• 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 turbine blade (20) intended to be rotatably mounted in a turbine chamber (10) of a turbomachine (1). The blade comprises a blade body (21) having a blade head (22) and at least one sealing means adapted to seal between the blade (20) and an inner wall (11) of the chamber (10) when the blade (20) is mounted in the chamber (10), the sealing means being mounted on the blade head (22). The sealing means comprises at least a first sealing element (30a, 30b) movably mounted on the blade head (22) between a rest position and an operating position in which the sealing element (30a) , 30b) is radially projecting from the blade head (22) by a greater height than in the rest position. The invention further relates to a turbine assembly and a turbomachine both having at least one blade according to the invention.
    公开号:FR3025555A1
    申请号:FR1458434
    申请日:2014-09-09
    公开日:2016-03-11
    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] TECHNICAL FIELD The invention relates to the field of turbomachines and the arrangement of turbine blades fitted to turbomachines. STATE OF THE PRIOR ART Turbomachines are composed of numerous parts among which the turbine or turbines are not the least. Indeed, a turbine in particular for the role of recovering the energy from the combustion of gases to drive the propeller shaft of the propeller and the compressor. The optimization of the turbine or turbines is therefore essential for the proper functioning of a turbomachine. A turbine has an expansion chamber, generally composed of turbine rings, and vanes mounted in the chamber. Some of these blades are fixed and participate in the formation of the stator, while others are rotatably mounted and participate in the formation of the rotor. It should be noted that, depending on the configuration, a turbomachine may comprise a single turbine or comprise two that follow one another, a so-called high-pressure turbine and a so-called low-pressure turbine, the high-pressure turbine being upstream of the low-pressure turbine in the direction general flow of gases.
    [0002] However, in order to ensure maximum efficiency of a turbine, it is necessary to ensure that a maximum part of the gases resulting from the combustion contributes to the displacement of the rotor and thus to avoid leakage of stray gas. It is known to prevent such leaks from equipping the turbine blades with sealing elements called wipers. These wipers are arranged on the dawn head. Complementarily, the inner wall of the turbine chamber comprises a layer of abradable material. The wipers are dimensioned so as to come into contact with the layer of abradable material. Thus, at the first start of the 3025555 2 turbomachine, the wipers will come into contact with the abradable material and remove by wear the superfluous abradable material portion ensuring a minimum clearance between the blades and the inner wall of the chamber. With such wipers and the layer of abradable material, the turbines 5 have a reduced clearance between the blades and the inner wall of the chamber and much of the gas leakage is avoided. Nevertheless, such a game management system is not perfectly adapted. Indeed, with such a management system, the adjustment of the game is for the configuration of the turbomachine in which the play between the wipers and the inner wall 10, without abradable layer, is minimum. In operation and depending on the temperature in the turbine, the clearance between the wipers and the inner wall, excluding abradable layer, can vary significantly. As a result, in certain operating configurations of the turbomachine gas leaks are important. The performance of the turbomachine is therefore penalized.
    [0003] SUMMARY OF THE INVENTION The object of the invention is to solve this drawback and is thus intended to provide a turbomachine turbine blade which, when mounted movably in a turbine chamber, makes it possible to provide a clearance between the turbine engine and the turbine engine. blade and the inner wall of the minimum chamber regardless of the configuration of the turbomachine.
    [0004] To this end, the invention relates to a turbine blade intended to be rotatably mounted in a turbomachine turbine chamber and comprising: a blade body having a blade head; at least one d sealing adapted to seal between the blade and an inner wall of the chamber when the blade is mounted in the chamber, the sealing means being mounted on the blade head, the sealing means comprising at least one first sealing member movably mounted on the blade head between a resting position and an operating position in which the sealing element is radially protruding from the blade head by a greater height. important in the rest position. Due to its movable mounting, the sealing element makes it possible to provide, by its variation in height of projection of the blade head, an adjustment of the game which is adaptive.
    [0005] Indeed, the sealing element can be moved, regardless of the clearance between the rest of the blade and the inner wall, in contact with the inner wall of the chamber. Sealing is thus ensured both in the configurations of the turbomachine in which the game is minimal than in the configurations in which it is maximum. The performance of the turbomachine is therefore not penalized by any gas leaks in the turbine regardless of the clearance between the remainder of the blade and the inner wall and thus regardless of the configuration of the turbomachine. The first sealing element can be mounted movable in translation between its rest position and its operating position, this mobile assembly in translation preferably being in a substantially radial trajectory with respect to the axis of the turbomachine when the Dawn is mounted in the room. Such an assembly makes it possible to minimize the displacement movement of the sealing element between its rest position and its operating position. The sealing element can be freely mounted in displacement so that the rotation of the blade around the axis of the turbomachine 20 moves the sealing element towards its operating position. With such an assembly, it is not necessary to provide any system for moving the sealing member since the displacement and adjustment of this same displacement are solely by the centrifugal force associated with the rotation of the sealing element. dawn when starting the turbomachine.
    [0006] The blade may further comprise a biasing means adapted to constrain the sealing member into its operative position. Such a constraint means allows a displacement of the sealing element before the start-up of the turbomachine thus ensuring a good seal of the turbine blade wheel fitted during the entire operation of the turbomachine.
    [0007] The sealing means may further comprise a housing arranged in the blade, said housing housing the sealing member in the rest position, said housing being preferably arranged in a heel of the blade head. Such a housing makes it possible to limit the influence of the sealing element 5 vis-à-vis the aerodynamics of the blade. The sealing element may comprise a base and a sealing wall which extends circumferentially, vis-à-vis the axis of the chamber when the blade is mounted therefrom, from the base. A sealing element comprising such a sealing wall is particularly suitable for making the interface between the blade and the inner wall of the chamber substantially watertight. The sealing element may be dimensioned to be in contact with a circumferential portion of the inner wall of the chamber, the sealing element being preferably shaped so that, when blades form a wheel of the turbine, the set of sealing elements in contact with a substantially continuous circumferential line of the chamber. With such a configuration, the sealing at the interface between the blades forming a turbine wheel and the inner wall of the chamber is particularly good.
    [0008] The sealing means may comprise at least one second sealing member movably mounted on the blade head between a rest position and an operating position in which the second sealing member is radially projecting from the head of the blade. dawn from a higher height than in a rest position. Such a second sealing element makes it possible to perfect the seal 25 between the blade and the inner wall of the chamber thus ensuring a good efficiency of the turbomachine whatever its operating configuration. The invention also relates to a turbine assembly comprising a housing defining a turbine chamber and at least one turbine blade rotatably mounted in the chamber, the turbine blade being a blade according to the invention.
    [0009] The invention further relates to a turbomachine comprising a turbine chamber and at least one blade mounted in said chamber, said blade being a blade according to the invention. Such a turbine assembly and such a turbomachine benefit from the advantages provided by the use of a blade according to the invention. BRIEF DESCRIPTION OF THE DRAWINGS The present invention will be better understood on reading the description of exemplary embodiments, given purely by way of indication and in no way limiting, with reference to the appended drawings in which: FIG. 1 illustrates a schematic view of a turbomachine comprising a turbine equipped with blades according to the invention, - Figure 2 illustrates a close-up view of a turbine chamber illustrated in Figure 1 showing a blade according to the invention comprising two sealing elements which are in 3, a close-up view of the turbine chamber illustrated in FIG. 1 in which the turbomachine is in a configuration where the clearance between the inner wall of the turbine chamber and the blade, excluding elements. the sealing elements being in contact with the inner wall of the turbine chamber, FIG. 4 illustrates a close-up view of the turbine chamber illustrated in Figure 1 in which the turbomachine is in a configuration where the clearance between the inner wall of the turbine chamber and the blade, excluding sealing elements, is minimal, the sealing elements being in contact with the inner wall of the turbine chamber.
    [0010] Identical, similar or equivalent parts of the different figures bear the same numerical references so as to facilitate the passage from one figure to another. The different parts shown in the figures are not necessarily in a uniform scale, to make the figures more readable.
    [0011] DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS FIG. 1 schematically illustrates a turbomachine 1 comprising two turbines, a high-pressure turbine 3 and a low-pressure turbine, the high-pressure turbine 3 being upstream of the low-pressure turbine 4 in the general sense The low-pressure turbine 4 comprises a turbine chamber 10 equipped with blades 20 according to the invention. FIG. 2 illustrates a close and schematic view of the low-pressure turbine chamber 4 in which the turbine blades 20 are movably mounted, FIG. 2 illustrating only one. In such a configuration, the blade 20 illustrated in FIG. 2 is assembled with other blades of the same type to form a turbine wheel and to be included in a non-referenced rotor of the turbomachine 1. The blades 20 form with the turbine chamber 10 and a turbine casing, which delimits the chamber 10, a turbine assembly. It should be noted that such a blade 20 is particularly advantageous for equipping a low-pressure turbine 4 with the turbomachine. Nevertheless, it is also conceivable, without departing from the scope of the invention, for such a blade 20 to equip a high-pressure turbine 3 of the turbomachine 1 or to equip both the low-pressure turbine 4 and the turbine 3. The blade 20 comprises a blade body 21, or blade, longitudinal which extends substantially radially with respect to the axis of the turbomachine 1, not shown. At the inner end of the blade body 21, that is to say the one lying opposite the axis of the turbomachine 1, the blade body 21 comprises a connection system, not shown, such that fir attachment or hammer clip so as to allow its mounting on a disk, not shown as such. The outer end of the blade body, that is to say the one facing an inner wall 11 of the turbine chamber 10, forms the blade head 22. As illustrated in FIG. , the blade head comprises a heel 25. The heel 25 is an element of the blade 20 which extends circumferentially at the level of the blade head 20 on either side of the blade body 3025555 7 The heel 25 is shaped to form with the other heels of the blades of the same wheel, a frustoconical ring, centered around the axis of the turbomachine 1, and which is facing the inner wall 11 of the chamber 10. The heel 25 comprises, as illustrated in FIG. 2, two extensions 23a, 23b in the direction of the inner wall of the chamber 10 each delimiting a respective housing 24a, 24b for a first and a second sealing element 30a, 30b. Each of these extensions 23a, 23b takes the form of a rail extending substantially circumferentially with respect to the axis of the turbomachine 1, the central portion of said rail forming the housing 24a, 24b corresponding to said extension 23a, 23b. The shape of each housing 24a, 24b of the extensions 23a, 23b of the blade is adapted so that the sealing member 30a, 30b which is housed therein can move in translation between a rest position, in which it is at distance from the inner wall 11 of the chamber 10, and an operating position in which the element protrudes from the blade head 22 to come into contact with the inner wall 11 of the chamber 10. In their operating position , each sealing member 30a, 30b is radially projecting from the blade head 22 by a greater height than in the rest position. Such a conformation is obtained by a constant section of the housing 24a, 24b along the radial direction of the turbomachine 1 over a height greater than the displacement of the sealing element 30a, 30b between its rest position and its position. Operating. Each housing 24a, 24b has an opening for the passage of the sealing element 30a, 30b which is housed therein during its displacement in contact with the inner wall 11 of the chamber 10.
    [0012] Each sealing element 30a, 30b comprises a circumferential section of the axis of the T-shaped turbomachine inverted in the radial direction of the turbomachine 1, the horizontal bar of the T being a base 32a, 31b of the element. sealing, the vertical bar of the T being a sealing wall 32a, 32b. The sealing element 30a, 30b extends in a circumferential curve, with respect to the axis of the turbomachine, over at least a part of the circumferential length along the same axis of the heel 25. base 31a, 31b of each sealing element 30a, 30b has a constant circumferential section and complementary to that of the housing 24a, 24b corresponding to allow free displacement in translation of the sealing member 30a, 30b in the radial direction of the turbomachine 1. Thus, the base 31a, 31b of each sealing member 30a, 30b has a circumferential width slightly smaller than that of the housing 24a, 24b corresponding. The sealing wall 32a, 32b of each sealing element 30a, 30b extends radially from the corresponding base 31a, 31b in the direction opposite to the axis of the turbomachine 1. The height of each of the walls 32a, 32b is adapted so that its outer end, that is to say the opposite end to the base 31a, 31b, can come into contact with the inner wall 11 of the chamber 10, whatever the clearance between the heel 25 and the inner wall 11. Such an adaptation can be obtained with a height of the sealing wall 32a, 32b greater than the distance between the outer wall of the housing 24a, 24b corresponding, that is to say ie proximal with the inner wall 11 of the chamber 10, and the inner wall of the chamber in the configuration where the clearance between the heel 25 and the inner wall 11 of the chamber 10 is maximum (configuration shown in Figure 3).
    [0013] In order to limit the risks of wear of the sealing elements 30a, 30b and of damage to the inner wall 11 of the chamber 10, the sealing elements 30a, 30b are preferably made of a Ceramic Matrix Composite material ( CMC). The sealing elements form with the housings 24a, 24b, a sealing means adapted to seal between the blade 20 and the inner wall 11 of the chamber 10. Thus, a turbine equipped with such blades 20 has , as illustrated in Figures 3 and 4, a good seal between the blades 20 and the inner wall 11 of the chamber 10 through the sealing elements 30a, 30b. In fact, when the blades are put into rotation, the free translation of the sealing elements 30a, 30b 3025555 9 in the corresponding housings 24a, 24b allows the sealing elements 30a, 30b to move from the position of rest, illustrated in Figure 2, to the operating position shown in Figures 3 and 4 regardless of the clearance between the heel 25 and the inner wall 11 of the chamber 10.In fact, with the sizing of the housing 24a, 5 24b and sealing walls 32a, 32b which is adapted, the base 32a, 32b of each sealing element will abut only, as illustrated in Figure 3, when the clearance between the corresponding heel 25 and the internal wall 11 of the chamber 10 is maximum. Thus, and as illustrated in FIG. 3, when the turbine engine is started, the speed of rotation of the rotor is sufficient to move the sealing elements 30a, 30b without, at first, reaching a speed in which the length of the rotor blade body 21 is influenced. In this configuration, the clearance between the heel 25, excluding sealing elements 30a, 30b, and the inner wall 11 is then maximal. The displacement of the sealing elements 30a, 30b bring them into abutment on the outer wall of the housing 24a, 24b, having their outer end in contact with the inner wall 11. When the turbomachine reaches its full speed, as illustrated on FIG. 4, the rotor has a speed such that the generated centrifugal force causes an extension of the blade body 21. As a result, with the expansion of the chamber, the clearance between the bead 25, excluding the sealing element 30a, 30b, and the inner wall 11 is reduced and becomes minimal. In this configuration, the sealing elements 30a, 30b are held by the support of their outer end on the inner wall, and are placed in an intermediate position in the corresponding housing.
    [0014] The sealing elements 30a, 30b are thus maintained in these two extreme configurations in contact with the inner wall 11 of the chamber 10, the gas leaks at the space between the blades 20 and the inner wall 11 of the Chamber 10 are limited regardless of the configuration of the turbomachine. The performances of the turbomachine are thus preserved.
    [0015] It should be noted, of course, that if FIGS. 2 to 4 do not show a layer of abradable material at the inner wall 11 of the chamber 10, this possibility is compatible with the invention. According to this possibility, the sealing elements 30a, 30b come into contact with the abradable layer and cause wear 5 thereof. When such an abradable layer is present, the housings 24a, 24b are thus sized to compensate for the wear of the abradable layer and allow the sealing elements 30a, 30b can be in contact with the latter regardless of the wear of this layer and the configuration of the turbomachine.
    [0016] If in the embodiment described above the sealing elements 30 are mounted free in translation relative to the remainder of the blade, it is also conceivable that this movement is constrained. Thus, it is possible, for example, to provide a spring system that can be adapted to, in operation of the turbomachine, put the sealing element in contact with the inner wall of the chamber. Similarly, it is also possible to provide a pneumatic control adapted to put the sealing element in contact with the inner wall of the chamber. In addition, if the configuration of the sealing elements in the embodiment described above is particularly suitable for a blade comprising a heel, it is also conceivable to equip a blade having no heel with such elements. sealing this without going beyond the scope of the invention. Finally, if in the embodiment described above the sealing elements are mounted movable in translation, the mobile assembly of the latter may be other without departing from the scope of the invention. Indeed, it is quite possible to mount the rotationally movable sealing elements with an arrangement adapted for the rotation of the rotor to move them in contact with the inner wall of the chamber.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Impeller blade (20) designed to be rotatably mounted in a turbine chamber (10) of a turbomachine (1) and comprising: - a blade body (21) having a blade head (22), at least one sealing means adapted to seal between the blade (20) and an inner wall (11) of the chamber (10) when the blade (20) is mounted in the chamber (10), the sealing means being mounted on the blade head (22), the blade (20) being characterized in that the sealing means comprises at least a first sealing element (30a, 30b) mounted movably on the blade head (22) between a rest position and an operating position in which the sealing element (30a, 30b) projects radially from the blade head (22) by a greater height than 'in the rest position.
    [0002]
    2. blade (20) according to claim 1, wherein the first sealing member (30a, 30b) is mounted movable in translation between its rest position and its operating position, this movable assembly in translation preferably being in a path substantially radial vis-à-vis the axis of the turbomachine when the blade (20) is mounted in the chamber (10).
    [0003]
    3. blade (20) according to claim 1 or 2, wherein the sealing member (30a, 30b) is mounted freely in displacement so that the rotation of the blade (20) around the l The axis of the turbomachine (1) moves the sealing element towards its operating position.
    [0004]
    4. A blade according to claim 1 or 2, further comprising a constraint means adapted to constrain the sealing member in its operating position.
    [0005]
    5. blade (20) according to any one of claims 1 to 4, characterized in that the sealing means further comprises a housing (24a, 24b) 3025555 12 arranged in the blade head (20), said housing (24a, 24b) housing the sealing member (30a, 30b) in the rest position, said housing (24a, 24b) being preferably arranged in a heel (25) of the blade head (22).
    [0006]
    The blade (20) of any one of claims 1 to 5, wherein the sealing member comprises a circumferentially extending base (31a, 31b) and a circumferentially extending sealing wall (32a, 32b). to the axis of the chamber when the blade is mounted, from the base (31a, 31b). 10
    [0007]
    The blade (20) according to any one of claims 1 to 6, wherein the sealing member (30a, 30b) is sized to contact a circumferential portion of the inner wall of the chamber, the sealing member being preferably shaped so that when blades form a wheel of the turbine, all the sealing elements is in contact on a substantially continuous circumferential line of the chamber (10).
    [0008]
    8. blade (20) according to any one of claims 1 to 7, wherein the sealing means comprises at least a second sealing member (30b, 30a) mounted to move on the blade head (22) between a rest position and an operating position in which the second sealing member (30b, 30a) radially projects from the blade head (22) by a greater height than in the rest position.
    [0009]
    9. Turbine assembly, comprising a casing delimiting a chamber (10) of turbine and at least one turbine blade rotatably mounted in the chamber (10), said assembly being characterized in that the turbine blade is a blade according to any one of claims 1 to 8.
    [0010]
    10. Turbomachine (1) comprising a chamber (10) of turbine and at least one blade (20) movably mounted in said chamber (10), the turbomachine (1) being characterized in that said blade (20) is a blade according to any of claims 1 to 8.
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    同族专利:
    公开号 | 公开日
    FR3025555B1|2019-08-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3117716A|1963-04-10|1964-01-14|Bell Aerospace Corp|Ducted rotor|
    FR2388181A1|1977-04-20|1978-11-17|Rolls Royce|SEALING FOR ROTARY CONCENTRIC SHAFTS|
    DE19531561A1|1995-08-28|1997-03-06|Abb Research Ltd|Turbine blade stiffening member|
    EP1469165A1|2003-04-16|2004-10-20|Snecma Moteurs|Reduction of the blade tip clearance in a gas turbine|
    DE102004050739A1|2004-10-19|2006-04-20|Mtu Aero Engines Gmbh|Gas turbine has slits in radially outer ends of vanes of rotor to contain radially movable sealing element sealing gap between vane and housing|FR3059041A1|2016-11-21|2018-05-25|Safran Aircraft Engines|ROTOR / STATOR CONTROL DEVICE WITH SPRING LOAD|
    FR3073000A1|2017-11-02|2019-05-03|Safran Aircraft Engines|MOBILE AUB OF A TURBOMACHINE|
    FR3082873A1|2018-06-21|2019-12-27|Safran Aircraft Engines|TURBOMACHINE ASSEMBLY, TURBOMACHINE BLADE AND TURBOMACHINE|
    FR3088954A1|2018-11-22|2020-05-29|Safran Aircraft Engines|SEALING ASSEMBLY|
    法律状态:
    2015-09-09| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-11| PLSC| Search report ready|Effective date: 20160311 |
    2016-09-05| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-17| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 5 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1458434A|FR3025555B1|2014-09-09|2014-09-09|TURBINE DAWN AND TURBOMACHINE|
    FR1458434|2014-09-09|FR1458434A| FR3025555B1|2014-09-09|2014-09-09|TURBINE DAWN AND TURBOMACHINE|
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