• 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:
    A turbomachine turbine (1) comprising a casing (4) and a turbine distributor stage (2), the turbine distributor stage (2) being made of a ceramic matrix composite material and having a plurality of sectors (20). annular ring forming an inner ring (240) and an outer shell (260), each annular sector (20) having an inner platform (24) forming a portion of the inner shell (240), an outer platform (26) forming a portion of the outer shell (260), and at least one blade (28) extending between the outer platform (26) and the inner platform (24) and integral therewith, said blade (28) having a hollow profile defining an inner housing (280) extending between the inner platform (24) and the outer platform (26), and the inner and outer platforms (26, 28) each having an orifice (245, 265) communicating with said housing (280) internal to the blade (28). Each annular sector (20) of the distributor stage (2) comprises at least one mast (6) passing through said openings (245, 265) of the platforms and the internal housing (280) of said at least one blade (28), said mast being fixed to said housing (4) on the one hand and in connection with said annular sector (20) on the other hand, and two pins (63).
    公开号:FR3061929A1
    申请号:FR1762338
    申请日:2017-12-18
    公开日:2018-07-20
    发明作者:Lucien Henri Jacques QUENNEHEN；Sebastien Serge Francis CONGRATEL；Nicolas Paul TABLEAU；Matthieu Arnaud GIMAT；Clement Marie Benoit ROUSSILLE
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    @ Holder (s): SAFRAN AIRCRAFT ENGINES.
    ® Agent (s): CABINET BEAU DE LOMENIE.
    FR 3 061 929 - A1 ® TURBOMACHINE TURBINE COMPRISING A CERAMIC MATRIX.
    @) A turbine engine turbine (1) comprising a casing (4) and a turbine distributor stage (2), the turbine distributor stage (2) (1) being of composite material with ceramic matrix and comprising a plurality of sectors (20) annulars forming a crown having an interior ferrule (240) and an exterior ferrule (260), each annular sector (20) having an interior platform (24) forming a part of the interior ferrule (240), an exterior platform ( 26) forming a part of the outer shell (260), and at least one blade (28) extending between the outer platform (26) and the inner platform (24) and integral with these, said blade (28) having a hollow profile defining an internal housing (280) extending between the interior platform (24) and the exterior platform (26), and the interior and exterior platforms (26, 28) each having a communicating orifice (245, 265) with said internal housing (280) of the blade (28).
    Each annular sector (20) of the distributor stage (2) comprises at least one mast (6) passing through said orifices (245, 265) of the platforms and the internal housing (280) of said at least one blade (28), said mast being fixed to said casing (4) on the one hand and in connection with said annular sector (20) on the other hand, and two pins (63).
    COMPOSITE MATERIAL A DISTRIBUTOR

    Invention background
    The invention relates to turbomachines, in particular aeronautical turboshaft engines or industrial turbines, and more particularly a turbine distributor stage made of composite material with ceramic matrix or matrix at least partially made of ceramic, hereinafter referred to as CMC material.
    The field of application of the invention is in particular that of aeronautical gas turbine engines. The invention is however applicable to other turbomachinery, for example industrial turbines.
    Improving the performance of turbomachinery and reducing their polluting emissions leads to consider increasingly higher operating temperatures.
    For elements of hot parts of turbomachines, it has therefore been proposed to use composite materials with a ceramic matrix denoted CMC thereafter.
    CMC materials are typically formed from a fibrous reinforcement of refractory fibers, such as carbon or ceramic fibers, densified by a ceramic matrix or at least partially ceramic.
    These materials have remarkable thermo-structural properties, that is to say mechanical properties which make them capable of constituting structural elements and the ability to maintain these properties at high temperatures. In addition, CMC materials have a density much lower than that of metallic materials traditionally used for elements of hot parts of turbomachines.
    Thus, the documents WO 2010/061140, WO 2010/116066 and WO 2011/080443 describe the production of blades of movable wheels of turbomachines in CMC with integrated platform and heel. The use of CMC materials for turbine distributors has also been proposed, in particular in documents WO 2010/146288, FR 2 979 662 and EP 2 443 318.
    A traditional metal turbine distributor stage has a crown shape made up of several assembled sectors, each sector comprising an interior platform, an exterior platform and a plurality of blades extending between the interior and exterior platforms and integral with them. The juxtaposed interior platforms form an interior ferrule and the juxtaposed exterior platforms form an exterior ferrule. The interior and exterior ferrules delimit the gas flow stream in the distributor stage.
    Introducing a distributor stage, for example a high pressure distributor stage, in CMC makes it possible to increase the maximum tolerated temperature compared to a metallic distributor stage, and thus to decrease the amount of cooling air used. This thus makes it possible to increase the performance of the turbomachine.
    However, CMC, by its very different properties from metal, is more sensitive to certain mechanical stresses. In fact, the CMC has greater rigidity and lower expansion. It behaves better in compression, but its admissible tensile stresses are lower than those of metal.
    In addition, the integration in a metallic environment of a CMC part is delicate because of the differential thermal expansions between the CMC and the metal. This is all the more delicate in a turbomachine, and more particularly in a high-pressure part of the turbomachine, because the environment is very hot, which exacerbates the differences in coefficients of thermal expansion between the materials, the aerodynamic forces undergone by a high pressure distributor stage being also very high in this turbine zone.
    A high pressure distributor stage is known, comprising annular sectors maintained in position, on the one hand, by means of two pins passing through a round hole and an oblong hole produced in a lower portion of the interior platform, the lower portion s extending in a radial direction from an inner face of the inner ferrule formed by the distributor stage, and, on the other hand, by means of a stopper mounted on an outer face of the outer platform, the upper portion s extending from the outer platform in the radial direction of the annular crown.
    This architecture generates an integration constraint because it is impossible to hang the annular sectors from above, that is to say to hang them on the external casing.
    The blade of a distributor is subjected to significant efforts from the combustion gases. When the distributor is hung from above, that is to say by the casing, or from below, the combustion gases put the blade in bending and are therefore sources of stress.
    It is known from documents US 2008/279679 and EP 3 009 601 of turbines provided with a distributor stage having annular sectors, the blades of which are crossed by masts coupled to the casing.
    Subject and summary of the invention
    The invention aims to overcome the above drawbacks and to overcome the difficulties mentioned above by proposing a turbomachine turbine comprising a turbine distributor stage in CMC, the mounting of which is simplified and adapted to maintain the annular sectors in a deterministic manner. while allowing the annular sector to deform independently of the metallic parts at the interface.
    An object of the invention provides a turbomachine turbine comprising a casing and a turbine distributor stage, the turbine distributor stage being made of a ceramic matrix composite material and comprising a plurality of annular sectors forming a crown having an inner ferrule, a outer ferrule, each annular sector having an inner platform forming a part of the inner ferrule, an outer platform forming a part of the outer ferrule, and at least one blade extending between the outer platform and the inner platform and integral with these ci, and the metal ring comprising at least one at least partially annular sector, said blade having a hollow profile defining an internal housing extending between the interior platform and the exterior platform, and the interior and exterior platforms each having a communicating orifice with internal blade housing.
    According to a general characteristic of the invention, each annular sector of the distributor stage comprises a mast passing through said orifices of the platforms and the internal housing of the blade, the mast being fixed to said casing on the one hand and in connection with said annular sector. on the other hand.
    The mast makes it possible to provide a means of fixing an annular sector of a distributor stage in CMC from above, that is to say to the casing, while minimizing the bending moment, insofar as the length of bending is reduced by about half by the mast crossing the annular sector.
    Each annular sector of the dispenser stage is thus maintained in a deterministic manner, that is to say so as to avoid that the annular sector starts to vibrate and by controlling its position, and this while allowing the annular sector to deform under the effects of temperature and pressure, among other things, independently of the interfaced metal parts.
    According to a first aspect of the turbine, the turbine further comprises a sleeve fitted into the internal housing of the blade and fixed to the mast to hold the blade in position.
    The sleeve defines a ball joint making it possible to minimize the force due to the aerodynamic moment without modifying the integration of the ring sector in the turbine. Indeed, the ball joint formed by the sleeve fixed inside the blade leaves the blade free to move around the axis defined by the mast.
    According to a second aspect of the turbine, the turbine further comprises first and second pins, the inner platform comprising a portion projecting inwardly from the crown of the distributor stage having a first circular orifice configured to receive the first pin and a second oblong hole configured to receive the second pin, the mast further comprising a third and a fourth circular holes, the first pin passing through the first hole and the third hole and the second pin passing through the second hole and the fourth hole for fix the mast to the annular sector.
    The oblong shape of the second opening allows differential expansion between the mat and the annular sector.
    According to an embodiment of the second aspect of the turbine, the external platform can comprise a stop extending projecting from the face of the external platform opposite the casing in the direction of the casing, and the casing can comprise an annular rib s' extending projecting towards the external platform and cooperating with said stop.
    The stop and the rib make it possible to prevent the annular sector from tilting around the axis between the two pins under the force of the gases.
    In a third aspect of the turbine, the mast is made of metallic material so as to offer good mechanical strength, the mast taking up all the aerodynamic forces to transfer them to the casing.
    The mast can be made of any other material.
    In a fourth aspect of the turbine, which the mast is made in one piece with the casing. Alternatively, the mat can be screwed, or welded to the housing.
    In a fifth aspect of the turbine, which each annular sector comprises a plurality of blades and a mast for each blade of the annular sector.
    The invention also relates to a turbomachine comprising at least one turbomachine turbine as defined above.
    Another subject of the invention is also an aircraft comprising at least one turbomachine as defined above.
    Brief description of the drawings.
    The invention will be better understood on reading the following, for information but not limitation, with reference to the accompanying drawings in which:
    - Figure 1 is a schematic sectional view of a portion of a turbomachine turbine according to a first embodiment of the invention;
    - Figure 2 shows schematically a top view of the turbine portion of Figure 1;
    - Figure 3 is a schematic sectional view of a portion of a turbomachine turbine according to a second embodiment of the invention.
    Detailed description of embodiments
    Figures 1 and 2 are respectively illustrated a schematic sectional view and a schematic top view of a turbomachine turbine according to a first embodiment of the invention.
    A high pressure turbine 1 of a turbomachine, for example an aeronautical turbine engine, as shown partially in FIG. 1, comprises a plurality of fixed distributor stages 2 which alternate with moving wheels 3 in the flow direction, indicated by an arrow in FIG. 1, of the gas flow F in the turbine 1 and which are mounted in a turbine casing 4.
    Each movable wheel 3 comprises a plurality of vanes 32 having an inner ferrule 34, and at least one blade 38 extending from the inner ferrule 34 and linked to the latter. On the inner side of the inner ferrule 34, the blade is extended by a foot engaged in a housing for a disc 33. On the outer side, the top of the blades 32 is facing an abradable material carried by a ring 36 for sealing the tops of the blades 32.
    Throughout the present text, the terms “interior” and “exterior” are used with reference to the position or the orientation relative to the axis of rotation X of the turbine 1.
    The blades 32 can be traditional metal blades or blades made of CMC material obtained for example as described in documents WO 2010/061140, WO 2010/116066, WO 2011/080443.
    At least one of the distributor stages, such as the distributor stage 2 of FIG. 1, is formed by joining together several annular sectors 20 of CMC material as illustrated in FIG. 2 which presents a perspective view of the turbine portion of Figure 1.
    Each annular sector 20 of the distributor stage 2 comprises an interior platform 24, an exterior platform 26 and a blade 28 extending between the interior and exterior platforms 24 and 26 and integral with these. As a variant, several blades could extend between the interior and exterior platforms of the same distributor sector. Once assembled with the casing 4 of the turbine 1, the sectors 20 form a single ring of distributors 2 having an internal ferrule 240 formed by the juxtaposition of the internal platforms 24 of the sectors 20 and an external ferrule 260 formed by the juxtaposition of the external platforms 26 of sectors 20.
    The inner ferrule 240 of the distributor stage 2 has an outer surface 24e and an inner surface 24i, and the outer ferrule 260 of the distributor stage 2 also has an outer surface 26e and an inner surface 26i. The sectors 20 forming the distributor stage 2, the interior platform 24 of each section 20 therefore has a portion of the exterior surface 24e and a portion of the interior surface 24i of the exterior shroud 240, and the exterior platform 26 of each sector 20 also has a portion of the outer surface 26e and a portion of the inner surface 26i of the inner shroud 260. The blade 28 of each sector 20 extends between the outer surface 24e of the inner shroud 240 and the inner surface 26i of the outer ferrule 260, and more particularly between the corresponding outer surface portion 24e and the corresponding inner surface portion 24i.
    The outer surfaces 24e and 34e of the inner ferrules 240 and 34 of the distributor stage 2 and of the movable wheels 3 and the inner surfaces 26i and 36i of the outer ferrule 260 of the distributor stage 2 and of the sealing ring 36 mobile wheels 3 delimit a stream 45 for the flow of gas flow F in the turbine 1.
    Throughout the text, the terms “upstream” and “downstream” are used with reference to the direction of flow of gas flow F in the stream 45 indicated by an arrow.
    Each blade 28 has a hollow profile having an inner housing 280 extending over the entire height of the blade 28, that is to say between the inner platform 24 and the outer platform 26 of the annular sector. The inner platform 24 of each annular section 20 includes an orifice 245 whose shape corresponds to the section of the inner housing 280 in the plane in which the inner platform extends 24. Similarly, the outer platform 26 of each annular section 20 comprises an orifice 265 whose shape corresponds to the section of the interior housing 280 in the plane in which the interior platform extends 26. The orifices 245 and 265 of the interior 24 and exterior platforms 26 are produced in the extension of the interior housing 280 of the blade 28.
    The turbine 1 also comprises, for each annular sector 20, a mast 6 welded to the casing 4 and extending in the radial direction, towards the axis of revolution of the turbine 1 which corresponds to the axis of revolution of the casing 4 The mast 6 is configured to pass through the orifices 245 and 265 of the internal 24 and external 26 and the internal housing 280 of the corresponding blade 28.
    In the case where each annular sector comprised several blades, the turbine would comprise, at most, a corresponding number of masts for each annular distributor sector.
    In this first embodiment illustrated in Figures 1 and 2, each blade 28 further comprises a sleeve 62 inserted and fixed inside the interior housing 280. The sleeve 62 is configured to be traversed by the mast 6 without blocking it in rotation about the axis of revolution of the mast 6. The sleeve 62 thus defines a ball joint with the mast 6 which makes it possible to stiffen the blade 28 in the radial plane of the turbine 1.
    The assembly is carried out by fixing one by one each annular sector 20 on the corresponding mast 6 of the casing 4 and by maintaining the annular sectors 20 thus mounted in position using a specific tool until all the annular sectors 20 are mounted and form an annular distribution ring.
    In Figure 3 is illustrated a schematic sectional view of a portion of a turbomachine turbine according to a second embodiment of the invention.
    The elements identical to the first embodiment illustrated in FIGS. 1 and 2 bear the same numerical references.
    The second embodiment differs from the first embodiment in that, for each annular sector 20 of the distributor stage 2, the connection between the mast 6 and the annular sector 20 is carried out not with a sleeve, but at the using a first counter 63 and a second counter not visible in the sectional view of FIG. 3 since it is hidden by the first counter 63.
    In this embodiment, the interior platform 24 of each annular sector 20 has a portion 242 projecting from its interior surface 24i towards the interior of the crown of the distributor stage.
    2. The projecting portion 242 has a first circular orifice 244 configured to receive the first pin 63 and a second oblong orifice configured to receive the second pin.
    The mast 6 further comprises a third circular orifice 66 and a fourth circular orifice, the first pin 63 passing through the first orifice 244 and the third orifice 66 and the second pin passing through the second orifice and the fourth orifice to fix the mast 6 to the sector ring finger 20.
    Furthermore, as illustrated in FIG. 3, the first and second pins 63 also pass respectively through a first and a second orifice of an internal metal ring 5 to fix the metal ring to the distributor stage 2.
    The outer platform 26 of the annular sector 20 further comprises a stop 7 extending projecting from the outer surface 26e of the outer platform 26 in the direction of the casing 4, and the casing 4 comprises an annular rib 8 projecting towards the outer platform 26, that is to say towards the inside of the crown of the turbine 1, and cooperating with the stop 7.
    The stop 7 and the rib 8 thus make it possible to prevent the annular sector 20 from rocking around the axis between the two pins 63 under the force of the gases. The pins 63 and the stop 7 with the rib 8 make it possible to position the blade 28 of the distributor 2 radially and tangentially and to stiffen the blade 28 in the radial plane of the turbine. Under the effect of the gas force, the sector will tilt around the axis formed by the first and second round and oblong holes 244. The stop will then prevent the distributor from tipping over.
    The invention thus provides a turbomachine turbine comprising a turbine distributor stage in CMC, the assembly of which is simplified and adapted to maintain the annular sectors in a deterministic manner while allowing the annular sector to deform independently of the metallic parts at the interface.
    权利要求:
    Claims (7)
    [1" id="c-fr-0001]
    1. Turbine (1) of a turbomachine comprising a casing (4) and a turbine distributor stage (2), the turbine distributor stage (2) (1) being of composite material with ceramic matrix and comprising a plurality of sectors ( 20) annulars forming a crown having an interior ferrule (240) and an exterior ferrule (260), each annular sector (20) having an interior platform (24) forming a part of the interior ferrule (240), an exterior platform (26 ) forming a part of the outer shell (260), and at least one blade (28) extending between the outer platform (26) and the inner platform (24) and integral with these, said blade (28) having a hollow profile defining an internal housing (280) extending between the interior platform (24) and the exterior platform (26), and the interior and exterior platforms (24, 26) each having an orifice (245, 265) communicating with said internal housing (280) of the p ale (28), characterized in that each annular sector (20) of the distributor stage (2) comprises at least one mast (6) passing through said orifices (245, 265) of the platforms and the internal housing (280) of said au at least one blade (28), said mast being fixed to said casing (4) on the one hand and in connection with said annular sector (20) on the other hand, and a first and a second pin (63), the inner platform ( 24) comprising a portion (242) projecting inwardly from the crown of the distributor stage (2) having a first circular orifice (244) configured to receive the first pin (63) and a second oblong orifice configured to receive the second pin, the mast (6) further comprising a third hole (66) and a fourth circular hole, the first pin (63) passing through the first hole (244) and the third hole (66) and the second pin passing through the second orifice and the fourth orifice for fixing the mast (6) to the annular sector (20).
    [2" id="c-fr-0002]
    2. Turbine (1) according to claim 1, in which the external platform (26) comprises a stop (7) projecting from the face (24e) of the external platform (26) opposite the casing (4) towards the casing (4), and the casing (4) comprises an annular rib (8) projecting towards the external platform (26) and cooperating with said stop (7).
    [3" id="c-fr-0003]
    3. Turbine (1) according to one of claims 1 or 2, in which the mast (6) is made of metallic material.
    [4" id="c-fr-0004]
    4. Turbine (1) according to one of claims 1 to 3, wherein the mast (6) is made in one piece with the housing (4).
    10
    [5" id="c-fr-0005]
    5. Turbine (1) according to one of claims 1 to 4, wherein each annular sector (20) comprises a plurality of blades (28) and a mast (6) for each blade (28) of the annular sector (20) .
    [6" id="c-fr-0006]
    6. Turbomachine comprising at least one turbine (1) for a turbomachine according to one of claims 1 to 5.
    [7" id="c-fr-0007]
    7. An aircraft comprising at least one turbomachine according to claim 6.
    I
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    同族专利:
    公开号 | 公开日
    US10738635B2|2020-08-11|
    FR3061928B1|2019-11-15|
    US20180202302A1|2018-07-19|
    FR3061928A1|2018-07-20|
    FR3061929B1|2019-04-12|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20080279679A1|2007-05-09|2008-11-13|Siemens Power Generation, Inc.|Multivane segment mounting arrangement for a gas turbine|
    EP3009601A1|2014-09-30|2016-04-20|United Technologies Corporation|Airfoil assembly with spacer and tie-spar|
    US5272869A|1992-12-10|1993-12-28|General Electric Company|Turbine frame|
    US6884030B2|2002-12-20|2005-04-26|General Electric Company|Methods and apparatus for securing multi-piece nozzle assemblies|
    US9617870B2|2013-02-05|2017-04-11|United Technologies Corporation|Bracket for mounting a stator guide vane arrangement to a strut in a turbine engine|
    US9915159B2|2014-12-18|2018-03-13|General Electric Company|Ceramic matrix composite nozzle mounted with a strut and concepts thereof|
    US10370986B2|2015-07-24|2019-08-06|General Electric Company|Nozzle and nozzle assembly for gas turbine engine|
    US10309240B2|2015-07-24|2019-06-04|General Electric Company|Method and system for interfacing a ceramic matrix composite component to a metallic component|DE102017221669A1|2017-12-01|2019-06-06|MTU Aero Engines AG|Support device for a housing of a turbomachine, housing for a turbomachine and turbomachine|
    FR3093128B1|2019-02-25|2021-05-14|Safran Aircraft Engines|Turbomachine housing|
    US11028728B2|2019-03-22|2021-06-08|Raytheon Technologies Corporation|Strut dampening assembly and method of making same|
    US11008880B2|2019-04-23|2021-05-18|Rolls-Royce Plc|Turbine section assembly with ceramic matrix composite vane|
    FR3097264B1|2019-06-12|2021-05-28|Safran Aircraft Engines|Turbomachine turbine with CMC distributor with load recovery|
    FR3098246A1|2019-07-04|2021-01-08|Safran Aircraft Engines|Turbomachine turbine with CMC distributor with load recovery|
    FR3102795A1|2019-10-31|2021-05-07|Safran Aircraft Engines|Turbomachine turbine with CMC distributor with load recovery|
    FR3108673A1|2020-03-27|2021-10-01|Safran Aircraft Engines|TURBINE OF TURBOMACHINE WITH DISTRIBUTOR IN CMC WITH BLENDING OF FULL MATS AT THE CROWN|
    FR3109961A1|2020-05-06|2021-11-12|Safran Aircraft Engines|Improved CMC distributor for turbomachine turbine|
    法律状态:
    2018-01-22| PLFP| Fee payment|Year of fee payment: 2 |
    2018-07-20| PLSC| Publication of the preliminary search report|Effective date: 20180720 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 5 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1750375A|FR3061928B1|2017-01-18|2017-01-18|TURBOMACHINE TURBINE COMPRISING A DISPENSING STAGE OF CERAMIC MATRIX COMPOSITE MATERIAL|
    FR1750375|2017-01-18|
    FR1762338A|FR3061929B1|2017-01-18|2017-12-18|TURBOMACHINE TURBINE COMPRISING A DISPENSING STAGE OF CERAMIC MATRIX COMPOSITE MATERIAL|FR1762338A| FR3061929B1|2017-01-18|2017-12-18|TURBOMACHINE TURBINE COMPRISING A DISPENSING STAGE OF CERAMIC MATRIX COMPOSITE MATERIAL|
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