• 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:
    It is an assembly for a gas turbine, comprising stationary vanes forming a distributor (5) whose adjacent side faces (171, 173) are placed end to end and which comprise slots (31 a, 33a) made in opposite the adjacent side faces of two successive fixed vanes, and sealing plates (35) arranged individually in the slots vis-à-vis two successive fixed vanes. At least some of the sealing pads have a natural curvature and are wedged, deformed under bending stress, in the slots.
    公开号:FR3033827A1
    申请号:FR1552185
    申请日:2015-03-17
    公开日:2016-09-23
    发明作者:Olivier Jean Daniel Baumas；Nicolas Daniel Delaporte；Anthony Pierre Beguin
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to the general field of devices providing a sealing function in a turbomachine, in particular an airplane turbojet or turboprop engine. The turbines of such machines typically comprise a plurality of stages each comprising an annular row of stationary vanes carried by a casing of the turbine and an annular row of vanes rotatably mounted about a central axis of rotation.
    [0002] Radially, in delimitations of the circulating gas vein, in particular the vanes have areas called platforms where two successive blades are adjacent. Annually extending, these platforms are sectored, that is to say that they each consist of a plurality of segments joined end to end, along a circumference, around the central axis of rotation. It is necessary to provide at least a relative seal between the adjacent segments of these platforms in order to prevent air leakage that is particularly detrimental, particularly to the proper cooling of these segments and which may also lead to a decrease in engine performance. or even damage to parts downstream. For this purpose, it is known to interpose tabs or sealing plates between the adjacent segments. Such tongues or plates are generally housed in substantially axial and / or radial slots made opposite each other in the adjacent side faces of the segments. They thus make it possible to obstruct the clearance existing between two adjacent segments in order to limit the air leaks irrespective of the thermal expansion undergone by the segments. Thus, for example, there is known a gas turbine assembly, comprising: a plurality of stationary vanes forming a distributor whose adjacent lateral faces are placed end to end and which comprise slots facing each other; in the adjacent lateral faces of two successive fixed vanes, and sealing plates arranged individually in the slots facing two successive fixed vanes. A persistent problem remains, however, related to a pronounced wear of these sealing pads, see their absence: The wear reduces the size of the pads which can then go out of their homes (slots). A solution proposed here is that at least some of said sealing plates naturally have a curvature and are wedged in the slots, being deformed under mechanical stress.
    [0003] Mounting these curved plates in the present sealing slots designed for flat plates will allow pre-stressing without having to modify the slots. Thus locked under tension, platelets will be less sensitive to the conjunction of vibrations and temperature, typical causes of wear. Indeed, pushed to the bottom of their homes by the force of the air, the current pads vibrate and come to wear in the bottom of distributors. Favorably, some at least platelets will have a length and several inverse curvatures along this length. Thus (at least) doubly curved, the plates can not only be mounted in prestressing in their receiving slots, but maintain a preload even in case of slight wear of a wafer end. For the sake of an optimized balance efficiency / ease of manufacture / cost, it is recommended that at least some of the pads have two reverse curvatures.
    [0004] Thus doubly curved in their length, the plates can not only be mounted in prestressing in their receiving slots, but retain a preload even in case of slight wear of one end of platelets.
    [0005] 5 and providing: - along said length, only two curved vertices, respectively located about 1/4 and about 3/4 of this length, - and / or platelets having a maximum deflection of 1mm to +/- 1 0% at these two vertices, the stresses on the platelets will be balanced and will continue to tend towards the aforementioned optimized equilibrium. In addition, in order to combine suitable flexibility and resistance over time, it is recommended that the inserts be made of nickel-cobalt hot-melt alloy with a thickness of 0.2mm to +/- 10%.
    [0006] And it is also advisable: - that the radial vanes of the distributor have external and internal platforms respectively delimiting, radially outer and inner, the gas flow passage in the turbine, - that the slots in which are arranged said sealing plates are elongated in a general direction from upstream to downstream with respect to a flow of gas in the turbine, and that in such an elongated slot the seal plate is by pressing against walls of said slots, disposed away from a downstream end of the slot.
    [0007] Indeed, it will avoid, or at least limit, the typical wear in the bottom of slots. Other features and advantages are further detailed below, with reference to the accompanying drawings in which: FIG. 1 is a partial schematic view in axial axial section of a part of a turbomachine, it being specified that the solution is applies one or more low-pressure stages to one or more high-pressure stages. FIG. 2 is a local perspective view, along arrow II of FIG. 1, of a part of the dispenser shown diagrammatically in FIG. 1 and carrying seal means of the invention, FIGS. are enlarged views, in medial axial sections, of a radially outer portion of one of the vanes of the dispenser of FIG. 2, mounted, in each case with a wafer embodiment, and FIG. of one of the embodiments of the wafer presented as a sealing means relevant in the invention. In Figure 1 is more precisely schematically a turbine part 1 of an aerospace turbine engine. In the gas turbine 1, there is seen a rotor 3 and a stator, also called a distributor, belonging to the same stage of the turbine, which may comprise several, successively, parallel to the axis around which the vanes rotate. In this description is "radial" what is (substantially) radiating with respect to the axis 7 and is "axial" which extends (substantially) next, or parallel, to the axis 7. The rotor 3 defines a wheel having a plurality of blades 9 attached to a disk 11 and rotatably mounted each about the axis 7, here axially downstream of the distributor. Each blade 9 comprises a blade 13 and a radially inner platform 15. A ring 16 sealing the blade against the outside air is disposed around the blades 13, radially outside thereof, to limit the fact that the air in the vein does not bypasses the blading. The stator 5 comprises a plurality of stationary vanes 17 which collectively form an annular structure, centered on the axis 7, and individually a ring segment (see FIG. 2).
    [0008] Each segment 17 has one or more blades 19 extending radially between an outer platform 21 and an inner platform 23. The inner platforms 23 are attached to a fixed support structure, or stator, 25 and the outer platforms 21 are supported by the casing, or casing, 27 arranged radially outside (around) the stator 5. This may be specific to the high pressure part or the stage 1 of a turbine low pressure. On the other stages, the vanes can be fixed at their outer part 21 to the turbine casing and the inner platform 23 can not be maintained. The outer and inner platforms 21, 23 collectively form the outer and outer limits respectively of the vein 29 of the gas flowing through the turbine, this vein being also limited radially by the inner platform 15 and the gasket. At the location of the rotor 3. In FIG. 2, it can be seen that adjacent lateral faces 171, 173 of the vanes 17 of this distributor belonging to two successive sectors of blades 17a, 17b are placed end to end, circumferentially. around the aforementioned axis 7.In each side face (see for example that marked 175 sector 17a, opposite the face 171) are formed one or more slots, here 31a, 33a.
    [0009] In the present case, two series of slots have been provided in the lateral faces of the respective external and internal platforms 21, 23. In the corresponding adjacent lateral faces, such as here 171 and 173, of two internal (and / or external) platforms of two circumferentially successive fixed vanes, the considered slits, such as those marked 31b, 31c in FIG. -a-vis. And in each double slot opposite two successive sectors of this distributor, is housed (at least) a sealing plate 35 intended to obstruct the clearance between two adjacent segments to limit air leakage, regardless of the thermal expansion experienced by the segments.
    [0010] However, such wafers are highly stressed in this environment where vibration and temperature are critical for their wear. It is therefore in particular to limit premature and inappropriate wear of these wafers 35 that it is expected that they individually have a natural curvature (see Figure 2, left wafer at rest, out of its receiving slots) and are stuck in their receiving slots (see right figure 2, for example in the double slot vis-à-vis 31b, 31c, but also Figures 3 and 4), being deformed under mechanical stress, here bending. Curved, the plates 35 will thus be able to be mounted in prestressing in the receptive slots typically not curved (planes) of conventional distributor segments. Thus locked under tension, the pads will be less sensitive to the conjunction of vibrations and temperature. In FIGS. 3 and 4 (where the drawings are less symbolic than in the preceding figures), a radially outer portion of a fixed blade 17 and two types of curved plates 35 are shown, which can also be seen respectively in FIG. left and figure 5, at rest.
    [0011] 3, the outer platform 21 is provided with two tabs, respectively upstream and downstream, 211,213, connecting (fixing) to the housing 27 and which extend radially outwardly. The slot 31d, formed in the side face 177 of the outer platform 21, is extended by or comprises, in the example, two portions 311d, 313d transverse to an intermediate portion 315d. The intermediate portion 315d extends into the platform 21 which is slightly inclined with respect to the axis 7. The two transverse portions 311d, 313d respectively extend in the upstream leg (AM) 211 and in the downstream leg (AV) 213.
    [0012] In the example, only the portion 315d of the slot 31d houses, over part of its width or depth, a curved plate according to an embodiment of the invention and marked 35a, in contrast with the curvature In this example, the wafer 35a, of length L, has a single curvature, with a vertex centered at mid-length, at 350a in FIG. 3.
    [0013] Under bending stress in the contiguous slots which receive it, the plate bears at its ends and at 350a against two opposite walls which limit them internally, as illustrated. Figures 4,5, the wafer 35b has the same length L and several inverse curvatures, two in this case, along this length 10 This solution will promote preservation of the prestressing, even in case of slight wear of a wafer end , in the slots. For the sake of an optimized balance efficiency / ease of manufacture / cost, the wafer 35b has two inverse curvatures, with a point of inflection at mid-length.
    [0014] In fact, it has: - along the length L, only two curved peaks 350b, 351b, situated respectively at about 1/4 and about 3/4 of this length, - and a maximum height of curvature, or arrow, h of 1mm to +/- 10% at the location of these two peaks.
    [0015] It will be understood that this arrow h is perpendicular to the length L and the jerk 1, the distance between the vertices, or that between one of the vertices and one of the ends, as shown in FIG. Moreover, a suitable flexibility and a resistance in time, it is recommended that the platelets 35, 35a, 35b are made of hot-resistant alloy based on nickel and cobalt, with a thickness of 0.2 mm, at +/- 10%. Overall, each wafer will be favorable as a parallelepiped thin plate-shaped body, possibly beveled angles.
    [0016] It should be considered that, when dimensioned, the aforesaid curved plates could be usefully introduced into the "radial" slots 311d, 313d, and provided both at the outer and outer platforms 21 and 23. 3 and 4, it will also be noted that the stress engagement of the plates allows, in particular, in the "axial" slots 315d extending along the length of the platforms 21 (like those 31a, 33a, FIG. differently so "radial" slots of the transverse portions 311d, 313d), the plates are not plated sloping downstream bottom. Figures 3 and 4, a space 310d remains between the downstream end of the wafer and the downstream wall of the slot considered.
    [0017] Thus, in the slot 315d thus elongated generally in a direction from upstream (AM) downstream (AV) with reference to the direction of flow of the gas in the vein 29, the sealing plate disposed therein is, by pressure against walls of the slot, kept away from a downstream end 3150d of the slot, even if, in operation, the plates will be plated, despite the prestressing, at the bottom of the slots.
    权利要求:
    Claims (7)
    [0001]
    REVENDICATIONS1. Gas turbine assembly, comprising: - a plurality of stationary vanes forming a distributor (5) whose adjacent side faces (171, 173) are placed end to end and which comprise slots (31a, 33a, 315d ...) made facing each other in the adjacent lateral faces of two successive fixed vanes; and sealing plates (35, 35a, 35b) arranged individually in the slots (31a, 33a, 315d. -vis of two successive fixed vanes 10, characterized in that at least some sealing plates (35,35a, 35b) have at least one natural curvature and are wedged, deformed under mechanical stress, in the slots.
    [0002]
    2. The assembly of claim 1, wherein at least some of the wafers (35,35a, 35b) have a length (L) and several inverse curvatures along this length.
    [0003]
    3. The assembly of claim 2, wherein at least some platelets have two inverse curvatures along said length, with vertices (350b, 351b) respectively about 1/4 and about 3/4 of that length.
    [0004]
    4. The assembly of claim 2 or 3, wherein at least some platelets have a maximum deflection (h) of 1mm to +/- 10% at the point of the vertices (350b, 351b).
    [0005]
    5. An assembly according to one of claims 1 to 4, wherein the platelets 25 (35,35a, 35b) are hot-nickel-based alloy of nickel and cobalt, with a thickness of 0.2mm to +/- 10%.
    [0006]
    6. Assembly according to one of claims 1 to 5, wherein the blades belong to a turbine turbine low pressure (1) of a turbomachine.
    [0007]
    7. An assembly according to one of claims 1 to 6, wherein: the fixed blades extend radially about an axis (7) and have external and internal platforms (21,23) delimiting, respectively, Radially outer and inner, a vein (29) for a gas flowing through the turbine, - the slots (31a, 33a, 315d ...) in which said sealing pads are disposed are elongate in a general direction from 5 from the upstream (AM) downstream (AV) with respect to a circulation of the gas in the turbine, - and, in such an elongated slot, the sealing plate (35, 35a, 35b) is, by pressing against walls of said slots, disposed away from a downstream end (3150d) of the slot. 10
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    同族专利:
    公开号 | 公开日
    FR3033827B1|2019-08-23|
    WO2016146920A1|2016-09-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2010027384A1|2008-09-05|2010-03-11|Siemens Energy, Inc.|A seal structure between transition ducts of a plurality of combustor units of a gas turbine|
    US20120292862A1|2011-05-20|2012-11-22|Frank Moehrle|Turbine seals|
    WO2013139837A1|2012-03-21|2013-09-26|Alstom Technology Ltd|Strip seal and method for designing a strip seal|WO2019048766A1|2017-09-06|2019-03-14|Safran Aircraft Engines|Turbine assembly with ring segments|
    US20190085713A1|2017-09-21|2019-03-21|Safran Aircraft Engines|Turbine sealing assembly for turbomachinery|
    FR3106158A1|2020-01-14|2021-07-16|Safran Aircraft Engines|SECTORIZED BLADE CROWN FOR TURBOMACHINE INCLUDING AN INTER-SECTOR SEALING BODY WITH IMPROVED FORM COMPATIBILITY|US7316402B2|2006-03-09|2008-01-08|United Technologies Corporation|Segmented component seal|
    WO2008033897A1|2006-09-12|2008-03-20|Parker-Hannifin Corporation|Seal assembly|
    法律状态:
    2016-02-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-23| PLSC| Publication of the preliminary search report|Effective date: 20160923 |
    2017-03-15| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2019-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1552185|2015-03-17|
    FR1552185A|FR3033827B1|2015-03-17|2015-03-17|GAS TURBINE SEAL PACKAGE ASSEMBLY|FR1552185A| FR3033827B1|2015-03-17|2015-03-17|GAS TURBINE SEAL PACKAGE ASSEMBLY|
    PCT/FR2016/050552| WO2016146920A1|2015-03-17|2016-03-11|Assembly with sealing plates for gas turbine|
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