• 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) of a member (7) of a turbomachine (1), for example a rotor of a turbine (7), said rotor (3) comprising: - a first element (30), - a second element (20), defining with the first element a ventilation cavity (9), the rotor (3) being characterized in that it further comprises a spacer (40), attached and fixed between the first element ( 30) and the second element (20) and comprising a series of through passages (42) configured to allow an injection of cooling fluid (F) into the ventilation cavity (9).
    公开号:FR3048998A1
    申请号:FR1652234
    申请日:2016-03-16
    公开日:2017-09-22
    发明作者:Benjamin Cyrille Jacques Oudin；Pascal Casaliggi；Thierry Laurent Capolungo；Didier Desire Rene Pasquiet
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    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
    An example of a turbomachine has been illustrated in FIG.
    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.
    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 3. The distributor 2 deflects the flow of gas taken at 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.
    The rotor comprises several disks, for example four 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 a wiping-tight sealing ring fixed on the hub of each disc facing which is placed a static portion 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.
    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-pressure compressor 4, which is introduced into the rotor in order to cool its discs, in particular its cells. For this purpose, lunules (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 the cells through the cavity defined by the hub. of the downstream disc and the sealing ring. These lunules, which are depressions extending substantially radially relative to the axis X of the turbomachine, are often machined in the mass of the sealing ring. Alternatively, they can be machined directly into the mass of the disc. 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 necessary to sufficiently ventilate the cells, due to the geometry of the lunules and their complex realization. This dispersion can indeed reach 40% between the minimum admissible section and the section obtained for the lunulae. In addition, there is currently no simple and reliable control means for verifying that the section of lunules is sufficient to properly ventilate the disks.
    It is therefore usual to oversize the section of the lunules by increasing the nominal section of the lunules to ensure sufficient ventilation of the disks. 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.
    It has therefore been proposed in the document FR 3,019,584 in the name of the Applicant, a ventilation system comprising through holes, formed at the connection of two adjacent disks. The dimensioning section of this ventilation system then corresponds to that of the through-holes, which are easier and more precise to make than lunulae. This ventilation system thus ensures sufficient ventilation for the disks while limiting the flow of air taken for this ventilation, thus improving the performance of the turbomachine.
    However, in use, it turns out that these machining generate very high stresses in the discs because of the strong centrifugal and thermal stresses that are likely to limit the life of these parts that are critical because necessary for proper operation of the turbomachine.
    SUMMARY OF THE INVENTION
    An object of the invention is therefore to provide a rotor ventilation system of an element such as a low-pressure turbine of a machine, which does not reduce the life of the rotor and does not weaken it all. by guaranteeing sufficient ventilation of these disks and by limiting the flow of air taken for this ventilation.
    For this purpose, the invention proposes a rotor of a member of a turbomachine, for example a rotor of a turbine, said rotor comprising: a first element; a second element defining with the first element a ventilation cavity; the rotor being characterized in that it further comprises a spacer, attached and fixed between the first element and the second element and comprising a series of through passages configured to allow an injection of cooling fluid into the ventilation cavity.
    Certain preferred but nonlimiting characteristics of the rotor described above are the following, taken individually or in combination: the first element comprises an annular disc comprising a hub and a rim, said rim being configured to receive blades of the member, the second element comprises a sealing ring comprising an internal radial flange fixed on the hub and an outer radial flange in contact with the rim, the sealing ring defining with the disc the cavity of ventilation of the rim; spacer is annular, and wherein said spacer is attached and fixed between the inner radial flange and the disc hub, the spacer is discontinuous and has a plurality of sub-parts secured between the inner radial flange and the hub, the passages being obtained by leaving a gap between two adjacent sub-parts, - each passage comprises a through hole, formed in the entrance etoise and opening at the hub, away from the ventilation cavity, - the spacer comprises a radially outer edge opening into the ventilation cavity and a radially inner edge opening at the hub, away from the ventilation cavity, and each passage further comprises a groove extending between the through hole and the radially outer edge, the groove is through, a section of the through hole is larger than a section of the groove, a series are formed in the internal radial flange of the sealing ring and the spacer is fixed between the hub and the inner radial flange so that the passages are opposite said lunules, - the inner radial flange of the ring. seal is bent and comprises an axial portion adjacent to the outer radial flange, the spacer is bent and comprises a shoulder shaped to come opposite the part axial axis of the inner radial flange, and the groove of the passages extending to the shoulder of the spacer, and / or - the inner radial flange comprises a series of tongues and is fixed to the hub via said tongues, and wherein the spacer is attached to the inner radial flange so that the passages extend between two adjacent tabs.
    According to a second aspect, the invention also proposes a turbine, in particular a low-pressure turbine of a turbomachine, comprising a rotor as described above.
    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 by way of non-limiting examples and in which:
    FIG. 1 represents an example of a turbomachine to which the invention applies,
    FIG. 2 is a sectional view of a disk of a first exemplary embodiment of a rotor according to the invention,
    FIG. 3 is a sectional view of a disk of a second exemplary embodiment of a rotor according to the invention,
    FIG. 4 is a perspective view of an exemplary embodiment of a 360 ° spacer that can be used in the rotor of FIG. 3,
    FIG. 5a is a partial perspective view of the spacer of FIG. 4, positioned on an exemplary sealing ring, seen from the downstream face of the spacer,
    FIG. 5b is a view from the upstream face of the assembly of FIG. 5a, and
    Figure 6 is a perspective view of another embodiment of a spacer sector angle of less than 360 °, positioned on an exemplary sealing ring.
    DETAILED DESCRIPTION OF AN EMBODIMENT The invention will be described more 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 However, this is not limitative in that the turbine 7 could comprise a different number of stages, and that the invention is equally applicable in any rotor of a rotor. member of a turbojet, such as a high-pressure turbine 6 which can be single or multi-stage or a high pressure or low pressure compressor.
    The turbine 7 conventionally comprises one or more stages (see FIG. 1), 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 several discs 30, for example four discs 30, each of which comprises a hub 31 extending radially inward towards the 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 discs 30 of the rotor 3 can in particular be assembled coaxially by bolting. Each rotor disc 3 can be connected to an adjacent disc 30 via a ferrule 36.
    For example, as indicated in FIGS. 2 and 3, the second and third discs 30 (depending on the direction of flow of the gases in the turbomachine) each comprise a ferrule 36 which extends from its downstream radial face and which is fixed on the disk 30 immediately downstream (i.e. the third and fourth disks 30, respectively). This ferrule 36 thus delimits a radially internal cavity 8 with the hub 31 immediately downstream. The ferrule 36 may in particular be fixed by bolting.
    In what follows, the invention will be described in relation to the second and third disc 30 of the turbine 7. However, the invention applies to all the discs 30 of a turbine 7, and more particularly to the discs 30. included between the second disk 30 and the last disk 30 of the turbine 7 insofar as these disks 30 are all connected to the disk 30 immediately upstream via the ferrule 36 of the upstream disk 30.
    An annular sealing ring 20 sealing the passage of the cooling air flow F of the rims 33 of the discs 30 is further secured to each disc. In one embodiment, the sealing ring 20 can also ensure a seal between the downstream of the blade and the upstream of the blade fixed immediately upstream. For this purpose, for a given disc 30, the sealing ring 20 comprises an internal radial flange 22 fixed to the hub 31 of the disc 30 and an external radial flange 24 in contact with the rim 33 of the disc 30. The flange radial inner 22 and the outer radial flange 24 of the sealing ring 20 thus define with this disk 30 a ventilation cavity 9 of the rim 33 of the disc 30. The sealing ring 20 may conventionally include wipers .
    In the exemplary embodiment illustrated in the figures, the inner radial flange 22 of the sealing ring 20 of the third disc 30 is fixed between the ferrule 36 of the second disc 30 and the hub 31 of the third disc 30.
    In one embodiment, the ferrule 36 of the second disk 30 may comprise a substantially axial portion 36a with respect to the X axis, which extends towards the third disk 30 and delimits the internal cavity 8, and a radial portion 36b by relative to the X axis which corresponds to the free end of the shell 36 and which is fixed on the hub 31 of the third disk 30.
    In order to ventilate the rim 33 of the discs 30 of the rotor 3, a pressurized air flow F can be taken upstream of the turbine 7, typically at the high-pressure compressor 4 of the turbomachine 1, and be introduced into the cells 32 of their rim 33 to cool the discs 30. For this, the rotor 3 comprises a ventilation system for each disc 30, adapted to put in fluid communication the radially inner cavity 8 and the ventilation cavity 9. For this purpose, the rotor 3 comprises an annular spacer 40, attached and fixed between the inner radial flange 22 of the sealing ring 20 and the hub 31 of the disc 30, which comprises a series of through passages 42 axially configured to allow an injection of cooling fluid F in the ventilation cavity 9 from the radially inner cavity 8.
    The passages 42 extend substantially at least in part radially with respect to the X axis from a radially internal zone (adjacent to the X axis) to a radially outer zone (adjacent to the rim 33) of the annular spacer 40 The passages 52 thus form cooling fluid circulation channels F of the radially inner cavity 8 towards the ventilation cavity 9. In fact, the fixing of the sealing ring 20 on the hub 31 is tight, so that the pressurized air flow F can only borrow the traffic channels thus formed.
    The attachment of a spacer 40 reported thus allows to accurately calibrate the amount of cooling fluid F (pressurized air) introduced into the ventilation cavity 9, the passages 42 can be made, for example by machining, during a step distinct from the production of the disks 30 and without having to machine the disks 30 (or the sealing ring 20). The passages 42 are no longer areas of weakness of the disks 30, which allows to increase their service life, while ensuring their good cooling.
    The implementation of such a spacer 40 also makes it possible to significantly reduce the manufacturing cost of the rotor 3 in that it makes it possible to limit or even eliminate the necessary to ventilate the rim 33 and whose control was particularly expensive. In addition, the spacer 40 is easy to perform and for a lower cost. Finally, optionally, the spacer 40 makes it possible to adjust the section of the ventilation flow at each passage 42. The spacer 40 can for example be fixed by bolting (screw and nut system 35) on the hub 31 and the inner radial flange 22, through fixing holes 22c formed in said inner radial flange 22. This method of attachment can be advantageous especially when the inner radial flange 22 is itself fixed to the hub 31 by bolting, in which case it is sufficient to interpose the spacer 40 between the inner radial flange 22 and the hub 31.
    Alternatively, the spacer 40 can be attached by shrinking, screwing, clamping, etc.
    As illustrated in FIG. 6, in a first embodiment the spacer 40 may be discontinuous and comprise several sub-parts 40 'which are individually fixed between the internal radial flange 22 of the sealing ring 20 and the hub 31. , typically at the level of each bolting. In this case, the sub-parts 40 'are fixed so as to provide a space E between two adjacent sub-parts 40', said spaces E defining the passages 42 for the injection of the cooling fluid F from the radially internal cavity 8 in the ventilation cavity 9. The sub-parts 40 'may be of identical shape and size, or alternatively may be distinct in order to adjust the desired ventilation rates on a case-by-case basis.
    Alternatively, in a second embodiment illustrated in Figure 4, the spacer 40 may be continuous, that is to say monobloc and, where appropriate, formed in one piece (as illustrated in particular in Figures 4 , 5a and 5b). In this case, the passages 42 are formed in the spacer 40, for example by machining, drilling, etc.
    Each passage 42 may comprise, as illustrated in FIG. 5a, an axially traversing orifice 43 formed in the spacer 40 and opening into the internal cavity 8, that is to say at the level of the hub 31 and at a distance (radially towards the axis X of the rotor) of the ventilation cavity 9, and a groove 44, extending substantially radially with respect to the axis X from the orifice 43 and opening into the ventilation cavity 9.
    More specifically, the spacer 40 comprises a radially outer edge 46 opening into the ventilation cavity 9 and a radially inner edge 45 opening into the internal cavity 8, at the hub 31. The through orifices 43 are then formed at a distance from the two edges 45, 46, while the groove 44 is formed between the orifice 43 and the radially outer edge 46.
    The section of the groove 44 is chosen so as to allow sufficient ventilation of the discs 30 of the rotor 3 by taking a minimum of air flow upstream of the turbine 7 so as not to penalize the efficiency of the turbomachine. As a result, it is the section of the grooves 44 which is dimensioning (calibrating). The section of the orifices 43 is simply chosen to be larger than the section of the grooves 44, in order to ensure sufficient withdrawal of cooling fluid F into the internal cavity 8. In addition, optionally, the section may also be to be chosen to remain smaller than the section of the holes of the internal radial flange 22 facing to reduce the risk of error when mounting the screws in the holes. Thus, an orifice 43 whose section is lower can serve as a key. The orifices 43 also make it possible to reduce the stresses. Indeed, these orifices 43 correspond to discharge holes. By their radius, they also make it possible to reduce the tangential mechanical stresses (predominant in a rotating part) which circulate in the spacer 40 by deflecting the flow of stresses in a progressive manner. Indeed, in the case of a dry stop breaking, the flow is deflected very quickly, which generates significant mechanical stresses, harmful to the service life of the part. Note that such shapes are present in particular in the embodiment of Figure 4, wherein the spacer 40 is a continuous part and monoblock 360 °. These orifices 43 are however not necessary if the spacer 40 is in accordance with the embodiment illustrated in FIG. 6.
    The section of the grooves 44 is chosen as a function of the stage of the corresponding disc 30 (second disc 30, third disc 30, etc.), the temperature of the turbine 7, the flow of the air stream through the turbomachine etc. This choice being part of the usual work of the skilled person, it will not be detailed further here.
    The cross section of the grooves 44 may be rectangular. Such a section is indeed easy to achieve in comparison with lunules that have difficult to process and reproducible rays. Furthermore, the groove 44 may comprise a groove only (single groove 44) or be composed of several grooves, parallel or not (multiple groove 44).
    The through orifices 43 may be of circular cross 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 grooves 44 and the through holes 43 may have a different section (triangular, oval, or any other sectional shape).
    The groove 44 may be through or alternatively blind.
    Optionally, the inner radial flange 22 of the sealing ring 20 may comprise a substantially annular band 22a (FIG. 5b) from which extend a series of tongues 22b or ears serving to fix the ring of Sealing 20 on the hub 31. The strip 22a and the tabs 22b are, in one embodiment, one-piece and integral. The sealing ring 20 may be bolted to the hub 31, in which case each tab 22b includes a through hole 22c configured to receive a rod of this fastening system. The spacer 40 can then be fixed on the disc 30, between the inner radial flange 22 and the hub 31, so that each orifice 43 of a passage 42 is between two adjacent tabs 22b. In this embodiment, the orifices 43 of the passages 42 thus open on both sides into the internal cavity 8.
    In the exemplary embodiment illustrated in the figures, the sealing ring 20 comprises, between the outer radial flange 24 and the inner radial flange 22, a substantially axial flange 23, which forms a bend with the internal radial flange 22. The hub 31 further comprises, at this axial flange 23, an annular projection 38 which is opposite (FIG. 2) and bears against (FIG. 3) said axial flange 23.
    In this case, the spacer 40 also comprises a bent portion 48 whose shape and dimensions respectively correspond to the shape and dimensions of the bend of the sealing ring 20, so as to conform to the shape of the internal radial flange. 22 and the axial flange 23 and at least partially cover the axial flange 23. This configuration thus allows the introduction of the cooling fluid F into the ventilation cavity 9 despite the presence of the annular projection 38 of the hub 31 (see figures 2 and 3). For this purpose, the spacer 40 may comprise an annular plate 47, fastened along the internal radial flange 22, and a shoulder 48 extending from the annular plate 47 so as to face the axial flange 23. radially outer edge 46 of the spacer 40 then corresponds to the edge of the shoulder 48 and extends facing the radially outer surface of the axial flange 23 so that the passage 42 opens well into the ventilation cavity 9. Thus, in the case where the passage 42 comprises a groove 44, said groove 44 can be formed in the annular plate 47 and in the shoulder 48 of the spacer 40 and extend as far as its edge 46.
    Optionally, lunules 26 (FIGS. 3 and 5a), participating in the injection of cooling fluid F into the ventilation cavity 9, can also be formed in the sealing ring 20, more precisely in a portion of the sealing ring 20 which faces the spacer 40.
    These lunules 26 may then have a larger section than the section of the passages 42 of the spacer 40, thus increasing their manufacturing tolerance. It is then the section of the passages 42 formed in the spacer 40 which is dimensioning (or calibrating) for the amount of cooling fluid F injected into the ventilation cavity 9, via the lunules 26. The cross section of the lunules 26 can therefore be chosen to be larger than the cross section of the passages 42, to bring the pressurized air flow F passages 42 to the ventilation cavity 9.
    The lobes 26 are formed in the downstream face of the inner radial flange 22 (Figure 5a).
    When the sealing ring 20 comprises an axial flange 23, the lunettes 26 may also be formed in the axial flange 23 to open into the ventilation cavity 9 and to allow the passage 42 of the cooling fluid F.
    In this case, the spacer 40 may either extend only along the inner radial flange 22 and be substantially flat, or comprise a bent portion (shoulder 48) of shape corresponding to the shape of the bend of the ring of tightness 20.
    The lobes 26 may be obtained by milling in the mass of the inner radial flange 22 (and optionally the axial flange 23). The spacer 40 may include an anti-rotation stop, configured to prevent the spacer 40 (or the sub-portions 40 'of spacer 40) from rotating during operation of the rotor 3. For example, in the case where the spacer 40 comprises a shoulder 48, said shoulder 48 limits the radial movements of the spacer 40 and thus form an anti-rotation stop.
    Optionally, the spacer 40 may have one or more of the following features: - Additional machining may be formed in the spacer 40 to meet weight gain objectives. - Scallops or any other shape configured to reduce stresses in the spacer 40 may be formed with the spacer 40, - The passages 42 may have, within the same spacer 40, different sections to modify the amount of air injected into the ventilation cavity 9 according to their angular position about the axis X of the rotor 3. Such a configuration may prove advantageous, for example when the distribution of the fastening bolts of the sealing ring 20 on the hub 31 is heterogeneous or if the fan specifications of the rotor 3 change. - The spacer 40 may be multi-stage, that is to say include several plates placed against each other so as to overlap. - The spacer 40 may be thin and have a thickness of about 1 mm when made of a nickel-based super alloy type material. It is therefore easy to insert between the radial flange and the hub 31, compact and does not penalize the overall mass of the rotor 3.
    It will be noted that the ventilation spacer 40 of the invention can be applied to other parts of a turbomachine requiring calibrated ventilation, and is not limited to its application to a rotor of a turbine.
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    1. Rotor (3) of a member (7) of a turbomachine (1), for example rotor of a turbine (7), said rotor (3) comprising: - a first element (30), - a second element (20), defining with the first element a ventilation cavity (9), the rotor (3) being characterized in that it further comprises a spacer (40), attached and fixed between the first element (30) and the second element (20) and comprising a series of through passages (42) configured to allow injection of cooling fluid (F) into the ventilation cavity (9).
    [2" id="c-fr-0002]
    The rotor (3) according to claim 1, wherein the first member (30) comprises an annular disk (30) comprising a hub (31) and a rim (33), said rim (33) being configured to receive blades (34) of the organ.
    [3" id="c-fr-0003]
    The rotor of claim 2, wherein the second member (20) comprises a sealing ring (20) comprising an inner radial flange (22) attached to the hub (31) and an outer radial flange (24) in contact with the rim (33), the sealing ring (20) defining with the disc (30) the ventilation cavity (9) of the rim (33).
    [4" id="c-fr-0004]
    4. Rotor according to claims 2 and 3 taken in combination, wherein the spacer (40) is annular, and wherein said spacer (40) is attached and fixed between the inner radial flange (22) and the hub (31) of the disc (30).
    [5" id="c-fr-0005]
    5. Rotor (3) according to claim 4, wherein the spacer (40) is discontinuous and comprises a plurality of sub-parts (40 ') fixed between the inner radial flange (22) and the hub (31), the passages ( 42) being obtained by leaving a space (E) between two adjacent sub-parts (40 ').
    [6" id="c-fr-0006]
    6. Rotor (3) according to one of claims 4 or 5, wherein each passage (42) comprises a through hole (43) formed in the spacer (40) and opening at the hub (31), to distance from the ventilation cavity (9).
    [7" id="c-fr-0007]
    7. Rotor (3) according to claim 6, wherein the spacer (40) comprises a radially outer edge (46) opening into the ventilation cavity (9) and a radially inner edge (45) opening at the hub ( 31), away from the ventilation cavity (9), and each passage (42) further comprises a groove (44) extending between the through hole (43) and the radially outer edge (46).
    [8" id="c-fr-0008]
    8. Rotor (3) according to claim 7, wherein the groove (44) is through.
    [9" id="c-fr-0009]
    9. Rotor (3) according to one of claims 7 or 8, wherein a section of the through hole (43) is larger than a section of the groove (44).
    [10" id="c-fr-0010]
    10. Rotor (3) according to one of claims 7 to 9, wherein a series of lunettes (26) are formed in the inner radial flange (22) of the sealing ring (20) and the spacer ( 40) is fixed between the hub (31) and the inner radial flange (22) so that the passages (42) are opposite said lunules (26).
    [11" id="c-fr-0011]
    11. Rotor (3) according to one of claims 7 to 10, wherein: - the inner radial flange (22) of the sealing ring (20) is bent and comprises an axial portion (23) adjacent to the external radial flange (24), - the spacer (40) is bent and comprises a shoulder (48) shaped to face the axial portion (23) of the inner radial flange (22), and - the groove (44). ) passages (42) extending to the shoulder (48) of the spacer (40).
    [12" id="c-fr-0012]
    12. Rotor (3) according to one of claims 4 to 11, wherein the inner radial flange (22) comprises a series of tongues (22b) and is fixed on the hub (31) via said tabs (22b). ), and wherein the spacer (40) is attached to the inner radial flange (22) so that the passages (42) extend between two adjacent tabs (22b).
    [13" id="c-fr-0013]
    13. Turbine (7), in particular a turbine (7) low pressure of a turbomachine, comprising a rotor (3) according to one of claims 1 to 12.
    类似技术:
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    同族专利:
    公开号 | 公开日
    CN108884714B|2021-08-31|
    WO2017158304A1|2017-09-21|
    FR3048998B1|2019-12-13|
    US20190085699A1|2019-03-21|
    CN108884714A|2018-11-23|
    EP3430238A1|2019-01-23|
    EP3430238B1|2020-01-08|
    US10934846B2|2021-03-02|
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    US6185925B1|1999-02-12|2001-02-13|General Electric Company|External cooling system for turbine frame|
    DE50306044D1|2003-09-05|2007-02-01|Siemens Ag|Shovel of a turbine|
    FR2948726B1|2009-07-31|2013-07-05|Snecma|AUBES WHEEL COMPRISING IMPROVED COOLING MEANS|
    FR2967453B1|2010-11-17|2012-12-21|Snecma|AUBES RETENTION DISC|
    US20120134782A1|2010-11-30|2012-05-31|Creston Lewis Dempsey|Purge systems for rotary machines and methods of assembling same|
    FR3019584B1|2014-04-07|2019-05-17|Safran Aircraft Engines|SYSTEM FOR VENTILATION OF A TURBINE USING CROSSING ORIFICES AND LUNULES|FR3092861A1|2019-02-18|2020-08-21|Safran Aircraft Engines|TURBOMACHINE ASSEMBLY WITH A CLAMP ON A SEALING RING|
    法律状态:
    2017-03-14| PLFP| Fee payment|Year of fee payment: 2 |
    2017-09-22| PLSC| Publication of the preliminary search report|Effective date: 20170922 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 6 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1652234A|FR3048998B1|2016-03-16|2016-03-16|TURBINE ROTOR COMPRISING A VENTILATION SPACER|
    FR1652234|2016-03-16|FR1652234A| FR3048998B1|2016-03-16|2016-03-16|TURBINE ROTOR COMPRISING A VENTILATION SPACER|
    US16/085,408| US10934846B2|2016-03-16|2017-03-16|Turbine rotor comprising a ventilation spacer|
    PCT/FR2017/050614| WO2017158304A1|2016-03-16|2017-03-16|Turbine rotor comprising a ventilation spacer|
    CN201780022818.5A| CN108884714B|2016-03-16|2017-03-16|Turbine rotor including a ventilation spacer|
    EP17716567.7A| EP3430238B1|2016-03-16|2017-03-16|Turbine rotor comprising a ventilation spacer|
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