• 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 rotor blade for a turbomachine, comprising a body (170) locally defining a blade provided at a radially outer end of a heel (33), characterized in that it further comprises at least one element of seal (39) extending beyond the radially outer end of the bead and bonded with a bead area by a movable mechanical connection (37).
    公开号:FR3027622A1
    申请号:FR1460356
    申请日:2014-10-28
    公开日:2016-04-29
    发明作者:Didier Noel Durand；Olivier Jean Daniel Baumas；Nicolas Daniel Delaporte
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to a rotor blade for an aerospace turbomachine, a rotating assembly for a turbomachine comprising a series of such blades, a method of operating a rotorcraft, and a method for operating the rotorcraft. such a rotating assembly, as well as a method of making the blade. The preferred turbomachine is an airplane turbojet engine. EP0708227 illustrates a state of the art closest and poses the various possible problems relating to the sealing of the turbomachine rotor blades. Thus, to ensure maximum performance in aeronautical turbomachines, it is essential to minimize gas leakage between numbers of fixed elements and rotary elements of these turbomachines. In the present specification, as in the technical field concerned, the upstream AM and downstream AV terms are defined so that the upstream is located axially on the side from which the general flow flow of the turbomachine originates, and the downstream is located axially on the side towards which this same flow flows. And the terms "inside" and "outside" are defined radially with respect to the axis about which the aforementioned rotating elements (axis 7 below) rotate, "axial" and "radial" being defined with respect to this same axis 7 Schematically, along the aforesaid axis and from upstream to downstream, an aircraft engine turbine engine often comprises a blower, a low pressure compressor, a high pressure compressor, a combustion chamber and then turbines. , successively high pressure and low pressure. In particular the turbines each comprise a fixed part, or stator, carrying blades held by their fixed ends on a housing, and a rotating portion about a longitudinal central axis, defining a rotor also provided with vanes. Thus, as known, the low-pressure turbine 1 of a turbojet engine or turboprop engine of FIG. 1 comprises a plurality of turbine wheels 3 which are arranged in series inside an outer casing 5 and revolve around a central axis 7 of the turbomachine, downstream of a fixed annular distributor 9 provided with a series of blades. In practice, the dispenser comprises a wheel with a plurality of distributor sectors. Each wheel 3 comprises a disk 11 carrying outer blades 13 at its outer periphery. In the example shown, the low-pressure turbine comprises four disks 11 whose blades are of progressively increasing length from upstream to downstream relative to in the flow direction of the gases leaving the combustion chamber 15 of the upstream turbine engine. As can be seen better in FIG. 2, which also illustrates the prior art, each disk 11 comprises, at its outer periphery, teeth 23 arranged alternately with grooves, or cells, in which are engaged axially and retained radially blade roots. 26, the 20 vanes extending radially from the cells 25 in an annular flow vein 27 of a stream of hot gas from the upstream combustion chamber 15. More precisely, each blade body 17 has radially, since the outside to the inside, a blade 19, a platform 29 extending substantially perpendicular to the axis 31 of elongation of the blade, and a stilt 31 connecting the platform to the foot of 26. These blade roots may have a dovetail or similar shape to ensure their radial retention in the cells 25. The platforms 29 of the blades 13 are arranged circumferentially end-to-end so as to define together the li internal reference moth of the flow flow of hot gases flowing in the turbine.
    [0002] As previously disclosed in EP0708227, each blade 13 may be made of composite material and thus be made of a fiber fabric impregnated with a resin and defining base fibers of the composite material. In the material, additional fibers are present, one portion of which extends beyond the blade. The portion of these fibers which is outside the blade constitutes a brush (or brush seal) 21. As seen in FIGS. 2 and 3, each rotor blade 13 thus comprises a body 17 defining locally a blade 19 whose free end has a brush seal 21, so that when the blade 6 is rotating, the brush 21 rubs on the track of the housing 5, which housing defines a fixed circumferential envelope, in one or more parts, around blades. As there are several types of seals on the blade side, there are several types of fixed seals. In the illustrations, one of them, positioned on the fixed elements of the turbomachine (on the housings or the stators) in line with the rotating elements (rotor or blade), is made of an abradable material, typically with honeycomb structures, for example of honeycomb type.
    [0003] Thus, to promote sealing as shown schematically in FIG. 3, a series of blocks 22 of abradable material fixed internally to the casing 5 can radially face the brush joints 21, beyond their outer periphery. In practice, the blocks 22 are angular sectors. The invention presented here is an alternative in particular to such a known brush solution that can be difficult to implement industrially, especially since, in the particular case of low pressure turbines, thermal stresses are sources of additional difficulties. . Indeed, there is the problem of the temperature resistance of brushes whose materials are problematic to choose.
    [0004] The problem of predicting wear between the two parts in contact and maintenance has also been taken into account.
    [0005] Thus, with on one side the abradable material 22, on the other hand the brushes 21, it can be difficult to manage the balance of wear, therefore the quality of the seal, over time, since under the the action of the centrifugal and axial forces exerted on the blades and because of the expansion of the materials as a function of the ambient temperature, the friction of the blade on the abradable seal can deteriorate this seal, because of the constitution relatively fragile of this abradable material. Thus, when the speed of rotation of the blades decreases, the forces and the temperature also decrease, resulting between the fixed and rotary elements concerned a leakage flow if the area of the seal is deteriorated. An object of the invention presented here is to provide a solution to this and to avoid the disadvantages of the prior art. It is therefore proposed that the rotor blade concerned, which comprises a body which locally defines a blade having at one radially outer end a blade head, further comprises at least one seal element connected with a zone. the blade head by a movable mechanical connection between a rest position and an active position in which the seal member is radially projecting from the blade head, the movable mechanical linkage comprising a hinge. In fact, such a "mobile attachment" will be provided so that the free end of the outer seal member can move more or less away from the blade head, preferably radially outward. Thus, the seal member may escape in case of excessive radial force, thus avoiding both inappropriate wear of the material against which it comes otherwise wear and / or damage to the joint member itself. That in particular the mobile mechanical connection comprises a pivot connection, preferably free, allow a "self-adaptation" that the blade is rotated about the axis 7, or at rest.
    [0006] To facilitate and secure the realization of such a blade, it is recommended that the blade head defines a heel, this heel being integrated with the manufacturing blade, or reported and attached to it. In known manner, a heel is a kind of small platform that forms a flange around the outer end of the blade. Typically, placed side by side circumferentially around all the vanes fixed by their feet to the central disc which drives these vanes, the heels together define an outer limit for the vein of gaseous flow that passes between the blades. Again to promote the control of wear between the two parts in contact and therefore the maintenance, it is also advisable that the movable joint element is made of composite material. Structurally, it is furthermore recommended that for said movable mechanical connection: - the joint element has a base and the blade head a protuberance, - and one of the base and the protuberance defines a concave bowl in which will be engaged an externally convex form of the other among the outgrowth and the base. Thus, we will ensure both retention in translation and articulation. And, to facilitate the one-piece and solid realization of the base of the seal member, it is advised that it has an outwardly convex shape then movably engaged in a concave cup of the blade head. Again structurally, it will furthermore be preferred that said concave cup has an opening where the externally convex shape will be engaged, the edges of the opening defining stops for the mobility of the outer seal member with respect to the blade head. . As regards the turbomachine rotating assembly also concerned here, it is recommended that it comprises: a rotor disk rotatably mounted about the longitudinal axis of the motor 30 and possibly having grooves at the outer periphery; rotor blades of the type mentioned above each fixed to the rotor disk, for example received respectively in the grooves of this disk, and a fixed casing provided with contact blocks, for example abradable material, surrounding the seal elements of blades, these elements being movable relative to the contact blocks, without necessarily bending. In accordance with the desired joint member / blade head mobility, it is furthermore provided that, on each rotor blade, the or each gasket element is preferably movable relative to the blade head at least substantially along an axis. transverse to the axis around which the rotor disc is rotatably mounted. As regards the method of operation of this rotary assembly to which another aspect of the invention also relates, it is favorably provided that said movable joint elements all come into contact with the contact blocks, only from a predetermined speed of rotation. blades. Moreover, in addition or not to this, it will be favorably provided that said movable joint elements incline, without necessarily flexing, in a variable manner with respect to the contact blocks, - depending on at least one of the speed of rotation of the blades, the temperature of at least one of said blades, and the cooling of the casing to which the blocks are internally fixed, and / or depending on the wear of the abradable material, which will be less hard than that of the joint elements.
    [0007] As for the manner of producing a rotor blade of the aforementioned type, it is advisable in the present application: to realize this rotor blade, by orienting the concave bowl transversely with respect to a longitudinal axis of the blade, to realize apart from each seal member, - then to engage together, by sliding, the concave bowl and the outwardly convex shape.
    [0008] This sliding will be favorably free, so that the retention for the final blocking will preferably be obtained by abutment against the adjacent blades. The invention will possibly be better understood and other details, characteristics and advantages of the present invention will appear even more clearly on reading the following description, given by way of non-limiting example and with reference to the accompanying drawings, in which: which: - Figures 1,2,3 relating to the prior art are respectively a schematic half axial sectional view of a low pressure turbine, a perspective view of blades engaged, each with their fixed lower end, in the cells of one of the rotor disks and a front view of a brush seal presented in EP0708227; - Figure 4 is a partial schematic axial section of the top of a blade according to the invention, with the opposite part of the fixed casing of a low pressure turbine then at rest; - Figure 5 is a partial schematic perspective of the same area as that of Figure 4, rotating turbine; FIGS. 6, 7 are two other views identical to FIG. 4, but with the turbine rotating respectively at intermediate speed and at the highest speed; and FIG. 8 is an alternative embodiment of mobile mechanical connection of the heel solution. According to the invention, and as explained above, the solution here exposed therefore passes by replacing the brush seal of the embodiment of FIGS. 1.3 by another solution which in particular does not require the production of the blades each made of material composite of the type of that of EP0708227. Figure 4 and following schematize possible embodiments of such a solution. The elements identical to those of the preceding figures are identically referenced, while the still existing but modified parts of the blades are an incremented reference of one hundred. Thus, the blades 13 become 130, which can take the place of the first in Figure 1 and each be designed as shown schematically in Figure 2, for their inner part.
    [0009] In addition to being metallic, for example forged or molded, each rotor blade 130, which naturally rotates about the axis 7, comprises a body 170 locally defining a blade 190 provided at one radially outer end of a head blade 33, that is to say an end portion adapted to be provided (in one piece or reported) of at least one seal member 39. Preferably, each blade head 33 will be defined by or will include a heel 330 which can be seen as an illustration in particular in Figure 5. It is therefore a small platform which defines a flange at the radially outer end of the blade considered. Conventionally, all of these heels 330 form a ring around the radiating vanes 190 and externally channel the annular flow vein 27. In the following description, it has been considered, in connection with the embodiment illustrated in FIGS. 4-7 and without limitation, that such a heel is present on each blade. Thus, beyond the radially outer end of its heel, each vane 130 comprises at least one, here two, sealing member (s), said joint members 39 extending so that the free end of outer seal member considered can move more or less away from the heel, radially outward, as can be seen by comparing Figures 4,6,7. More precisely, this capacity is here ensured by at least one, here two, mechanical link (s) movable (s) 37 established between at least one, here two, zone (s) 35 of the heel and the element or elements (s) seal 39.
    [0010] Thus, by position variation, in particular radial, of the seal member (s) 39 via their (their) mechanical link (s) movable (s) 37, it will be possible to adapt the peripheral sealing between each heel 330 and the casing track, or envelope, opposite, defined in the preferred example by the block considered abradable material 22. The problem of the prediction of wear between the two parts in contact and of the maintenance will be even less present if, as illustrated, each movable mechanical connection 37 comprises an articulation allowing, by pivoting, a retraction of the seal member 39 concerned, in case of excessive effort. In the preferred embodiment of Figures 4-6, each movable mechanical connection 37 comprises in fact a pivot connection, each rotatably mounted about an axis, respectively 41a, 41b, substantially transverse to the axis 7.
    [0011] Furthermore, in order to structurally realize the or each mobile mechanical connection, it is in particular proposed, as shown diagrammatically in FIGS. 6 and 8: - that the seal member 39 has a base 39a and the heel 330 has a protrusion 33a, on its external face 33b and that one of the base and the protuberance defines a concave bowl 43 in which is engaged an externally convex shape 45 of the other of the outgrowth and the base. However, again for good mechanical strength and ease of manufacture and maintenance, it is recommended that each seal member 39 instead has, as in the embodiments of Figures 4-7, a base 39a of externally convex shape engaged with movably in a concave bowl 43 of the heel 330. Radially outwardly, each base 39a is preferably extended by a blade-shaped portion 39b adapted to come at its free end supported by a sector of a circle against the face 22a next to the track that adjoins it, and which belongs in the preferred example to block 22 concerned. To promote articulation movements, or more generally for the mobility of the outer seal member 39 relative to the heel 330, it will be preferred that the corresponding concave cup 43 has an opening 47 in which is engaged the externally convex shape 45 provided . And to limit the amplitude of the movements for purposes including security and reliability, it will be preferred that the edges of each opening 47 laterally define stops, such as 49a, 49b Figure 6 end of 10 stroke of the element external seal 39 relative to the heel 330. As illustrated in Figures 4-6, each heel 330 of rotor blade 130 will preferably comprise two outer seal members 39, one upstream the other downstream, thus forming a double obstacle . In order to combine lightness, mechanical strength, ease of manufacture and maintenance, it is furthermore recommended that each seal member 39 be of composite material, such as ceramic matrix composite, CMC. Such a choice seems a good compromise, since this material will withstand the high temperature of the area and will limit the phenomena of wear during contact with the stator, because of its lower density compared to that of identical metal parts. In particular, such a solution will make it possible, unlike the aforementioned brush solution 21 of the prior art, for the seal elements 39 to be movable relative to the blocks 22 of abradable material, without necessarily having to bend, the aforementioned mobility avoiding having to to bend. Comparing the same FIGS. 4 to 7, it may further be noted that the seal members 39 will all come into contact with the blocks of abradable material only from a predetermined speed of rotation of the blades. Indeed, at rest as Figure 4, the seal members 39 illustrated 30 are, by gravity, in abutment against one of their abutments 49a, 49b.
    [0012] Preferably, this stop will be the upstream stop 49a, the less radially outer of the two and placed so that the corresponding seal member 39 is then, at rest dawn, oriented (with its blade 39b) substantially parallel to the axis 7.
    [0013] On the other hand, with the rotor rotating, the corresponding seal member 39 rises more radially as shown in FIGS. The downstream abutment 49b may also be located so that the corresponding seal member 39 can not go beyond the radial direction 51, so that it always prevents the flow of upstream gas to the outside. downstream in this zone, rotating rotor. In the context of this operation, it is moreover provided that, preferably, said movable joint members 39 incline relative to the body 170, and in particular to the heel 330 concerned, again without necessarily bending, and especially to variable with respect to the blocks 22 of abradable material considered, as a function of the speed of rotation of the blades 130. In this regard, FIGS. 5,6 show that, with respect to the rest position of FIG. mobile joints 39, while in the active position position, are more inclined outwards and radial axis 51 when the turbine rotates at an intermediate speed (FIG. 6) than when it rotates at a higher speed (FIG. 7), and in particular at full speed nominal speed (the sealing blocks 22 being assumed in good condition). This is due to the differential expansions that occur and to the radial reconciliation which then takes place between the beads 33 and the sealing blocks 22. It should also be noted that the distance separating the blade heads and the corresponding abradable ring, defined by the circumferential assembly of the blocks 22, will depend on the speed of rotation of the blades, but also other operating conditions such as the power demanded from the engine, via a more or less fuel injection, and / or time spent at high load and / or at high rotational speed of the turbine. In general, this distance varies according to the engine speed, the thermal reaction of the blade as well as the cooling of the outer skin of the turbine casing 5. Thus, the distance above is shorter in FIG. 7 than in FIG. 6 and accordingly the movable joint elements 39 are more inclined towards the radial direction 51 FIG. 6 than FIG. 7. It is also expected that the same elements Mobile joints 39 will incline, again without necessarily flexing, variably with respect to the sealing blocks 22, depending on the wear of the abradable material. Therefore, a downstream abutment 49b located so that the corresponding seal member 39 can not go beyond the radial direction 51 will be of interest. As an alternative to the embodiment of FIGS. 4-7, FIG. 8 shows a solution (not preferred) where: the seal member 39 has a base 39a and the heel 330 has a protuberance 33a, on its external face 33b, and the base defines a concave bowl 43 in which is engaged the externally convex shape 45 of the protuberance 33a of the heel. Although less safe guiding, this solution is possible.
    [0014] Regarding now the mounting of articulated seal members 39, it will be effected, in particular for the illustrated pivot connection, by sliding (axis 41a, 41b) with fitting of each joint member, respecting the slight clearance necessary pivoting (preferably free pivoting), as in the case of a dovetail assembly. The restraint for sliding blocking will preferably be made by abutments of the considered seal element against the adjacent blades, as understood in view of FIG. 5. As for the abradable that can be understood each contact block 22, it will preferably be made of a material that is less hard than the material of the seal elements 39. The latter may be made of a ceramic matrix composite, CMC, with the same advantages as those mentioned above.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Rotor blade for a turbomachine, comprising a body (170) locally defining a blade having at one radially outer end a blade head (33,330), characterized in that it further comprises at least one seal element ( 39) connected with a zone of the blade head (33,330) by a mechanical connection (37) movable between a rest position and an active position in which the seal element (39) projects radially from the blade head ( 33,330), the movable mechanical connection (37) comprising a hinge.
    [0002]
    The rotor blade of claim 1, wherein the blade head (33,330) defines a bead (330).
    [0003]
    The rotor blade according to claim 1 or 2, wherein the movable mechanical connection (37) comprises a pivot connection.
    [0004]
    4. rotor blade according to one of claims 1 to 3, wherein, for the movable mechanical connection: - the seal member (39) has a base (39a) and the blade head (33,330) a protrusion ( 33a), and one of the base and the protuberance defines a concave bowl (43) in which is engaged an outwardly convex shape (45) of the other of the outgrowth and the base.
    [0005]
    5. rotor blade according to one of claims 1 to 4, wherein the seal member (39) has a base (39a) of externally convex shape movably engaged in a concave bowl (43) of the head of pale (33,330) .30
    [0006]
    6. rotor blade according to one of claims 4 or 5, wherein said concave bowl (43) has an opening (47) which is engaged the externally convex shape, the edges of the opening defining stops (49a, 49b). ) for the mobility of the outer seal member (39) relative to the blade head (33,330).
    [0007]
    7. Rotary assembly for a turbomachine, comprising: - a rotor disc (11) rotatably mounted about an axis (7), - a series of rotor blades (130) according to one of claims 1 to 6, 10 fixed each to the rotor disk, - a stationary housing (5) provided with blocks (22) for contact with the seal elements (39) of the rotor blades which said blocks surround, the sealing elements (39) thus being movable relative to said contact blocks. 15
    [0008]
    8. The assembly of claim 7, wherein, on each rotor blade, the or each seal member (39) is mounted free in motion so that a rotation of the vanes (130) by the rotor disk ( 11) moves the seal member (39) to the active position. 20
    [0009]
    9. A method of operating a rotating assembly for a turbomachine according to claim 7 or 8, wherein: - said movable elements (39) of the rotor blades (130) all come into contact with the blocks (22) contact , only from a predetermined speed of rotation of the blades, and / or said movable joint elements (39) of the rotor blades (130) incline, without necessarily flexing, in a variable manner with respect to the blocks ( 22), depending on the speed of rotation of the blades.
    [0010]
    10. A method of operating a rotating assembly for a turbomachine according to claim 7 or 8, wherein said movable seal members (39) of the rotor blades (130) incline, without necessarily flexing, in a variable manner with respect to to the contact blocks (22) as a function of at least one of the speed of rotation of the blades, the temperature of at least one of said blades, and the cooling of the housing (5) to which the blocks (22) are internally fixed.
    [0011]
    11. A method of producing a rotor blade for a turbomachine according to claim 4 alone or in combination with one of claims 5,6, wherein: - the rotor blade is made (130 ), by orienting the concave cup (43) transversely to a longitudinal axis (31) of the blade, - the seal member (s) (39) is made, and the concave bowl (43) and the outwardly convex shape (45).
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    同族专利:
    公开号 | 公开日
    RU2017112724A|2018-11-29|
    CA2963853A1|2016-05-06|
    US20170335709A1|2017-11-23|
    BR112017008593A2|2018-03-27|
    RU2722241C2|2020-05-28|
    RU2017112724A3|2019-04-29|
    CN107109958B|2020-01-31|
    WO2016066932A1|2016-05-06|
    US10550712B2|2020-02-04|
    EP3212897B1|2018-07-18|
    EP3212897A1|2017-09-06|
    FR3027622B1|2018-11-09|
    CN107109958A|2017-08-29|
    CN107109958B9|2020-04-10|
    引用文献:
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    法律状态:
    2015-10-09| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-29| PLSC| Search report ready|Effective date: 20160429 |
    2016-10-06| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1460356|2014-10-28|
    FR1460356A|FR3027622B1|2014-10-28|2014-10-28|ACTIVE ROTOR ROTOR DRAW, ROTATING ASSEMBLY AND METHOD OF OPERATING THE SAME|FR1460356A| FR3027622B1|2014-10-28|2014-10-28|ACTIVE ROTOR ROTOR DRAW, ROTATING ASSEMBLY AND METHOD OF OPERATING THE SAME|
    CN201580058911.2A| CN107109958B9|2014-10-28|2015-10-22|Rotor blade with active clearance control, rotating assembly and method of operating the same|
    PCT/FR2015/052844| WO2016066932A1|2014-10-28|2015-10-22|Rotor vane with active clearance control, rotary assembly and operating method thereof|
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