• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a rotor (3), comprising: - a first and a second disk (30), each comprising an upstream arm (36) and a downstream arm (38), - a sealing ring (40) comprising a radial flange (44), and - a ventilation system, comprising: * through holes (46), formed in the radial flange (44), * upstream lunules (48), and * downstream lunules (50), orifices (46), the upstream lunules (48) and the downstream lunules (50) together forming channels for circulating a flow (F) of pressurized air in the rotor (3).
    公开号:FR3019584A1
    申请号:FR1453062
    申请日:2014-04-07
    公开日:2015-10-09
    发明作者:Lionel Rene Henri Weller；Sylvie Devaux；Ludovic Gallego
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates generally to gas turbine engines, and more particularly to the ventilation of the stages of a turbine, for example a low pressure turbine of a turbomachine. Fields of application of the invention are aircraft turbojet and turboprop engines and industrial gas turbines. BACKGROUND ART An example of a turbomachine has been illustrated in FIG.
    [0002] A turbomachine 1 typically comprises a nacelle which forms an opening for the admission of a given flow of air to the engine itself. Conventionally, the gases flow from upstream to downstream through the turbomachine. Generally, the turbomachine comprises one or more compression sections 4 of the air admitted into the engine (generally a low pressure section and a high pressure section). The air thus compressed is admitted into the combustion chamber 5 and mixed with fuel before being burned. The hot combustion gases from this combustion are then expanded in different turbine stages. A first expansion is made in a high pressure stage 6 immediately downstream of the combustion chamber 5 and which receives the gases at the highest temperature. The gases are expanded again by being guided through so-called low pressure turbine stages 7.
    [0003] A turbine, low pressure 7 or high pressure 6 conventionally comprises one or more stages, each consisting of a row of fixed turbine blades, also called distributors, followed by a row of turbine blades, which form the rotor . Dispenser 2 deflects the flow of gas drawn from the combustion chamber 5 to the turbine blades at a suitable angle and speed to drive these rotating blades and the rotor of the turbine in rotation.
    [0004] The rotor comprises several disks, for example five disks, which generally comprise peripheral grooves such as cells in which the blades are nested. The rotor of the turbine is subjected to a very hot thermal environment, well above the maximum permissible temperatures by the rotor parts. For this reason, the rotor generally comprises an annular ring rotating with wipers (also called sealing ring), opposite which is placed a static part having a bore comprising an abradable material capable of withstanding high temperatures, in order to reduce the convective exchanges between the flow of hot air from the air stream and the rotor. The sealing ring is fixed on the rotor by means of an annular radial flange at the junction between the mobile disks, more precisely between a downstream arm of the upstream disk and an upstream arm of the downstream disk. Moreover, the wipers are generally constituted by continuous or segmented annular blades disposed on the rotor at the flange, while the bore of abradable material 14 is arranged facing, on a lower face of the dispenser.
    [0005] Specific ventilation for the rotor disks has also been implemented, comprising a pressurized air flow taken upstream of the turbine, typically at the level of the high compressor, which is introduced into the rotor in order to cool its disks, especially its alveoli. For this purpose, and as illustrated in FIG. 2, lunules 100 (or radial grooves) are formed circumferentially on a downstream face of the radial flange of the sealing ring, in order to bring the flow of pressurized air to cavities through the cavity delimited by the upstream arm of the downstream disk and the sealing ring. These lunules 100, which are depressions extending substantially radially relative to the axis X of the turbomachine, are usually machined directly in the mass of the radial flange. However, it turns out that their implementation is tedious and can not be controlled accurately, so it is necessary to oversize to ensure a minimum section to ventilate the cell bottoms. In practice, there is indeed a very high dispersion of the calibrating section, that is to say the minimum section of the lunules 100 necessary to sufficiently ventilate the cells, due to the geometry of the lunula 100 and their complex realization. This dispersion can indeed reach 40% between the minimum admissible section and the section obtained for the lunules 100. Moreover, there is as yet no simple and reliable control means making it possible to verify that the section of the lunules 100 is sufficient. to properly ventilate the discs. It is therefore usual to oversize the section of the lunula 100. However, the amount of pressurized air taken upstream of the turbine is then much greater than necessary, which greatly reduces the performance of the turbomachine.
    [0006] SUMMARY OF THE INVENTION An object of the invention is to improve the design and robustness of the turbine ventilation system of a turbomachine turbine, in particular a low pressure turbine, so as to ensure sufficient ventilation. of these disks while limiting the flow of air taken for this ventilation, and thus improve the performance of the turbomachine. For this, the invention proposes a turbine rotor, for example a low-pressure turbine of a turbomachine, comprising: a first disk comprising at least a first upstream arm, a first downstream arm and a first hub; disk, comprising at least a second upstream arm, a second downstream arm and a second hub, - an annular sealing ring comprising an annular radial flange, said radial flange being fixed on the rotor between the first downstream arm of the first disk and the second upstream arm of the second disk, and - a ventilation system, adapted to put in fluidic communication a radially inner cavity, in which extend the first hub and the second hub and a radially outer cavity, extending between the second arm upstream and the sealing ring, the rotor being characterized in that the ventilation system comprises: a series of through orifices formed in the radial flange between the e first downstream arm and the second upstream arm, - a series of upstream loops, adapted to put in fluid communication the radially inner cavity and the series of through holes, and - a series of downstream lunules, adapted to put in fluid communication the series of through holes and the radially outer cavity. Some preferred but non-limiting characteristics of the rotor described above are as follows: the upstream loops are formed in an upstream face of the radial flange, the upstream loops are formed in a downstream face of the first downstream arm of the first disc, the downstream lunules are formed in a downstream face of the radial flange, the downstream lunules are formed in an upstream face of the second upstream arm 20 of the second disk, the upstream lunules open into the radially inner cavity and the downstream lunules open into the radially outer cavity, the Through-holes open into the upstream and downstream lunules, a section of the through-holes is smaller than a section of the upstream ones and a section of the downstream ones, and the through orifices extend substantially parallel to an axis of revolution of the rotor. According to a second aspect, the invention also proposes a turbine, in particular a low-pressure turbine, characterized in that it comprises a rotor as described above, as well as a turbomachine, comprising such a turbine.
    [0007] BRIEF DESCRIPTION OF THE DRAWINGS Other features, objects and advantages of the present invention will appear better on reading the detailed description which follows, and with reference to the appended drawings given as non-limiting examples and in which: FIG. 1 FIG. 2 is a fragmentary perspective view of an annular sealing ring 10 with wipers comprising lunettes for ventilating the rotor according to the prior art. FIG. 3a illustrates an axial sectional view along the X axis of FIG. 1 of a turbine rotor comprising an exemplary embodiment of a ventilation system according to the invention. FIG. 3b is an axial sectional view. of a turbine rotor comprising a second embodiment of a ventilation system according to the invention, Figure 4 is a view of an upstream face of the wiper ring of the figure 3a, and FIG. 5 is a view of a downstream face of the wiper seal ring of FIG. 3a. DETAILED DESCRIPTION OF AN EMBODIMENT The invention will be described very particularly with reference to a low-pressure turbine 7, comprising a series of alternating distributors 2 (or stators) along the X axis of rotation of the turbomachine 1 with a series of mobile disks 3 (or rotor). This is however not limiting, since the turbine 7 could comprise a different number of stages, and that the invention also finds application in a high-pressure turbine 6, which can be single or multi-stage.
    [0008] The turbine 7 conventionally comprises one or more stages, each consisting of a distributor 2 followed by a rotor 3 (or moving wheel). The rotor 3 has an axis X of revolution which corresponds to a main axis of the turbomachine 1 and comprises a plurality of discs 30, for example five discs 30, each of which comprises a hub 31 extending radially inwards toward the rotor X axis. Peripheral grooves such as cells 32, in which the blades 34 are engaged, are formed in a rim 33 of the hubs 31. The various rotor discs 30 may in particular be assembled coaxially by bolting. Each rotor disc 30 then comprises an upstream arm 36 which extends upstream from the upstream radial face of the disc 30, around which can be mounted an annular sealing ring 40 sealing the passage of the cooling air of the discs 30, as well as a downstream arm 38 which extends from the downstream radial face of the disc 30, adapted to be connected with the upstream arm 36 of the adjacent downstream disc 30. Here, upstream and downstream are defined by the flow direction of the gases in the turbomachine 1. The sealing ring 40 may conventionally comprise wipers 42 on an outer radial face. The sealing ring 40 is attached to the upstream and downstream arms 38 of the disks 30 by means of an annular radial flange 44 (FIG. 4). In the exemplary embodiment illustrated in the figures, the radial flange 44 extends radially with respect to the X axis between the upstream arm 36 and the downstream arm 38. The upstream and downstream arms 36 and the radial flange 44 may in particular be fixed together by bolting. In the embodiment illustrated in the figures, the upstream arm 36 of the disc 30 comprises a substantially axial portion (ferrule) 36a with respect to the axis X, which extends between the disc 30 and the flange of the annulus 30. sealing 44, and a radial portion 36b with respect to the X axis, which corresponds to the free end of the upstream arm 36. Similarly, the downstream arm 38 of a disc 30 comprises a substantially axial portion (ferrule) 38a relative to the X axis, which extends between the disk 30 and the flange of the sealing ring 44, and a radial portion 38b with respect to the X axis, which corresponds to the free end of the arm 38. The upstream arm 36 and the downstream arm 38 can then be fastened together to the flange 44 of the sealing ring 40 via their radial portions 36b, 38b.
    [0009] In order to ventilate the cavities 32 of the discs 30 of the rotor 3, a pressurized air flow can be taken upstream of the turbine 7, typically at the level of the high-pressure compressor, and introduced into the cavities 32 in order to cool the discs 30 For this, the rotor 3 comprises a ventilation system for each disk 30, adapted to put in fluid communication a radially inner cavity 8, in which the hub 31 of the disk 30 extends, and a radially outer cavity 9, in which extend the upstream arm 36 and the sealing ring 40.
    [0010] The ventilation system comprises: a series of through orifices 46, which can extend substantially parallel to the X axis, formed in the radial flange 44 between the downstream arm 38 and the upstream arm 36, a series of upstream loops. 48, adapted to put in zo fluidic communication the radially inner cavity 8 and the series of through orifices 46, and - a series of blind 50 downstream lunules, adapted to put in fluid communication the series of through holes 46 and the cavity radially external 9. The upstream loops 48, the through holes 46 and the downstream lunules 50 thus together form channels for circulating the flow F of pressurized air from the radially inner cavity 8 to the radially outer cavity 9. upstream 36 and downstream 38 flanges on the radial flange 44 is sealed. The flow F of pressurized air can only borrow the 30 traffic channels thus formed.
    [0011] The section of the through orifices 46 is chosen so as to allow sufficient ventilation of the discs 30 of the rotor 3. Consequently, it is the section of the through orifices 46 which is dimensioning for the ventilation of the discs 30, and no longer the section of the discs 30. The section 48 of the upstream and downstream loops 50 is therefore simply chosen to be larger than the section of the through orifices 46, in order to bring the flow F of pressurized air from the radially inner cavity 8 to the through orifices 46, then through orifices 46 to the radially outer cavity 9.
    [0012] Since, nowadays, piercing techniques make it possible to obtain orifices of precise and controlled size and shape, the tolerances related to the production of the through-orifices 46 in the radial flange 44 are much smaller than for the embodiment of lunules (of the order of ± 0.05 mm instead of ± 0.2 mm for the lunula 100), so that it is possible to reduce the dispersion of the ventilation section from 40% to about 5%. In addition, the methods for controlling the size and shape of orifices are also more precise, faster and less costly than for controlling the dimensions and shape of lunules. It is therefore much easier and faster to control the quality of the ventilation system of the rotor 3 than for the conventional arrangement illustrated in Figure 2. Therefore, thanks to this ventilation system 46, 48, 50, it is now possible to control precisely the section of the circulation channels of the flow F of pressurized air between the radially inner cavity 8 and the radially outer cavity 9, which allows on the one hand to reduce the flow F of pressurized air taken upstream of the turbine 7 (and therefore to improve the performance of the turbomachine 1) and secondly to ensure sufficient ventilation of the discs 30 of the rotor 3.
    [0013] The section of the through orifices 46 is chosen as a function of the stage of the corresponding disk 30, the temperature of the turbine 7, the flow rate of the air stream through the turbomachine 1, etc. This choice being the usual work of the skilled person, it will not be detailed further here. The through orifices 46 may be of circular section. It is indeed very easy nowadays to control the section of an orifice when it is circular, insofar as it is sufficient to determine its diameter. This is however not limiting, the through orifices 46 may have a non-circular section. Moreover, the through orifices 46 may extend along the axis X of revolution of the rotor 3, which also makes it possible to simplify the control of its passage section. As a variant, the through orifices 46 may also extend along an axis inclined with respect to the axis X. The lunules, for their part, may comprise grooves extending radially with respect to the axis of revolution X of the rotor 3.
    [0014] According to a first embodiment illustrated in FIGS. 4 and 5, the upstream loops 48 and the downstream lunules 50 are respectively formed in an upstream face 44a and in a downstream face 44b of the radial flange 44. in fluid communication with the radially inner cavity 8, they extend to a radially inner edge 44c of the radial flange 44. Furthermore, so that the downstream lunules 50 are in fluid communication with the radially outer cavity 9, they extend to protrude into said radially outer cavity 9, ie beyond the radial portion 36b of the upstream arm 36 extending opposite the radial flange 44. It should be noted that it is generally easier to machine open-ended lunules (that is to say projecting into one of the radially internal 8 or outer 9 cavities) that lunules extending at a distance from an edge.
    [0015] Thus, in an alternative embodiment (see FIG. 3b), the downstream lunulas 50 may be formed in the radial portion 36b of the upstream arm 36, facing the through orifices 46. In this way, the downstream lunulas 50 open into the cavity radially outer 9 and extend to a radially outer edge of the radial portion 36b of the upstream arm 36. In this embodiment, the upstream loops 48 can then be formed in the upstream face 44a of the radial flange 44, as illustrated in FIG. 4. Thus, both the upstream lunules 48 and the downstream lunules 50 open into the corresponding cavity 8, 9. Alternatively, the upstream loops 48 may be formed in the radial portion 38b of the downstream arm 38, facing the through orifices 46. The downstream lunules 50 may then be formed either in the downstream face 44b of the radial flange 44, as illustrated. in FIG. 5, or in a variant be made in the radial portion 36b of the upstream arm 36. The upstream and downstream lunules 48 and 50 may be obtained by milling in the mass of the radial flange 44 (or, if appropriate, of the arm portion 36b). upstream or part 38b of the downstream arm), while the through orifices 46 can be obtained by drilling.20.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Turbine rotor (3), for example a low pressure turbine (7) of a turbomachine (1), comprising: - a first disk (30), comprising at least a first upstream arm (36), a first downstream arm ( 38) and a first hub (31), - a second disk (30), comprising at least a second upstream arm (36), a second downstream arm (38) and a second hub (31), - a sealing ring Annulus (40) comprising an annular radial flange (44), said radial flange (44) being fixed on the rotor (3) between the first downstream arm (38) of the first disk (30) and the second upstream arm (36) of the second disc (30), and - a ventilation system (46, 48, 50), adapted to put in fluidic communication a radially inner cavity (8), in which the first hub (31) and the second hub ( 31), and a radially outer cavity (9) extending between the second upstream arm (36) and the sealing ring (40), the rotor (3) being characterized in that the system ventilation system comprises: - a series of through orifices (46), formed in the radial flange (44) between the first downstream arm (38) and the second upstream arm (36), - a series of upstream loops (48) adapted to fluidically communicate the radially inner cavity (8) and the series of through holes (46), and - a series of downstream lunules (50) adapted to fluidically communicate the series of through holes (46). ) and the radially outer cavity (9).
    [0002]
    The turbine rotor (3) (7) according to claim 1, wherein the upstream loops (48) are formed in an upstream face (44a) of the radial flange (44).
    [0003]
    The turbine rotor (3) (7) of claim 1, wherein the upstream lunules (48) are formed in a downstream face of the first downstream arm (36) of the first disk (30).
    [0004]
    4. turbine rotor (3) (7) according to one of claims 1 to 3, wherein the downstream lunules (50) are formed in a downstream face (44b) of the radial flange (44).
    [0005]
    The turbine rotor (3) (7) according to one of claims 1 to 3, wherein the downstream lunules (50) are formed in an upstream face of the second upstream arm (36) of the second disk (30).
    [0006]
    6. Rotor (3) turbine (7) according to one of claims 1 to 5, wherein the upstream lunules (48) open into the radially inner cavity 15 (8) and the downstream lunules (50) open into the cavity radially external (9).
    [0007]
    7. Rotor (3) turbine (7) according to one of claims 1 to 6, wherein the through holes (46) open into the upstream lunulas (48) 20 and in the downstream lunules (50).
    [0008]
    8. Rotor (3) turbine (7) according to one of claims 1 to 7, wherein a section of the through holes (46) is less than a section of the upstream lunules (48) and a section of the downstream lunules ( 50). 25
    [0009]
    9. turbine rotor (3) (7) according to one of claims 1 to 8, wherein the through holes (46) extend substantially parallel to an axis of revolution (X) of the rotor (3). 30
    [0010]
    10. Turbine (7), in particular low-pressure turbine, characterized in that it comprises a rotor (3) according to one of claims 1 to 9.
    [0011]
    11. Turbomachine (1), characterized in that it comprises a turbine (7) according to claim 10.5
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    法律状态:
    2016-04-14| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-06| PLFP| Fee payment|Year of fee payment: 4 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 5 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1453062A|FR3019584B1|2014-04-07|2014-04-07|SYSTEM FOR VENTILATION OF A TURBINE USING CROSSING ORIFICES AND LUNULES|
    FR1453062|2014-04-07|FR1453062A| FR3019584B1|2014-04-07|2014-04-07|SYSTEM FOR VENTILATION OF A TURBINE USING CROSSING ORIFICES AND LUNULES|
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