• 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 rotor, for example a low-pressure turbine of a turbomachine, comprising: - a first disk, comprising a downstream arm, - a second disk, - an annular sealing ring comprising a radial flange comprising a annular portion on which is made a scalloping defined by a plurality of circularly distributed festoons, said radial flange being fixed on the rotor between the downstream arm of the first disc and the second disc by screw-nut assemblies, the assembly screws passing through bores made in the downstream arm of the first disk, the festoons of the radial flange and the second disk and - a flow circuit comprising at least one lunule adapted to put in fluid communication a radially inner cavity and a radially outer cavity, the lunula being formed in a downstream face of the radial flange of the sealing ring, the rotor being characterized in that the lunula is m on at least one festoon.
    公开号:FR3062415A1
    申请号:FR1750875
    申请日:2017-02-02
    公开日:2018-08-03
    发明作者:Laurent Capolungo Thierry；Florian CARRY；Cyrille Jacques Oudin Benjamin；Myriam PELLETERAT DE BORDE
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    @ Holder (s): SAFRAN AIRCRAFT ENGINES.
    O Extension request (s):
    Agent (s):
    CABINET REGIMBEAU Civil society.
    FR 3 062 415 - A1 ® TURBINE ROTOR OF A TURBOMACHINE WITH BLADED VENTILATION. (57) The invention relates to a turbine rotor, for example a low pressure turbine of a turbomachine, comprising:
    - a first disc, comprising a downstream arm,
    - a second disc,
    an annular sealing ring comprising a radial flange comprising an annular portion on which scalloping is carried out defined by a plurality of scallops distributed circularly, said radial flange being fixed on the rotor between the downstream arm of the first disc and the second disc by screw-nut assemblies, the assembly screws passing through holes made in the downstream arm of the first disc, the festoons of the radial flange and the second disc and
    - A flow circuit comprising at least one lunula, adapted to put in fluid communication a radially internal cavity and a radially external cavity, the lunula being formed in a downstream face of the radial flange of the sealing ring, the rotor being characterized in that the lunula is formed on at least one festoon.
    i
    TURBOMACHINE TURBINE ROTOR
    LAMINATED VENTILATION
    GENERAL TECHNICAL AREA AND PRIOR ART
    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 turbojet and turboprop aircraft and industrial gas turbines.
    The general operation and the composition of such a system are known in the art and explained in the document FR. 3,018,584, the system subsequently presented being an improvement.
    Generally, a turbomachine comprises one or more sections for compressing 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 and mixed with fuel before being burned there.
    The hot combustion gases from this combustion are then expanded in different stages of the turbine. A first expansion is made in a high pressure stage immediately downstream of the combustion chamber and which receives the gases at the highest temperature. The gases are expanded again by being guided through the so-called low pressure turbine stages.
    A low pressure turbine conventionally comprises one or more stages, each consisting of a row of fixed turbine blades, also called distributors, followed by a row of movable turbine blades, which form the rotor. The distributor deflects the flow of gas withdrawn from the combustion chamber towards the movable blades of the turbine at an appropriate angle and speed in order to rotate these movable blades and the rotor of the turbine.
    The rotor includes several discs, for example four discs, which generally include peripheral grooves such as cells in which the movable blades are fitted.
    The turbine rotor is subjected to a very hot thermal environment, well above the maximum temperatures allowed by the rotor parts.
    This is why the rotor generally comprises annular rotating ferrules with wipers (also called sealing ring), fixed to the discs of the rotor by means of annular radial flanges.
    A disc can be framed by the downstream flange of the upstream sealing ring and the upstream flange of the downstream disc, the downstream flange of the upstream sealing ring being itself bordered by the downstream flange of the arm of a upstream disc, the whole being held in position by a screw-nut assembly.
    The wipers of a sealing ring are placed opposite 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 coming from the air stream and rotor.
    Furthermore, the wipers generally consist of continuous or segmented blades of annular shape, arranged on the rotor at the level of the flange, while the bore of abradable material is arranged opposite, on a lower face of the dispenser.
    A specific ventilation for the rotor discs has also been implemented, comprising a flow of pressurized air taken upstream from the turbine, typically at the high pressure compressor, which is introduced into the rotor in order to cool its discs , in particular its cells.
    To this end, and as illustrated in FIG. 1, lunulas 17 (or radial grooves) are formed circumferentially on a downstream face 18 of the radial flange 11 of the sealing ring 8 upstream of a rotor disc 1, to bring the pressurized air flow to the cells of the rotor disc.
    More precisely, these lunulae 17 are arranged between holes 20 intended for the passage of the assembly screws 21, these holes 20 being produced on a scalloping comprising a plurality of scallops 19 extending radially from the flange 11.
    Said lunules 17 are usually machined directly in the mass of the radial flange 11, and comprise a part limiting the flow upstream of the direction of flow and an oblique non-limiting part produced on the chamfer of the sealing ring.
    The portions of the lunulas 17 calibrating the ventilation flow rate however have a reduced section, which implies for their machining the use of tools having a very small radius.
    FIGS. 2a and 2b highlight the fact that the shapes thus produced comprise surface portions having a very small radius of curvature and generate high stress concentration coefficients at the lunula level.
    With reference to FIG. 2a, a high concentration of stresses is localized at the level of the lunulae, more precisely at the level of the portions comprising the shortest radii of curvature as illustrated in FIG. 2b.
    This phenomenon is damaging for the life of the part.
    OVERVIEW OF THE INVENTION
    An object of the invention is to increase the life of the sealing ring.
    Another object of the invention is to reduce the concentration of stresses in the most stressed areas of the part.
    According to one aspect, the invention proposes a turbine rotor, for example a low pressure turbine of a turbomachine, comprising:
    a first disc, comprising a downstream arm, a second disc, a sealing ring comprising a radial flange comprising an annular portion on which a scalloping is carried out defined by a plurality of scallops distributed circularly, said radial flange being fixed on the rotor between the downstream arm of the first disc and the second disc by screw-nut assemblies, the assembly screws passing through holes made in the downstream arm of the first disc, the festoons of the radial flange and the second disc and a circuit of flow comprising at least one lunula, adapted to put in fluid communication a radially internal cavity and a radially external cavity, the lunula being formed in a downstream face of the radial flange of the sealing ring, the lunula being formed on at least a festoon.
    Such a rotor is advantageously supplemented by the following different characteristics taken alone or in combination:
    the lunula comprises an upstream portion projecting into the radially internal cavity and a downstream portion opening into a through portion of the lunula, the emerging portion projecting into the radially external cavity;
    the opening portion of the lunula is inclined relative to the radially external portion of the lunula;
    - At least one toroidal counterbore is produced at the scallop holes, on the downstream face of the radial flange, this toric counterbore bringing the upstream portion and the downstream portion of the lunula into communication;
    at least one of the scallops comprises a lunula extending along an axis and a bore extending along a second axis, the axes of the lunula and the bore are coplanar;
    the upstream portion of the lunula has a section such that the admissible flow rate through the downstream portion of the lunula and the countersink is greater than the admissible flow rate through the upstream portion of the lunula;
    the downstream portion of the lunula has a surface having a minimum radius of curvature than that of the surface of the upstream portion;
    the downstream portion of the lunula is formed on the annular portion of the radial flange, the upstream portion of the lunula being formed on the crest of a festoon.
    According to another aspect, the invention relates to a turbine, in particular a low pressure turbine comprising such a rotor.
    According to another aspect, the invention relates to a turbomachine, comprising such a turbine.
    PRESENTATION OF THE FIGURES
    Other characteristics and advantages of the invention will emerge from the description which follows, which is purely illustrative and not limiting, and should be read with reference to the appended figures in which:
    FIG. 1 is a 3D model representing a sealing ring comprising lunules produced on the downstream face of its radial flange;
    FIG. 2a is a finite element modeling representing the spatial distribution of the stresses during the loading of the sealing ring;
    FIG. 2b is a finite element modeling representing the distribution of the stresses during the loading of the sealing ring at the level of a lunula;
    Figure 3 is a schematic representation showing a sectional profile view of a low pressure turbine of a turbojet;
    FIG. 4 is a 3D modeling representing the assembly produced between a disc, a sealing ring, a downstream arm of an upstream disc and an upstream arm of a downstream disc;
    FIG. 5 is a 3D modeling representing a lunula produced at the level of the drilling of a scalloping element;
    FIG. 6 is a 3D modeling of the lunula shown in FIG. 5 highlighting the portions of the lunula calibrating or not for the cooling flow of the discs.
    DESCRIPTION OF ONE OR MORE MODES OF IMPLEMENTATION AND IMPLEMENTATION
    The embodiments described below relate more particularly to the case of a low pressure turbine, comprising a series of distributors (or stators) alternated along the axis X of rotation of the turbomachine with a series of mobile disks (or rotor) . This is not however limiting, insofar as the turbine could comprise a different number of stages, and that the invention also finds application in a high pressure turbine, which can be single or multi-stage.
    Referring to Figure 3, the turbine conventionally comprises one or more stages, each consisting of a distributor followed by a rotor 1 (or moving wheel).
    The rotor 1 has an axis X of revolution which corresponds to a main axis of the turbomachine and comprises several discs 2, for example four discs 2, which each comprise a hub 3 extending radially inwards in the direction of the axis X. Peripheral grooves such as cells 4, in which the movable vanes 5 are fitted, are formed in a rim of the hubs 3.
    Throughout the present text, the upstream and downstream are defined by the direction of flow of the gases in the turbomachine.
    The notions of axial and radial directions refer to the X axis of the turbomachine.
    The different discs 2 of the rotor 1 can in particular be assembled coaxially by bolting. The first and second discs 2a and 2b then comprise a downstream arm 6 which extends downstream from the downstream radial face of each of the discs 2a and 2b, the fourth disc 2d comprising an upstream arm 7 extending towards the 'upstream from the upstream radial face of the disc 2d.
    In order to ventilate the cells 4 of the discs 2 of the rotor 1, a flow of pressurized air can be taken upstream of the turbine, typically at the level of the high pressure compressor, and be introduced into the cells 4 in order to cool the discs 2. For this, the rotor 1 comprises a ventilation system 14 for each disc 2, comprising the flow circuit 9 adapted to put in fluid communication a radially internal cavity 15, in which the hub 3 of the disc 2 extends, and a radially external cavity 16, delimited by the sealing ring 8 and the upstream 7 or downstream 6 arms of the discs 2.
    The second and third discs 2b and 2c further include upstream sealing rings 8 making it possible to form the ventilation circuit 14 for the cooling flow of the discs 2.
    The sealing ring 8 can conventionally comprise wipers 10 on an external radial face. The sealing ring 8 is fixed to the disc 2 using an annular radial flange 11. In the embodiment illustrated in Figures 1 and 2, the radial flange 11 extends radially with respect to the axis X between the flange 13 of the downstream arm 6 of an upstream disc (for example 2b) and a disc downstream (for example 2c). The downstream arm 6, the disc 2 and the radial flange 11 can in particular be fixed together by means of an assembly screw 21 and a nut 24.
    In the embodiment illustrated in FIGS. 3 and 4, the downstream arm 6 of the disc 2b comprises a substantially axial part 12 (ferrule) relative to the axis X, which extends between the disc 2b and the flange 11 of the sealing ring 8, and a radial flange 13 relative to the axis X, which corresponds to the free end of the downstream arm 6. The downstream arm 6 can then be fixed together to the flange 11 of the ring 8 and downstream disc 2c through their radial parts.
    The flow circuit 9 (visible in FIG. 5) comprises a series of radial lunulas 17, forming channels for the circulation of the pressurized air flow from the radially internal cavity 15 to the radially external cavity 16. In fact, the fixing of the flange 13 of the downstream arm 6 of the upstream disc 2b and of the downstream disc 2c on the radial flange 11 is sealed. The pressurized air flow can only pass through the circulation channels thus formed.
    The section of the lunulas 17 is chosen so as to allow sufficient ventilation of the discs 2 of the rotor 1 while limiting the flow of pressurized air taken upstream from the combustion chamber to avoid excessive degradation of the performance of the turbojet engine.
    The lunulae 17 may comprise grooves extending radially with respect to the axis of revolution X of the rotor 1.
    According to a first embodiment illustrated in FIG. 5, the lunulas 17 are formed in the downstream face 18 of the radial flange 8, more precisely at the level of the scallops 19 offering a locally increased surface to allow the holes 20 intended for the screws. assembly 21.
    So that the lunulas 17 are in fluid communication with the radially internal cavity 15, they extend up to the crest 23 of the scalloping 19.
    Furthermore, so that the lunules 17 are in fluid communication with the radially external cavity 16, they extend until they protrude into said cavity 16, opening onto a through portion 17c, inclined in this embodiment and produced on a chamfer and having a larger section.
    The axis A of the lunula 17 being coplanar with the axis B of the bore 20, a toroidal counterbore 22 is produced around the bore 20 to guarantee the continuity of the flow circuit 14 once the assembly has been carried out.
    A lunula 17 therefore comprises at least four distinct portions:
    A radially internal upstream portion 17a in communication with the radially internal cavity 15 and the countersink 22;
    The countersinking 22 allowing the cooling flow to bypass the screw 21 despite the pressure drop that this causes, and therefore placing in communication the radially inner upstream portion 17a of the lunula and a radially outer downstream portion 17b;
    The radially external downstream portion 17b in communication with the countersinking 22 and the through portion 17c;
    The opening portion 17c in communication with the downstream portion 17b and opening into the radially external cavity 16.
    In FIGS. 5 and 6, the upstream portions 17a and downstream 17b are shown extending radially. In a variant not shown, the portions may not be oriented strictly radially with respect to the axis of revolution of the rotor. Similarly, the through portion 17c can be inclined or not relative to the portions 17a and 17b.
    The location of the lunulae 17 at the level of the scallops 19 thus makes it possible to limit the effects of stress concentration by locating the calibrating part of the cooling flow in the ridge 23 of the scallops 19, which is a “dead” zone under stress.
    In order to preserve the performance of the turbojet engine, the cooling flow of the disks taken upstream from the combustion chamber is calibrated by means of a bottleneck limiting the flow rate.
    This neck is produced by the upstream portion 17a of the lunules, the very small section of which is configured to naturally limit the flow rate of the cooling flow.
    ίο
    With reference to FIG. 6, to simplify the regulation of this flow rate, only the upstream portion 17a of the lunulas is dimensioned to limit it. The other portions of the lunula therefore have a larger section than the section of the upstream portion 17a, in particular so that the effects of pressure drop along the lunula 17 do not play a role in calibrating the flow rate of the cooling flow. .
    The upstream portion 17a of the lunules therefore has a surface comprising shorter radii of curvature than the other portions of lunules 17. The stress concentration coefficients are therefore the most critical in the zone comprising the upstream portions 17a of the lunules.
    The less mechanically constrained area of the flange being the scallop crest 23, which is therefore in contact with the radially inner enclosure 15, the upstream portions 17a of the lunulas are formed on these scallop crests 23.
    The other portions of lunula 17b and 17c have a larger section, therefore comprising surfaces having larger radii of curvature and thereby limiting the concentration of stresses.
    This limitation of the stress concentrations in the annular portion 25 of the radial flange 11, being the most mechanically loaded zone, makes it possible to increase the life of the sealing ring 8.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Turbine rotor (1), for example a low pressure turbine of a turbomachine, comprising:
    a first disc (2a), comprising a first downstream arm (6), a second disc (2b), an annular sealing ring (8) comprising a radial flange (11) comprising an annular portion (25) on which is produced scalloping defined by a plurality of scallops (19) distributed circularly, said radial flange (11) being fixed on the rotor (1) between the downstream arm (6) of the first disc (2a) and the second disc (2b) by screw (21) - nut (24) assemblies, the assembly screws (21) passing through holes (20) made in the downstream arm (6) of the first disc (2a), the scallops (19) of the radial flange (11) and the second disc (2b) and a flow circuit (9) comprising at least one lunula (17), adapted to put in fluid communication a radially internal cavity (15) and a radially external cavity (16), the lunula (17) being formed in a downstream face (18) of the radial flange (11) of the sealing ring (8), the rotor (3) being characterized é in that the lunula (17) is formed on at least one festoon (19).
    [2" id="c-fr-0002]
    2. Rotor according to claim 1, characterized in that the lunula (17) has a radially inner portion (17a) projecting into the radially inner cavity (15) and a radially outer portion (17b) in fluid communication with a through portion of the lunula (17c), the through portion (17c) projecting into the radially external cavity (16).
    [3" id="c-fr-0003]
    3. Rotor according to claim 2, characterized in that the through portion of the lunula (17c) is inclined relative to the radially outer portion (17b) of the lunula.
    [4" id="c-fr-0004]
    4. Rotor according to one of claims 2 to 3, characterized in that at least one toroidal counterbore (22) is produced at the holes (20) of the scallops (19), on the downstream face (18) of the radial flange (11), this toroidal countersinking (22) bringing the radially internal portion (17a) and the radially external portion (17b) of the lunula (17) into communication.
    [5" id="c-fr-0005]
    5. Turbine rotor according to claim 4, characterized in that the radially internal portion of the lunula (17a) has a cross section such that the admissible flow rate through the radially external portion (17b) of the lunula and the countersink (22) is greater at the flow rate admissible by the radially internal portion of the lunula (17a).
    [6" id="c-fr-0006]
    6. Turbine rotor according to one of claims 2 to 5, characterized in that the radially external portion of the lunula (17b) has a surface having a minimum radius of curvature greater than that of the surface of the radially internal portion (17a ).
    [7" id="c-fr-0007]
    7. Turbine rotor according to one of claims 2 to 6, characterized in that the radially external portion (17b) of the lunula is formed on the annular portion (25) of the radial flange (11), the radially internal portion (17a) of the lunula being formed on a crest (23) of a festoon (19).
    [8" id="c-fr-0008]
    8. Turbine rotor according to one of the preceding claims, characterized in that at least one of the scallops (19) comprises a lunula (17) extending along an axis (A) and a bore (20) extending along a second axis (B), the axes of the lunula (A) and the bore (B) being coplanar.
    [9" id="c-fr-0009]
    9. Turbine, in particular low pressure turbine, characterized in that it comprises a rotor (1) according to one of claims 1 to 8.
    [10" id="c-fr-0010]
    10. Turbomachine, characterized in that it comprises a turbine according to claim 9.
    1/3
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    引用文献:
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    法律状态:
    2018-01-22| PLFP| Fee payment|Year of fee payment: 2 |
    2018-08-03| PLSC| Publication of the preliminary search report|Effective date: 20180803 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 4 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 5 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1750875A|FR3062415B1|2017-02-02|2017-02-02|ROTOR OF TURBINE TURBINE ENGINE WITH VENTILATION BY LAMINATION|
    FR1750875|2017-02-02|FR1750875A| FR3062415B1|2017-02-02|2017-02-02|ROTOR OF TURBINE TURBINE ENGINE WITH VENTILATION BY LAMINATION|
    US15/885,711| US10815784B2|2017-02-02|2018-01-31|Turbine engine turbine rotor with ventilation by counterbore|
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