• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
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    • 专利摘要:
    The invention relates to a turbomachine wheel, comprising a disc bearing blades whose feet (3a, 3c) are fitted in grooves (6a, 6c) substantially parallel to an axis of revolution of the disc, the foot (3a, 3c). each blade being connected to a blade (4a, 4c) by an integrated platform (5a, 5c), the wheel (1a, 1c) further comprising at least one annular flange (14, 21) fixed to the disk so as to form an axial abutment of the feet (3a, 3c) of the blades, characterized in that said flange comprises, on the one hand, an annular spoiler (16, 23) extending substantially axially on the side opposite the disc and forming an obstacle to a flow radial gas along said flange, and, on the other hand, annular wipers (34, 59) of a labyrinth seal (35, 62).
    公开号:FR3029960A1
    申请号:FR1462268
    申请日:2014-12-11
    公开日:2016-06-17
    发明作者:Antoine Jean-Philippe Beaujard；Michel Gilbert Roland Brault；Nathalie Nowakowski
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION AND STATE OF THE ART The present invention relates to the field of paddle wheels in turbomachines, such as a turboprop engine or a turbojet engine with keeled or unducted propellers, and more particularly turbine wheel impellers. such turbomachines. Some turbomachines may include a low pressure turbine heavily loaded by a very high rotational speed. Conventionally, a paddle wheel comprises a rotor disk, whose outer periphery comprises mounting grooves, in a direction substantially parallel to the axis, and radial retention of blade roots. Each blade is formed with a platform at the interface between a foot and a blade. The blade platforms are arranged circumferentially to delimit the radially inner wall of an annular flow vein of the flow of gas flowing in the turbine. In a conventional manner, a turbine comprises several successive wheels separated by distributor stages for straightening the flow in the vein. These distributors are stator elements which generally also comprise a blade crown which are in particular attached to an inner ferrule which delimits the radially internal wall of the annular vein to the distributor's right. To allow rotation of the wheels, the distributor rings are separated from the platforms of the blades of the wheels by axial and radial play. It is the same between the platforms of the blades and the inner wall of the inlet or outlet vein of the turbine. These spaces, where the wall of the vein is not reconstituted, are passages through which a portion of the flow can escape, and in particular leak from one stage to another of the turbine passing under the distributors.
    [0002] To limit these leaks detrimental to the performance of the turbine, it is known to use blades with spoilers that form baffles to deflect and limit gas leakage. The spoilers extend substantially axially under the vein in the vicinity of the passage left with the adjacent distributor, to reconstruct an annular surface obstructing the passage of gas in the vicinity of the platforms.
    [0003] These spoilers are currently integrated into platforms.
    [0004] 3029960 2 The presence of the spoiler complicates the manufacture of the blades. Indeed, the turbine blades are generally made in one piece, the spoilers being formed with the platforms and the blade roots. The use of composite materials using ceramics (CMC), to withstand high temperatures, poorly accommodates complex shapes and prevents the creation of blades with suitable spoilers. The presence of the spoilers also makes it more difficult to achieve fast rotating turbines by increasing loading and stresses on the blades. In order to remedy these problems of mass and difficulty of realization of the blades, it has already been proposed in the patent application WO-A1-2013 / 072605 to provide an annular spoiler carried by a separate part of the blades. In this case, the annular spoiler is held axially against the blades by a flange which is, moreover, conventionally used for the axial retention of the blade roots. This solution has the advantage of simplifying the manufacture of the blades and alleviate the stresses they suffer. It also allows a relatively simple assembly of the wheel by successive axial assembly of different elements. However, it increases the number of parts to be assembled because it is necessary to provide a specific holding means for the annular spoiler, which complicates the assembly. In addition, the annular spoiler slowed airflow leaks but did not prevent them. Sealing devices, for example labyrinth type radial seals, are generally installed in the radial clearance left between the rotor of the turbine and a distributor to limit a flow of gas that can circulate in the open passage through the axial clearances between the distributors and the two wheels that surround it. The radial joints at the distributor are necessarily offset axially relative to the blades of the wheels and spoilers. In addition, the configuration of the fast turbines can significantly move them away from the vanes of the adjacent wheels. There is a need to simply integrate these devices in mounting the wheels in the turbine. The object of the invention is notably to propose an integrated solution for limiting gas leaks between the stages, particularly in the case of turbomachines rotating at high speed, maintaining the advantages previously mentioned for the use of spoilers, while simplifying the wheel design. Although responding primarily 3029960 3 to the needs of a fast turbine, the invention is applicable also to other turbines and compressors. SUMMARY OF THE INVENTION To this end, the invention relates to a turbomachine wheel, comprising a disc carrying blades whose feet are fitted into grooves substantially parallel to an axis of revolution of the disc, the foot of each blade being connected to a blade by an integrated platform, the wheel further comprising at least one annular flange fixed to the disc so as to form an axial abutment of the blade roots, characterized in that said flange comprises, on the one hand, a spoiler annular extending substantially axially on the side opposite the disk and forming an obstacle to a flow of radial gas along said flange, and, on the other hand, annular wipers of a labyrinth seal. In this design, the flange carrying a spoiler makes it possible to simplify the design of the blades and reduce their inertia because the platforms no longer have to include additional parts restoring spoilers and resistant to corresponding inertial efforts at high speed. In addition, annular flanges make it possible to produce annular spoilers in one piece, and thus to prevent the gas escaping through the radial clearance between the blade platforms and the adjacent rotor from passing between segments that reconstruct a spoiler. . Furthermore, the wipers, cooperating with a complementary element on an adjacent stator, for example abradable attached to an adjacent distributor, to form a radial seal to complete the spoiler to limit leakage by the axial clearance between the blade platforms and the inner wall of the vein on the stator. The body of the flange can thus form the radially inner wall confining a leakage flow between the wheel and the stator over the entire portion of the passage which is located on the side of the wheel with respect to the labyrinth seal. This reduces the number of parts while effectively combating leakage of gas from the vein due to axial play between the wheels and stators. Advantageously, the outer radial end of said flange is substantially aligned axially with an outer annular surface for guiding an air flow of the blade platforms and is optionally axially supported on said platforms.
    [0005] 3029960 4 It is thus possible to reconstruct the continuity of the vein wall at the ends of the platforms. An axial support avoids, unlike a radial support, the flange induces stresses on the platforms at high speeds of rotation. This also makes it possible to limit leakage of the flow between the flange and the platforms. Said flange may extend substantially over the entire radial dimension of the grooves of the disc. This makes it possible to close the passage of gas coming from the vein of the turbine and / or to control the passage of an auxiliary flow of cooling air at the blade roots.
    [0006] Preferably, said flange comprises at least one finger extending substantially axially on the side of the disc, said finger being inserted into a groove for receiving a blade root of the disc or a cavity of the disc, such as a cavity in a disc rim. In particular, said finger can be inserted axially under the root of a blade and is configured to be able to bear radially under this foot. It thus takes advantage of a radial clearance generally existing between the base of the foot and the bottom of the groove, which avoids weakening the disk rim and allows an adaptation of the flange without changing the foot of a blade. Said finger can also be configured to be able to bear radially on at least one rim portion of the disc. This finger is particularly useful in the case where the wipers are remote from the wheel to adapt to the geometry of the turbine and be placed in front of the abradable element of the stator. Indeed in this case the attachment of the flange to the disc is preferably located axially near the wipers to maintain them. The portion of the flange holding the spoiler against the blades is then removed from this attachment. Under the effect of centrifugal forces, the portion of the flange between the blades and the means for fixing to the disk may then deform and cause a detachment of the flange relative to the blades. The radial retention of the flange to the right of the feet, in combination with the effects of the couples induced by the presence of the spoiler during the rotation of the wheel at high speed, makes it possible to facilitate the support of the flange against the feet of the blades on any its height, in the radial direction, even if the foot extends far from the base 3029960 5 of the blade roots. This avoids detachment of the flange at the spoiler and a defect of reconstitution of the wall of the vein in the turbine between the platforms and the radial end of the flange. Preferably, said flange comprises an annular flange, radially internal, fixing to the disc. This flange may be located axially outside the spoiler relative to the disc. This design makes it possible to use the flange to block radially towards the center the passage of the gas from the vein between two successive wheels. Advantageously, the wipers are carried by a portion of the flange forming a connection between the spoiler and said attachment flange. The invention also relates to a turbomachine turbine comprising at least one wheel as described above. The turbine may comprise a distributor adjacent to said wheel and carrying a ring of abradable material configured to cooperate with the wipers of said flange to form a labyrinth seal.
    [0007] BRIEF DESCRIPTION OF THE FIGURES: The present invention will be better understood and other details, features and advantages of the present invention will become more apparent upon reading the description of a non-limiting example which follows, with reference to the accompanying drawings of FIG. which: - Figure 1 schematically shows a longitudinal section of the near part of the radially inner wall of the vein in a turbine according to the invention; FIG. 2 is a perspective view of a part of a disk of a blade wheel according to the invention on which a blade is installed; - Figure 3 shows a longitudinal section of a portion of the first wheel of Figure 1 after a first mounting step; FIG. 4 schematically shows in perspective the detail of an example of festoons for a jaw-connected link; Figure 5 shows a longitudinal section of a portion of the first wheel of Figure 1 after a second mounting step; Figure 6 shows a longitudinal section of a portion of the first wheel of Figure 1 after a third mounting step; - Figure 7 shows a longitudinal section of a portion of the first wheel and the first distributor of Figure 1 after a fourth mounting step; Figure 8 shows a longitudinal section of a portion of the first wheel and the first dispenser of Figure 1 after a fifth assembly step; - Figure 9 shows a longitudinal section of a portion of the second wheel of Figure 1 after a sixth mounting step; FIG. 10 shows a longitudinal section of a portion of the second wheel of FIG. 1 after a seventh assembly step; - Figure 11 shows a longitudinal section of a portion of the first wheel, the first distributor and the second wheel of Figure 1 after an eighth assembly step; FIG. 12 shows a longitudinal section of a portion of the second wheel, the second distributor and the third wheel of FIG. 1 after a twelfth assembly step. DESCRIPTION OF EMBODIMENTS The production of a low pressure turbine as shown in FIG. 1 illustrates various types of flanges carrying annular spoilers on wheels whose blades have simple platforms, allowing, for example, to consider making them in CMC. With reference to FIG. 1, the turbine example comprises three successive impeller wheels 1a, 1b, 1c. Each paddle wheel 1a, 1b, 1c comprises a disc rotating around the axis of the turbine, not shown, and having an outer peripheral rim 2a, 2b, 2c, to which the blades are fixed by their foot 3a, 3b, 3c. In the remainder of the presentation, the concepts of direction or axial dimension, radial and transverse, as well as meridian and transverse planes, are made with reference to this axis of rotation of the turbine. Similarly, the upstream and downstream terms will refer to the direction of flow along this axis of rotation of the gas flow F in the vein of the turbine from the upstream parts of the turbomachine.
    [0008] The blades 4a, 4b, 4c of the blades rotate in the vein and interact with the gas flow F. Each blade comprises a platform 5a, 5b, 5c, between the foot 3a, 3b, 3c and the blade 4a, 4b, 4c . These platforms 5a, 5b, 5c, are shaped to be contiguous circumferentially and constitute the radially inner wall of the flow passage 5 of the gas flow F at the blades 4a, 4b, 4c. Referring to Figure 2, showing a mounting detail on the first wheel for example, it can be seen that the outer rim 2a of the disc has grooves 6a axially passing through the rim 2a. These grooves 6a are evenly distributed around the circumference, they are also the recessed forms of teeth regularly distributed on the rim 2a. The root 3a of a blade may be mounted axially in a groove 6a by its radially inner portion 301, of dovetail or fir-shaped, so as to retain the blade radially on the disk. The feet 3a of the vanes are fitted into the grooves 6a, that is to say that their radially inner portions 301 are engaged with small gaps or with a tight fit in these grooves 6a. Upstream and downstream, this foot 3a stops axially in the transverse plane delimiting the rim 2a of the disk and has bearing surfaces in this plane. Furthermore, this foot 3a comprises a stub 302 at the radial periphery of which is the platform 5a, which is spaced radially from the outer periphery of the disk rim 2a and which is shaped to follow the axial profile of the inner wall 20 the vein of passage of the gaseous flow F. In the example considered, the platforms 5a of the blades of the wheel 1a are contiguous along meridian planes, so as to reconstitute a continuous annular wall of the vein of the gas flow F, to wheel level 1 a. The characteristics presented above for the first wheel 1 with reference to FIG. 2 are valid for the two other wheels 1b, 1c of the turbine. In FIG. 1, it can also be seen that the turbine also comprises two stators 7, 8 serving as distributors for the flow of gas F and placed between two successive wheels 1a-1b, 1b-1c. Each distributor 7, 8 comprises in particular a radially inner shell 9, 10 forming the internal wall of the stream of the gas flow F at the distributor 7, 8.
    [0009] To allow rotation of the wheels, the rings 9, 10 of the distributors have axial play with the platforms 5a, 5b, 5c of the blades of the wheels 1a, 1b, lc adjacent. It is the same between the inner wall 11 of the inlet vein and the platforms 5a of the first wheel 1a, and between the inner wall 12 of the outlet vein and the 5c platforms 5c of the third wheel 3a . These spaces are openings which can potentially pass between successive stages of the turbomachine of the leakage flows of the main flow F, such as the flow f represented by an arrow in broken lines in FIG. 1, going from the first wheel 1a to the second wheel lb passing under the first distributor 7.
    [0010] According to one aspect of the invention, on the first wheel 1 a starting from the upstream, for example, each blade mounted axially by its foot 3a in the grooves 6a of the disk rim 2a is locked axially upstream. by an annular flange 13 of a first type and axially downstream by an annular flange 14 of a second type, each of the flanges 13, 14 carrying an annular spoiler 15, 16.
    [0011] The upstream annular flange 13 of the first type has essentially the shape of a transverse flat ring, one face of which is pressed against the rim 2a of the disc. The spoiler 15 extends from the flange 13 at the axial clearance between the inner wall 11 of the upstream duct and the platforms 5a of the blades, so as to reduce the passage section and limit the leakage rate. Similarly, the spoiler 16 extends axially downstream from a transverse annular portion 32 of the downstream flange 14, pressed against the downstream transverse face of the rim 2a and the feet 3a of the blades. This spoiler 16 extends here under the platform 9 of the first distributor 7. In this way, it creates a baffle effect to reduce the leakage flow f. Unlike the prior art, these spoilers 15, 16 are not formed from the blades. The platforms 5a can therefore stop axially to the right of the blade feet 3a, they are therefore less complex and less massive. In addition, the spoilers 15, 16 being connected to the annular flanges 13, 14, they can be formed in one piece with these flanges 13, 14; whereas, in the prior art, each blade has a spoiler element whose association forms the annular spoiler. This therefore represents an additional simplification.
    [0012] In FIG. 1, it can be seen that the three wheels 1a, 1b, 1c of the turbine presented comprise upstream flanges 13, 17, 21 and independent end plates 14, 18, 22, respectively carrying spoilers 15, 19, 23 extending upstream and spoilers 16, 20, 24 extending downstream. These spoilers and flanges have different shapes depending on their situation in the turbine. The upstream flange 13, 17, 21 and the downstream flange 14, 18, 22 of each wheel 1a, 1b, 1c are independent because they are fixed on each side of the wheel, by different means and can therefore be mounted or disassembled independently. In addition, the function of axial stop in a given direction of one of the flanges is independent of the presence or not of the other flange.
    [0013] It is proposed below to present the different combinations of flanges and wheels, as well as their properties, by following the steps of mounting a turbine as shown in Figure 1. A first step is to mount the upstream flange 13 of the first wheel 1 to 15 thereon. With reference to FIG. 3, the upstream flange 13, of a first type, has essentially the shape of a transverse flat ring. It is fixed to the disc by a dog-type connection 25 on the rim 2a, in the transverse plane defining the rim 2a upstream and radially under the grooves 6a for receiving the feet 3a of the blades.
    [0014] In order to provide the dog-like connection 25, for example, the inner periphery of the flange 13 is scalloped, that is to say that it comprises a ring of teeth extending radially inwards with a given pitch. FIG. 4 schematically illustrates this principle by showing a series of slots falling on the flange 13 and, in a complementary manner, a ring of teeth extending radially outwardly, with the same pitch and with the same radial extension, integral with the Rim 2a of the disc and separated the latter by a groove having the width of the flange 13. The shapes and proportions of the teeth and the throat are parameters adapted by those skilled in the art. To assemble the flange 13 to the rim 2a, it is necessary to pass axially the teeth of the flange 13 between those of the rim 2a to install them in the groove, then turn half a step.
    [0015] As the flange 13 is annular, it suffices to circumferentially block it so that it is fixed to the rim 2a of the disc. For this purpose, the flange 13 comprises a few fingers 26, preferably at least three, which extend radially from its face facing the rim 2a, at the grooves 6a of the rim 2a.
    [0016] Such a finger 26 is shown in FIG. 3, when the flange 13 is mounted on the disk and the jaw link 25 has been axially locked. This finger 26 is then inserted into a cavity 27 of the rim 2a. Such a cavity 27 is diagrammatically shown in FIG. 2. This cavity 27 is here cut into a side wall of a groove 6a, which is also the wall of a tooth between two adjacent grooves 6a. The finger 26 is pressed against the side wall of the cavity 27. Furthermore, the width of the finger 26 is substantially equal to the circumferential extension of the cavity 27, so that the finger 26 is flush with the surface of the groove 6a . Advantageously, when there are, for example, three fingers 26 distributed circumferentially, positioning these three fingers 26 in complementary cavities 27 on the rim 2a makes it possible to block the flange 13 radially. In particular, if there is a radial clearance between the groove of the link clutch on the rim 2a and the flange 13, this allows to center the flange 13 relative to the wheel. Preferably, the finger or fingers 26 are in radial abutment on one of the faces of the corresponding cavity 27 when they are in place.
    [0017] It goes without saying that, in the example under consideration, the pitch of the tooth crowns of the interconnected connection 25, as well as the dimensions of the finger 26, are arranged in such a way that the finger 26 passes through the groove 6a when the flange 13 is inserted axially into the jaw-connected connection 25 before the flange 13 is rotated to lock it axially.
    [0018] In a second step, with reference to FIG. 5, the feet 3a of each blade of the first wheel Ia are then inserted axially downstream into the grooves 6a of the rim 2a of the disc. As can be seen in this figure, the finger 26 shown in the previous figure passes the foot 3a until it is stopped upstream by the downstream transverse face of the flange 13. In this position, the finger 26 is blocked circumferentially by the foot 3a. The flange 13 is completely blocked by 3029960 11 compared to the disk of the wheel 1a. The circumferential forces being limited, it suffices from a few fingers 26 of this type to effectively lock the flange 13. It will be noted that this assembly does not require to adapt the shape of the feet 3a of the blades. It allows to use a single piece type for the blades of the first wheel 5 1 a. Referring to Figure 5, it is also noted that the flange 13 extends radially over the entire height or radial dimension of the feet 3a of the blades. The flange 13 also bears axially against a portion of the rim 2a which is radially inside the feet 3a, and against the radial end of the platforms 5a of the blades. Here, the radial end of the flange 13 is shaped to follow in axial continuity the outer surface of the platforms 5a of the blades. The flange 13 and the platforms 5a here are joined with axial support. The flange 13 has no radial support on the platforms 5a or on the feet 3a. It does not induce centrifugal force during the rotation of the turbine.
    [0019] The transverse ring formed by the flange 13 can here completely cover the grooves 6a for receiving the feet 3a of the blades. On the other hand, it can axially close the annular space between the platforms 5a of the blades and the rim 2a of the disc. This configuration makes it possible to guide the flow F in the vein along the platforms 5a by minimizing the pressure drops and / or the formation of leakage flows under the platforms 5a. The annular spoiler 15, extending axially upstream, is disposed here on the upstream flange 13 near the platforms 5a. With reference to FIG. 1, the surface of the flow vein flowing in the turbine is diverging radially at the level of the first wheel 1a. The spoiler 15 is here configured to arrive near the surface 25 of the incoming vein 11 while remaining radially under the surface of this vein 11. In a third step, the downstream flange 14 is mounted axially downstream. the first wheel 1 a. With reference to FIG. 6, it will firstly be noted that the first wheel 1 has an assembly ring 28 radially inside the rim 2a and spaced axially downstream. This ring 28, which serves for assembly with the second wheel 2a, is secured to the disc 3029960 12 through, here, a substantially cylindrical portion integral with the rim 2a. This ring has a plurality of axial orifices 29 distributed circumferentially and intended to let a nut. The downstream flange 14, of a second type with respect to the upstream flange 13, comprises: an annular, transverse and radially inwardly extending fixing flange 30, which is pierced by axial holes 31 distributed circumferentially and correspondingly at the axial orifices 29 of the assembly ring 28 of the first wheel 1 a; a transverse annular portion 32 for stopping the feet 3a of the blades 10 and carrying the spoiler 16 which extends axially downstream; and an intermediate portion 33, here of substantially cylindrical shape, which carries wipers 34 intended to participate in a radial labyrinth seal 35, indicated in FIG. 1. The mounting of the downstream flange 14 takes place here axially, in the wedge 15 circumferentially so that the holes 31 of the fastening flange 30 of the flange 14 are opposite the orifices 29 of the assembly ring 28 of the first wheel 1 a. The transverse annular portion 32 supporting the spoiler 14 extends here substantially to the platform 5a of the blades. It bears axially on the downstream transverse face of the rim 2a and on the feet 3a.
    [0020] In addition, at least one finger 36, preferably several regularly distributed on the circumference, extends axially upstream of the transverse annular portion 32. Such a finger 36 is shown in Figure 6. It is preferably located near the radially inner edge of the transverse annular portion 32 pressing on the blade roots. It is arranged to be inserted into a cavity of the rim 2a when the flange 14 is pressed against the first wheel 1a and the holes 31 of its fastening flange 30 are in correspondence of the orifices 29 of the ring. assembly 28. Preferably, as shown in Figure 6, the finger 36 is inserted into a mounting groove 6a, under the foot 3a of a blade. In this position, each finger 36 can come into radial abutment against the base of a root 3a of a blade when the wheel 1a is in rotation, thus blocking radially the flange 14 at the base of the feet 3a of blades. Incidentally, these fingers 36, being circumferentially locked in the corresponding grooves 6a, make it possible to maintain the holes 31 of the fastening flange 30 of the flange 14 in front of the orifices 29 of the assembly ring 28 of the first wheel 1 during assembly. Moreover, FIG. 3 diagrammatically shows the passage of such a finger 36 under a root 3a of a blade, in the radial clearance which is generally left between the feet 3a and the bottom of the grooves 6a. It will also be noted here that the installation of the downstream flange 14 makes it possible to use a single blade model for the first wheel 1a. In a fourth step, with reference to FIG. 7, the first distributor 7 is mounted behind the first wheel 1a, equipped with its flanges 13, 14. It may be noted here that the inner ring 9 of the distributor 7, which forms, in the extension of the platforms 5a of the first wheel 1a, the internal wall of the stream F in the turbine, carries a web 37 which extends radially inwards. The inner periphery of the web 37 carries an abradable element 38 cooperating with the wipers 34 of the downstream flange 14, so as to form a labyrinth seal 35. The abradable element 38 is here a ring of abradable material entering radially in contact with the The spoiler 16 carried by the downstream flange 14 of the first wheel 1a extends under the shell 9 of the first distributor 7 and, in this example, its axial extension takes the major part of the difference between the part transverse 32 of the downstream flange 14 and the web 37 of the first distributor 7. Here, the web 37 of the first distributor 7 carries another annular spoiler 39, radially internal to the spoiler 16 of the flange 14, and having an axial overlap therewith, to form an additional baffle.
    [0021] In a fifth step, the upstream flange 17 of the second wheel 1b is placed on the assembly obtained in the fourth step. With reference to FIG. 8, this flange 17 corresponds to a third type of flange. Similar to the previous type, this flange 17 comprises: an annular flange 40 for fastening to the wheels, transverse and extending radially inwards, which comprises axial holes 41 distributed circumferentially in correspondence with those 29 of the mounting ring 28 of the first wheel 1a, a transverse annular portion 42 intended to form a stop upstream of the feet 3b of the blades of the second wheel 1b, and 5 an intermediate portion 43, which here has a frustoconical shape. In this fifth step, screws 44 will first be inserted through the orifices 29 of the assembly ring 28 of the first wheel 1a. These screws 44 protruding from the annular fastening flange 30 of the downstream flange 14 of the first wheel 1a, the fixing flange 40 of the upstream flange 17 of the second wheel 1b 10 can be pressed against that of the downstream flange 14 by passing the screw 44 through the corresponding holes 41. It can be seen in FIG. 8 that this third type of flange 17 resembles the second type of flange 14. The transverse annular portion 42, intended to stop the blade roots 3b axially upstream, carries an annular spoiler 19 which extends substantially axially upstream. As for the previous type, this spoiler 19 extends under the shell 9 of the first distributor 7 and fills more than half of the gap between the web 37 of the distributor 7 and the annular portion 42 of the flange 17. Moreover, the The web 37 of the dispenser 7 may also include an annular spoiler 45, radially internal to the spoiler 19 of the flange 17 and having an axial overlap therewith. Like the previous type of flange, the transverse annular portion 42 of the flange 17 carries, towards its radially inner edge, a plurality of fingers 46 extending radially downstream and intended to be inserted into grooves 6b the second wheel 1 b.
    [0022] Here, the intermediate portion 43 of the flange 17 is rather frustoconical in shape. This is because the diameter of the second wheel 1b is larger, as seen in Figure 1. However the main difference with the second type of flange 14 is that the intermediate portion 43 of the flange 17 does not wear. of elements participating in a labyrinth seal.
    [0023] Before installing the second wheel 1b, there are carried out on it two steps which correspond substantially to the first two mounting steps on the first wheel 1a. Referring to Figure 9, the second wheel 1b has a first assembly ring 47, upstream of the disk rim 2b, and a second ring 48, downstream of the rim 2b of the disk. These two rings 47, 48 are attached to the rim 2a of the disk by ferrules or frustoconical flanges. The first ring 47 has a diameter corresponding to that of the mounting ring 28 of the first wheel 1a and has axial orifices 49 distributed circumferentially so as to correspond to the screws 44 passing through the orifices 29 of the ring. assembly 28 of the first wheel 1 a. It is the same for the second ring 48 of the second wheel 1b vis-à-vis a mounting ring 50 for the third wheel lc, as can be seen in Figure 1. The diameters of these rings 47 , 48 are here significantly lower than that of the rim 2b of the disc of the second wheel 1b.
    [0024] Here, in a sixth step, downstream of the rim 2b of the disc of the second wheel 1b is installed a flange 18 similar to the flange 13 installed upstream of the first wheel 1a, in the first step. Like the upstream flange 13 of the first wheel 1a, the downstream flange 18 of the second wheel 1b consists essentially of a transverse flat ring extending in front of the feet 3b of the blades. As previously, the rim 2b of the disc and the internal periphery of the downstream flange 18 are configured so that the downstream flange 18 can be fixed thereto by a jaw-locked connection 51. As before, the downstream flange 18 comprises one or more fingers 52 turned, here upstream and being inserted into cavities 53 on the edges of the grooves 6b, as can be seen in FIG. 9.
    [0025] In a seventh step, the feet 3b of the vanes are inserted axially into the grooves 6b by the upstream face of the rim 2b. Referring to Figure 10, similarly to the first wheel 1a, the feet 3b of the blades thus in place permanently fix the downstream flange 18 by preventing it from rotating. Similar to the upstream flange 13 of the first wheel, this downstream flange 18 30 carries an annular spoiler 20 extending axially downstream, near the platforms 5b of the blades. The downstream flange is here in axial support against the platforms 3029960 16 5b and its radially outer end is flush with the surface of the platforms 5b forming a continuity of the wall of the vein of the flow of gas F downstream thereof. The eighth step corresponds to the mounting of the second wheel 1b on the assembly 5 obtained in the fifth step. In this eighth step, the orifices 49 of the upstream assembly ring 47 of the second wheel 1b are inserted axially around the screws 44 passing through the orifices 29 of the assembly ring 28 of the first wheel 1a and the holes 31. , 41 clamps 30, 40 of the two flanges 14, 17 in place. The connection between the first wheel 1a and the second wheel 1b is then locked by tightening a nut 54 on each screw 44, as can be seen in FIG. 11. This connection between the two successive wheels 1a, 1b serves also fixing the downstream flange 14 of the first wheel 1a and the upstream flange 17 of the second wheel lb to their respective wheels. It can be seen in FIG. 11 that the transverse annular portion 42 of the upstream flange 17 of the second wheel 1b, forming the upstream axial stop of the blade roots 3b, is contiguous with the platforms 5b and bears axially against the -this. The shape of the radial end of the flange 17 is further in continuity with that of the outer surface of the platforms 5b so as not to disturb the flow of gas F through the turbine. In addition, similarly to the downstream flange 14 of the first wheel 1a, the fingers 46 of the transverse portion 42 of the upstream flange 17 of the second wheel 1b have found their place under the feet 3b of blade in the grooves 6b of the second wheel 1b, forming a radial stop of the base of this transverse portion 42 of the upstream flange 17. At the end of this step, the part of the turbine surrounding the first distributor is completely assembled at the wheels and is found The configuration of FIG. 1. It will be noted, moreover, that the annular flanges 30, 40 for fixing the downstream flange 14 of the first wheel 1a and the upstream flange 17 of the second wheel 1b are contiguous. Thus, as can be seen in FIG. 1 and FIG. 11, the downstream flange 14 of the first wheel 1a and the upstream flange 17 of the second wheel 1b delimit the radially inner walls of an annular passage through which forced to pass a flow 3029960 17 leakage f, possibly escaping by the radial clearances between the ferrule 9 of the first distributor 7 and the platforms 5a, 5b of the blades of the first 1a and second 1b wheels. The leakage flow f is therefore limited in this passage by a succession of obstacles which are, going from upstream to downstream, the interposition of the spoiler 16 downstream flange 14 of the first wheel in front of the axial clearance between the platforms 5b of the blades of the first wheel and the shell 9 of the distributor, a baffle between the spoiler 16 of the downstream flange and the upstream spoiler 39 of the distributor 7, the radial labyrinth seal 35, a baffle between the downstream spoiler 45 of the distributor 7 and the spoiler 19 of the upstream flange 17 of the second wheel, and the interposition of the latter spoiler 19 in front of the axial clearance between the collar of the distributor 7 and the platforms 5b of the blade of the second wheel 1b. According to another aspect of the invention, the downstream flange 14 of the first wheel 1 forms in one piece the upstream portion of the inner wall of this passage, including the wipers 34 which participate in the labyrinth seal 35 forming a axial sealing under the web 37 of the first distributor 7, and carrying the spoiler 16 near the platforms 5a of the blades. According to yet another aspect that can be deduced by looking at FIG. 11, for the downstream flange 14 of the first wheel 1a as for the upstream flange 17 of the second wheel 1b, the fingers 36, 46 of each flange 16 , 17, passing under the feet 3a, 3b of the vanes, retain the inner radial edge of the transverse annular portion 32, 42 which supports the annular spoiler 16, 19. In this case, during the rotation of wheels 1a, 1b, the centrifugal force of the spoiler 16, 19, being axially offset relative to this transverse portion 3, 42, creates a torque around the radially inner base of the transverse portion 32, 42 which folds this portion towards the feet 3a, 3b blades. In this way, the radial end of each flange 14, 17 is pressed against the platforms 5a, 5b of the blades. It may be noted that, for the upstream flange 13 of the first wheel 1a and the downstream flange 18 of the second wheel 1b, the corresponding jaw connection 25, 51 has the same effect as the axial fingers 36, 46 while maintaining the 30 inner periphery of these flanges 13, 18 pressed against the rim 2a, 2b of the disc. In these conditions the centrifugal force on the spoiler 15, 20 also creates a torque that folds the outer radial edge of each flange 13, 18 to the platforms 5a, 5b of the blades. This is particularly useful for the upstream flanges 13, 17 because the spacing of the flange relative to the platforms 5a, 5b can disturb the flow arriving on the 5 blades of the wheel 1a, lb turbine. Moreover, when these flanges 13, 14, 17, 18 are arranged to be in continuity with the platforms 5a, 5b, this avoids parasitic openings, sources of leakage flow. In the example considered, as can be seen in FIG. 12, the configuration of the third wheel 1c with its flanges 21, 22 is similar to that of the first wheel 1a, by reversing upstream and downstream . The downstream flange 22 is here of the same type as the upstream flange 13 of the first wheel 1a, it is a transverse flat ring which is fixed by a linkage clutch 55 to the rim of the third wheel 2c. It also comprises one or more axial fingers cooperating with grooves of the disk rim 2c and the corresponding blade feet 3c to circumferentially block the flange 22. It also comprises an annular spoiler 24 configured to interpose in the axial clearance. between the platforms 5c of the blades of the third wheel lc and the inner wall 12 of the outlet vein. Upstream, the third wheel 1c wheel also has an assembly ring 50 20 whose diameter and holes for passing screws correspond respectively with the diameter and the mounting holes on the assembly ring 48 of the second wheel 1 b. The upstream flange 21 of the third wheel lc is a variant of the second type of flange, that 14 mounted downstream of the first wheel la. Indeed, this flange 21 comprises: an annular flange 56 for attachment to the wheels, transverse and extending radially inwards, which comprises axial holes distributed circumferentially in correspondence with those of the assembly rings 48, 50 of the second 1b and the third 1c, 30 a transverse annular portion 57 intended to form a stop upstream of the feet 3c of the blades of the third wheel lc, and 3029960 19 - an intermediate portion 58, which here has a frustoconical shape. The upstream flange 21 also carries wipers 59 connected to the intermediate portion 58. On the other hand, here the wipers 59 are connected to the intermediate portion 58 by a frustoconical crown 60 so that the wipers 59 are correctly positioned in front of the complementary abradable element 61 which is fixed to the second distributor 8 to form a labyrinth radial seal 62. This difference with respect to the previous configuration is due to the geometry of the vein which moves the second distributor 8 away from the third wheel 1c. The upstream flange 21 also comprises a plurality of fingers 63, starting from the base of the transverse portion 57 and arranged to fit under the feet 3c of the blades, in the grooves 6c, when the flange is mounted on the third wheel lc . These fingers 63 form a radial stop of the upstream flange 21 at the base of the feet 3c of the blades, as for the downstream flange 14 of the first wheel. In an alternative embodiment, a cavity may be hollowed out in the rim 2c of the disk, for example in a tooth between two grooves 6c, and the finger 63 may be inserted therein, while then bearing radially in the rim 2a itself. even. As the flange 21 is mounted axially, this cavity is not necessarily contiguous to a groove 6c.
    [0026] To obtain the configuration, described in FIG. 12 and FIG. 1, the assembly of the turbine comprises a ninth step in which the downstream flange 22 is fixed on the third wheel lc in a manner similar to what is done in the first step. for the upstream flange 13 on the first wheel 1 a. In a tenth step, the feet 3c of the blades are axially inserted in the grooves 6c of the rim 2c of the disc of the third roll c, as for the first wheel 1a in the second step. Then, in an eleventh step, the upstream flange 21 is placed on the third wheel 1c similarly to what is done for the downstream flange 14 on the first wheel 1a, in the third step. In a twelfth step, the third wheel lc being assembled with its flanges 21, 22, it is installed axially behind the assembly obtained at the end of the eighth step, 3029960 20 and then secured by screws its assembly ring. 50 and the fastening flange 56 of the upstream flange 21 to the downstream connecting ring 48 of the second wheel 1b. Still with reference to FIG. 12, when the screws passing through the mounting rings 48, 50 are tightened and fix the third wheel 1c against the second wheel 1b, the labyrinth seal 62 formed with the second distributor 8 closes an annular passage connecting the axial clearance between the platforms 5b of the blades of the second wheel lb and the inner ring 10 of the second distributor to the axial clearance between the shell 10 and the platforms 5c of the blades of the third wheel lc. The radially inner wall of this passage is formed by the upstream flange 21 of the third wheel 1c, downstream of the labyrinth seal 62. In addition, the spoilers 20, 23 on the flanges 18, 21, on the one hand, and spoilers on the internal web of the third distributor 8, on the other hand, form baffles in the radial direction having the same functions as in the case of the first distributor 7, to limit a leakage flow through the annular passage under the second distributor 8. It is noted, particularly in the latter case, that the wipers 59 are integral with the upstream flange 21 of the third wheel 1 c, avoids having to position, during assembly, an intermediate piece supporting these wipers. Only the upstream flange 21 of the third wheel lc intervenes here in addition to the discs of the wheels 1b, 1c in the definition and sealing of the annular passage under the second distributor 8. The shape and the combination of different flanges with wheels paddle, as well as their assembly has been shown here in detail for a particular turbine. It goes without saying that this example is purely illustrative. The invention is transposable to other forms of vein of a turbine, or even to compressors. Furthermore, the successive combinations of flange types installed on each wheel can be modified according to the configuration of the turbomachine and the mounting steps will then be adapted. Note that each of the types of flanges described can be mounted axially with respect to the wheel and allows axial mounting relative to the adjacent distributor on the turbine. The invention therefore makes it possible to mount the wheels and 3029960 21 of the distributors in a turbine or a compressor by a succession of axial assembly steps of the various parts described.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine wheel, comprising a disc carrying blades whose feet (3a, 3c) are fitted in grooves (6a, 6c) substantially parallel to an axis of revolution of the disc, the foot (3a, 3c) of each blade being connected to a blade (4a, 4c) by an integrated platform (5a, 5c), the wheel (1a, 1c) further comprising at least one annular flange (14, 21) fixed to the disk so as to form an axial abutment of the feet (3a, 3c) of the blades, characterized in that said flange comprises, on the one hand, an annular spoiler (16, 23) extending substantially axially on the side opposite the disc and forming an obstacle to a radial gas flow along said flange, and, on the other hand, annular wipers (34, 59) of a labyrinth seal (35, 62).
    [0002]
    2. Wheel according to claim 1, wherein the outer radial end of said flange (21) is substantially aligned axially with an outer annular surface for guiding an air flow platforms (5c) of the blades and is optionally in support axial on said platforms (5c).
    [0003]
    3. Wheel according to one of claims 1 or 2, wherein said flange (21) extends substantially over the entire radial dimension of the grooves (6c) of the disc.
    [0004]
    4. Wheel according to one of claims 1 to 3, wherein said flange (14, 21) comprises at least one finger (36, 63) extending substantially axially on the side of the disc, said finger (36, 63) being inserted in a groove (6a, 6c) for receiving a blade root (3a, 3c) or disk cavity, such as a cavity in a rim (2c) of the disk.
    [0005]
    5. Wheel according to claim 4, wherein said finger (36, 63) is inserted axially under the foot (3a, 3c) of a blade and is configured to be supported radially under the foot (3a, 3c). 3029960 23
    [0006]
    6. Wheel according to claim 4, wherein said finger (36, 63) is configured to be able to bear radially on at least one rim portion (2c) of the disk. 5
    [0007]
    7. Wheel according to one of claims 4 to 6, wherein said flange (14, 21) comprises an annular flange (40, 50) radially internal disc attachment.
    [0008]
    Wheel according to claim 7, wherein the wipers (34, 59) are carried by a portion (33, 43) of the flange (14, 21) forming a connection between the spoiler (16, 23) and said flange. fixing (40, 50).
    [0009]
    Turbomachine turbine comprising at least one wheel according to one of claims 1 to 8.
    [0010]
    10. Turbine according to the preceding claim, comprising a distributor (8) adjacent said wheel (1a, 1c) and carrying a ring of abradable material (38, 61) configured to cooperate with the wipers (34, 59) of said flange (14). , 21) to form a labyrinth seal (35, 62). 15 20
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    同族专利:
    公开号 | 公开日
    GB2533221B|2021-05-12|
    US10450884B2|2019-10-22|
    US20160169024A1|2016-06-16|
    GB201521777D0|2016-01-27|
    GB2533221A|2016-06-15|
    FR3029960B1|2021-06-04|
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    法律状态:
    2015-12-15| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-17| PLSC| Publication of the preliminary search report|Effective date: 20160617 |
    2016-12-05| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 5 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1462268A|FR3029960B1|2014-12-11|2014-12-11|BLADDER WHEEL WITH RADIAL SEAL FOR A TURBOMACHINE TURBINE|FR1462268A| FR3029960B1|2014-12-11|2014-12-11|BLADDER WHEEL WITH RADIAL SEAL FOR A TURBOMACHINE TURBINE|
    GB1521777.1A| GB2533221B|2014-12-11|2015-12-10|Impeller having a radial seal for a turbine engine turbine|
    US14/966,501| US10450884B2|2014-12-11|2015-12-11|Impeller having a radial seal for a turbine engine turbine|
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