• 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 mounting blades (10) at the periphery of a turbomachine disk (12), the disk (12) comprising cells alternately extending with teeth, the blades (10) respectively comprising : - feet to be inserted into the cells, - heels (26), and - blades (24) connecting the feet to the heels. According to the invention, the method comprises the steps of: (a) positioning the blades (10) so that the foot of each blade is axially facing one of the cells of the disk, (b) providing a tool mounting member (50) comprising a tip (40) shaped in part complementary to the heel (26) of one of the blades, (c) causing the tip (40) of the mounting tool (50) to cooperate with the heel (26) of the blade, (d) pivoting the blade root (26) by a rotational movement (54) of the mounting tool (50), and (e) axially inserting the foot of the blade (26). dawn in the alveolus of the disc
    公开号:FR3023581A1
    申请号:FR1456554
    申请日:2014-07-08
    公开日:2016-01-15
    发明作者:Sebastien Congratel；Christian Bariaud；Dominique Jean Andre Bousquet
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to the assembly of vanes at the periphery of a disk of a turbomachine, which may occur during the assembly of the turbomachine. The invention will be particularly suitable for disks that belong to a turbine engine low-pressure turbine. It relates to a mounting method, as well as a particular tool allowing the implementation of the method.
    [0002] In the context of the assembly of the parts of a turbomachine, for commercial purposes of complete production of the turbomachine for sale, or experimental for testing, testing or experimentation of the turbomachine or partial elements of the latter, it involves a step of blade assembly on the periphery of a turbomachine disk. The disc is a rotating part of the turbomachine attached to the low pressure shaft or the high pressure shaft of the turbomachine. The blades, once mounted on the disc, allow the transfer of energy between the flow through the secondary vein of the turbomachine and one of these trees.
    [0003] In order to ensure a structural retention of the blades around the disk, the disk comprises at its periphery cells oriented substantially parallel to the axis of the disk, and arranged alternately with the teeth of the disk. The blades comprise at their inner ends feet which, one faith inserted in the cavities of the disc, are retained radially by shape cooperation by the teeth of the disc. The blade roots are further extended radially by blades, then by heels constituting the outer ends of the blades. The heels generally comprise external wipers, that is to say outer radially projecting walls which are intended to cooperate with a radially outer element of the turbomachine. The heels may further comprise axial spoilers, that is to say axial walls intended to extend upstream and / or downstream of the heel in the turbomachine to define the outer limit of the secondary vein. In order to assemble the vanes and the disc, at first all the vanes to be mounted on the disc, aligned end to end circumferentially, are assembled in a configuration similar to their final state mounted on the disc. This "crown" of blades is then positioned in front of the disk so that the blade roots are axially facing the corresponding cells of the disk. The assembly is done by axial displacement of the blades, one by one, to insert the feet axially into the cells. Optionally, foils are arranged around the blade roots to serve as an interface between the feet and the cells and thus avoid their respective wear. The assembly of the blades is however made difficult by the shape of the heels. Indeed, the heels are oriented so as to be in circumferential supports on each other along a direction which is not the same as the direction of introduction of the blade roots into the cells. Thus, when attempting to mount a blade on the disc, the heel of this blade is blocked in axial displacement by the heels of the adjacent blades.
    [0004] In order to allow the blades to be fitted, wooden, plastic or other wedges are used which are inserted between the blades of the blades and separate the vanes from each other. The heels are no longer in support on each other, and it is possible to slide the dawn in the cell, without the heels are retained. However, such wedges can easily cause deformations, shocks or scratches on the blades, which can alter the mechanical strength of the blades and cause some blades to discard and restart the assembly of the blades on the disc. It has also been noticed that this method made it difficult to insert the foils correctly into the cells.
    [0005] It also happens that the blades are removed manually, which obviously implies the risk of accidents at work for the manipulator. The present invention provides a simple, effective and economical solution to facilitate the mounting of the blades on the disc. To this end, it proposes a method of blade assembly at the periphery of a turbomachine disk, relative to the axis of rotation of the disk, the disk comprising, at its radially outer periphery, cells extending substantially parallel to the axis of the disk and arranged alternately with teeth of the disc, the blades comprising respectively: - at a first radially inner end of the feet to be inserted into the cavities of the disk, - at a second radially outer end of the beads, and - blades connecting the feet to the heels, the method comprising the steps of: (a) positioning the blades in circumferential alignment so that the root of each blade is axially facing one of the cells of the disk, (b) providing a mounting tool comprising a shaped tip partially complementary to the heel of one of the vanes, (c) causing the tip of the mounting tool to engage the heel of the blade, (d) making pivoting the heel of the blade by a rotational movement of the mounting tool around a radial direction of the disk passing through the blade, and (e) axially inserting the root of the blade into the cell of the disk . In order to allow the mounting of one of the vanes, it is pivoted his heel around the radial direction until its support with the adjacent heels is in the same direction as the direction of introduction of the vanes into the cells. It is thus possible to slide the blade into the cell without the heel being retained. The tool used, because of its complementary shape with the heel, does not induce excessive localized stresses at dawn when it is rotated in order to rotate the heel. Handling is also very easy and fast for a user, and is unlikely to fail. It has further been noted that the invention allows a better engagement of foils in the alveoli of the disc. In a particular embodiment, at the end of step (a), the vanes of the vanes are circumferentially supported on each other along flanges oriented in a direction different from that in which the blade roots are oriented. .
    [0006] Advantageously, the method involves as many blades to be mounted on the disk as disk cells, and the steps (b), (c), (d) and (e) are repeated successively for all the blades. Preferably, all the blades are of identical shapes, and one and the same mounting tool is used during the repetition of steps (b), (c), (d) and (e). Prior to step (a), it is possible to mount a foil around the foot of the dawn, the foil being inserted with the foot of the dawn into the cell during step (e). The foil reduces wear on blade roots and cells.
    [0007] Advantageously, the mounting tool comprises gripping means such as a handle. Preferably, the gripping means and the tip of the mounting tool are removable relative to each other. It is thus possible to manufacture several complementary tips to different types of blades, while using the same gripping means that can be connected to each of these tips. According to a particular embodiment, the tip of the mounting tool comprises two axial stops between which are adjusted with a small clearance the axial ends of the heel during step (c). During step (c), the heel is thus taken by the mounting tool between the two stops, which implies that a rotation of the tool causes contact reaction a rotation of the heel. According to a remarkable embodiment, the tip of the mounting tool comprises at least one slot in which is adjusted with a small clearance at least one lick of the heel of the blade during step (c). This allows the mounting tool to provide an even better grip on the heel when rotating. The invention further relates to a blade mounting tool for mounting vanes at the periphery of a turbomachine disk as described above, comprising a tip shaped in part complementary to the heel of a blade, so as to ability to rotate the heel and the mounting tool in rotation, in particular around the direction of extension of the blade which corresponds to the alignment direction between the foot, the blade and the heel. The tip may comprise a face from which two shoulders facing one another face the axial ends of the heel of a blade, said face further comprising, between the two shoulders, at least one slot oriented substantially in parallel. to the shoulders, and intended to cooperate with a lash of the heel of a blade. Other advantages and features of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings, in which: FIG. 1 is a side view of a blade intended to be mounted on a turbomachine disk; Figure 2 is a view of a foil adapted to the foot of the blade of Figure 1; Figure 3 is a view of the disc and blades at the end of step (a) of the invention; Figure 4 is a magnification of the framed area of Figure 3; FIG. 5 is a tip of complementary shape to the heel of the blade of FIG. 1; Figure 6 is a view of the complete mounting tool including the tip of Figure 5; and - Figure 7 is a diagram of use of the mounting tool according to the invention. With reference to FIG. 1, a blade 10 is described intended to be mounted on a turbomachine disk 12. More particularly, the blade example shown, and disk thereafter, corresponds to a low-pressure turbine stage of the turbomachine. The blade extends longitudinally along a so-called radial direction, with reference to the radius of the turbomachine axis 16. The radially inner portion of the blade is a foot 14, intended to be mounted in a cell 18 of a disk , and extended externally by a stilt 20, then by a platform 22, then by a blade 24, and finally by a heel 26. The heel is composed of a platform 28 and further comprises on its outer face wipers 30, which are walls extending substantially radially outwardly and circumferentially. The blade is intended to interact with the flow of gas passing through the turbomachine in order to exchange the energy with the disk 12. The two platforms 22, 28 are walls that extend cylindrically on either side of the turbine. dawn 10, and respectively delimit internally and externally the vein where the flow of gas flows. Spoilers 32, 34 further extend upstream and downstream of the inner platform 22 and the outer platform 28 for the same purpose. In FIG. 2, it can be seen that the root 14 of the blade has a shape of bulb substantially complementary to the shape of a cell 18 of the disk 12. It is usual to mount a foil 36 on the root 14 of each blade 25 , that is to say a wall that surrounds the foot while conforming to its shape, and that will protect against wear the walls of the foot and the cell in which it is mounted. In Figures 3 and 4, we see the disc 12 on the periphery of which all the blades have been pre-positioned for mounting. The blades 10 are circumferentially end to end, so that the platforms 22, 28 of the vanes are in circumferential contact with each other, whether the inner platforms 22 or outer 28 blades. It can also be seen that the teeth 38 of the disc allow the blades 10 to be retained radially when the feet 14 are mounted in the cavities 18. The internal platforms 22 of the vanes have their circumferential edges oriented in the same direction as the direction of introduction. Feet 14 in the cells 18. All the blades 10 are offset axially with respect to their final positions, so that the feet 14 of the vanes are axially facing the cells 18 of the disc 12 before assembly.
    [0008] FIG. 5 shows the end piece 40 of the mounting tool 50 according to the invention, which is complementary in shape to the heel 26 of one of the blades 10, and can be used to drive the heel 26 in a radial direction. To allow a good grip of the heel 26 when the blades are arranged as in Figures 3 and 4, the tip 40 is provided to engage the outside of the heel 26. The tip comes to marry by the outside the shape of the heel with a small clearance, so that any rotation of the tip 40 around the radial direction causes, by contact reaction with the parts engaged with the heel 26, the rotation of the heel. It will be readily appreciated that the more complete and adjusted the shape cooperation between the end piece and the heel, the more the contact reaction will be distributed over the whole of the heel 26, which avoids excessive concentrations of mechanical stresses. For this purpose, according to the example shown in FIG. 5, which is relative to the type of blade introduced in FIG. 1, the endpiece has an internal face 42 which rests on the external face of the heel 26. and downstream of the nozzle are flanges 44 inwardly forming, face to face, two shoulders upstream and downstream substantially perpendicular to the inner face 42 of the nozzle. Its shoulders are spaced so as to abut against the upstream and downstream ends of the upstream and downstream spoilers 34 of the heel 26, when the mounting tool is engaged.
    [0009] In addition, the inner face 42 of the tip 40 comprises between the two shoulders 44, at least one slot 46, generally two slots 46, extending circumferentially in the tip and oriented substantially parallel to the shoulders, the or each slot having a complementary shape and fitted to each of the wipers 30 of the heel, which are introduced when the mounting tool is engaged.
    [0010] In Figure 6, we see that the tip 40 can be connected to gripping means 48, such as a conventional handle. This connection is removable in order to retain the same gripping means 48 for different types of tips 40 which correspond to other types of blades 10 than those given in example. It can be clearly seen in FIG. 6 that the mounting tool engages outside the blade 10, and leaves the circumferential edges of the heel 26 free while engaging the upstream and downstream edges of the heel 26. FIG. 7 shows how the mounting tool 50 is used to engage the blades 10 in the cavities 18 of the disc 12. While the engagement direction 52 of the blade roots 14 in the cells 18 is slightly inclined relative to at the axis 16 of the disc, as the circumferential edges of the inner platforms 22 of the blades 10, we see that the outer platforms 28 of the heels 26 of the blades have their circumferential rims aligned and supported on each other in the strictly axial direction. This difference in inclination means that it is in the natural state impossible to engage the blades 10 in the cells 18 without the heels 26 of the blades interfere with the movement. With the mounting tool 50 described above, the bead 26 is rotated (see arrow 54) by elastic deformation around the radial direction so that the circumferential edges of the external platforms 28 line up with each other. the direction 52 of engagement of the feet 14 in the cells 18. Once the heel reoriented, it can slide the blade 10 in the cell 18 without particular discomfort of the adjacent blades. We can repeat this manipulation for each blade to mount all the blades on the disc.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A method of mounting blades (10) at the periphery of a turbomachine disk (12) relative to the axis (16) of rotation of the disk, the disk (12) comprising, at its radially outer periphery, cavities ( 18) extending substantially parallel to the axis of the disc and arranged alternately with teeth (38) of the disc, the blades (10) comprising respectively: - at a first radially inner end of the feet (14) to be inserted into the cavities (18) of the disk, - at a second radially outer end of the beads (26), and - blades (24) connecting the feet to the beads, the method comprising the steps of: (a) positioning the blades (10); ) in circumferential alignment so that the foot (14) of each blade is axially facing one of the cavities (18) of the disk, (b) providing a mounting tool (50) comprising a tip (40) of partially complementary shape to the heel (26) of one of the vanes, (c) making the endpiece cooperate (40) of the mounting tool (50) with the blade root (26), (d) pivoting the blade root (26) by a rotational movement (54) of the blade tool (50). mounting (50) about a radial direction of the disc passing through the blade, and (e) axially inserting the root (14) of the blade into the cell (18) of the disc.
    [0002]
    2. A method of blade assembly according to claim 1, characterized in that at the end of step (a), the heels (26) of the blades (10) are in circumferential supports on each other according to flanges oriented in a direction different from that in which the feet (14) of the blades are oriented. 302 3 5 81 10
    [0003]
    3. A method of blade assembly according to one of claims 1 or 2, characterized in that it involves as many blades (10) to mount on the disk (12) that of cavities (18) of the disk, and in that steps (b), (c), (d) and (e) are successively repeated for all the blades. 5
    [0004]
    4. A method of blade assembly according to claim 3, characterized in that all the blades (10) are of identical shapes, and in that one and the same mounting tool (50) is used during the repetition of steps (b), (c), (d) and (e).
    [0005]
    5. A method of blade assembly according to one of the preceding claims, characterized in that prior to step (a), is mounted a foil (36) around the foot (14) of the dawn, the foil being inserted with the foot (14) of the blade into the cell (18) during step (e).
    [0006]
    6. A blade mounting method according to one of the preceding claims, characterized in that the mounting tool (50) comprises gripping means (48) such as a handle.
    [0007]
    7. A method of blade assembly according to claim 6, characterized in that the gripping means (48) and the tip (40) of the mounting tool (50) are removable relative to the other.
    [0008]
    8. A method of blade assembly according to one of the preceding claims, characterized in that the tip (40) of the mounting tool (50) comprises two axial stops (44) between which are adjusted with a low play the axial ends (34) of the heel (26) during step (c).
    [0009]
    9. A method of blade assembly according to one of the preceding claims, characterized in that the tip (40) of the mounting tool (50) comprises at least one slot (46) in which is adjusted with a weak play at least one wiper (30) of the heel (26) of the blade during step (c).
    [0010]
    10. A blade mounting tool (50) for mounting vanes (10) at the periphery of a turbomachine disk (12) according to one of claims 1 to 9, comprising a tip (40) shaped in partcomplémentaire the heel (26) of a blade, so as to be able to rotate the heel and the mounting tool.
    [0011]
    11. mounting tool (50) according to claim 10, characterized in that the tip (40) comprises a face (42) from which extend two opposite shoulders (44), said face further comprising between the two shoulders at least one slot (46) oriented substantially parallel to the shoulders.
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    同族专利:
    公开号 | 公开日
    EP3167162B1|2018-09-12|
    EP3167162A1|2017-05-17|
    CN106471217B|2019-03-15|
    US10787919B2|2020-09-29|
    RU2017101545A|2018-08-08|
    CN106471217A|2017-03-01|
    FR3023581B1|2016-07-15|
    WO2016005687A1|2016-01-14|
    BR112017000302A2|2017-11-07|
    US20170145841A1|2017-05-25|
    RU2017101545A3|2019-01-25|
    RU2701925C2|2019-10-02|
    CA2954105A1|2016-01-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20020085917A1|2000-12-28|2002-07-04|Roberts Dennis William|System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets|
    EP1955805A1|2007-02-08|2008-08-13|United Technologies Corporation|Bladed disk assembly method and impact device|
    EP2460980A2|2010-10-16|2012-06-06|MTU Aero Engines AG|Method for producing an integrated bladed rotor|
    SU1009689A1|1981-07-17|1983-04-07|Lavrov Vladimir V|Method of assembling blades with disk|
    GB0406889D0|2004-03-26|2004-04-28|Alstom Technology Ltd|Turbine and turbine blade|
    EP1916389A1|2006-10-26|2008-04-30|Siemens Aktiengesellschaft|Turbine blade assembly|
    US20120034086A1|2010-08-04|2012-02-09|General Electric Company|Swing axial entry dovetail for steam turbine buckets|EP3156603A1|2015-10-13|2017-04-19|Siemens Aktiengesellschaft|Assembling aid for assembling/de-assembling blades on a disk|
    US10883386B2|2017-06-21|2021-01-05|Mitsubishi Hitachi Power Systems Americas, Inc.|Methods and devices for turbine blade installation alignment|
    US10830756B2|2017-09-22|2020-11-10|Applied Materials, Inc.|Method to create a free-standing membrane for biological applications|
    US11084150B2|2018-01-31|2021-08-10|Raytheon Technologies Corporation|Wear liner installation tool|
    DE102019215220A1|2019-10-02|2021-04-08|MTU Aero Engines AG|System with a rotor blade for a gas turbine with a blade root guard plate having a sealing section|
    法律状态:
    2015-08-07| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-15| PLSC| Search report ready|Effective date: 20160115 |
    2016-07-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-28| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 6 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 7 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1456554A|FR3023581B1|2014-07-08|2014-07-08|MOUNTING AUBES IN PERIPHERY OF A TURBOMACHINE DISK|FR1456554A| FR3023581B1|2014-07-08|2014-07-08|MOUNTING AUBES IN PERIPHERY OF A TURBOMACHINE DISK|
    PCT/FR2015/051840| WO2016005687A1|2014-07-08|2015-07-02|Mounting of vanes in the periphery of a turbine engine disc|
    CA2954105A| CA2954105A1|2014-07-08|2015-07-02|Mounting of vanes in the periphery of a turbine engine disc|
    CN201580036951.7A| CN106471217B|2014-07-08|2015-07-02|In the installation method of turbine engine disk periphery blade|
    BR112017000302A| BR112017000302A2|2014-07-08|2015-07-02|reed assembly method and reed assembly tool|
    US15/323,902| US10787919B2|2014-07-08|2015-07-02|Mounting of vanes at the periphery of a turbine engine disc|
    RU2017101545A| RU2701925C2|2014-07-08|2015-07-02|Method of installing blades on periphery of disc of turbine engine and tool for mounting blade|
    EP15748279.5A| EP3167162B1|2014-07-08|2015-07-02|Mounting of vanes in the periphery of a turbine engine disc|
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