34 adjacent.
    These three orifices 30, 32, 34 are aligned along a line and are a central orifice 30 of larger diameter D1 and two lateral orifices 32, 34 of smaller diameter D2 diametrically opposed with respect to the central orifice 30. The line of alignment of the orifices 30, 32, 34 is preferably a circumference centered on the axis A.
    The orifices 30, 32, 34 are thus aligned on a circumference of the axis A, as can be seen in FIG. 2. Preferably, the angular orientation of the orifices is directed substantially on a line linked to the specific constraints of the part. .
    The orifice 30 is therefore located at point X, that is to say in the section plane of Figure 1, and the orifices 32, 34 are diametrically opposed with respect to the orifice 30 and located
    ° BE2020 / 5297 respectively in front and behind this plane and therefore not visible in figure 1.
    The orifices 32, 34 have the same diameter D2. Preferably, D2 <D1 <1.5.D2. By way of example, D1 is between 5 and 10mm and D2 is between 4 and 8mm. The centers of the orifices 32, 34 are located at the same distance L from the center of the orifice 30. Preferably, D1 <L <2.D1. L is for example between 7.5 and 15mm. The device according to the invention makes it possible to effectively purge the drum by reducing the stresses in the zone where the device is located, and by facilitating their production, for example by machining and in particular drilling. As mentioned in the foregoing, the drum can comprise several devices and therefore several series of three orifices. The devices are preferably located in the P plane and regularly distributed around the X axis. The increase in the number of devices on the same circumference makes it possible to guarantee that at least one of the devices will be located as close as possible to the point X. Given that the axis A of the turbomachine is not always horizontal in use, in particular during the takeoff and landing phases of the aircraft equipped with this turbomachine, the drum 10 could be equipped with a device or devices outside the X plane and for example downstream from this plane (with reference to the flow of gases in the flow of the turbomachine). Figure 1 shows a Y plane passing upstream of the rotor blading of the fourth stage, in which the purge devices according to the invention could be located.
    权利要求:
    Claims (10)
    [1]
    1. Rotor drum (10) for an aircraft turbomachine, comprising an annular wall (12) extending around a longitudinal axis (A), the wall carrying rotor blades (20) and comprising at least one purge device configured to allow at least one liquid to pass through said wall, characterized in that the device comprises a series of three adjacent circular ports (30, 32, 34), these three ports being aligned along a line and comprising a central orifice (30) of larger diameter D1 and two lateral orifices (32, 34) of smaller diameter D2 diametrically opposed with respect to the central orifice.
    [2]
    2. Drum (10) according to claim 1, wherein D2 <D1 <1.5.D2.
    [3]
    3. Drum (10) according to one of the preceding claims, wherein D1 is between 3 and 10mm and D2 is between 2 and 8MM.
    [4]
    4. Drum (10) according to one of the preceding claims, wherein the centers of the side holes (32, 34) are located at the same distance L from the center of the main hole (30).
    [5]
    5. Drum (10) according to claim 4, wherein Dl <L <
    2.D1.
    [6]
    6. Drum (10) according to claim 5, wherein L is between 5 and 15mm.
    [7]
    7. Drum (10) according to one of the preceding claims, wherein the orifices (30, 32, 34) are aligned on a circumference centered on said longitudinal axis (A).
    [8]
    8. Aircraft turbomachine, comprising a drum (10) according to one of the preceding claims.
    [9]
    9. Turbomachine according to claim 8, wherein the drum (10) comprises several bleeding devices distributed over the same circumference centered on said longitudinal axis (A),
    or even several devices distributed over several circumferences centered on the axis (A).
    [10]
    10. Aircraft comprising a turbomachine according to claim 8 or 9.
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20200362702A1|2020-11-19|
    FR3096073B1|2021-05-14|
    BE1027233A1|2020-11-20|
    FR3096073A1|2020-11-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20140147286A1|2012-11-29|2014-05-29|Mtu Aero Engines Gmbh|Turbomachine rotor disk|
    FR3028781A1|2014-11-25|2016-05-27|Snecma|AIRCRAFT TURBOMACHINE ROTOR PIECE COMPRISING A MACHINEABLE ANNULAR PROTUBERANCE PROVIDED WITH A DEHYLING ORIFICE AND METHOD OF PREPARING THE SAME|
    EP3192966A1|2016-01-14|2017-07-19|MTU Aero Engines GmbH|Rotor for an axial flow engine with axially aligned momentum flange and compressor|
    US20180087534A1|2016-09-23|2018-03-29|MTU Aero Engines AG|Rotor stage for a turbomachine, rotor drum, and rotor|
    法律状态:
    2021-07-15| FG| Patent granted|Effective date: 20210601 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1904970A|FR3096073B1|2019-05-13|2019-05-13|ROTOR DRUM FOR A TURBOMACHINE|
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