• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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  • 优先权
    • 专利摘要:
    A turbine ring assembly comprising CMC ring sectors (10) forming a ring (1) and a ring support structure (3), each sector (10) having an annular base (12) with, in a radial direction (DR), an inner face (12a) and an outer face (12b) from which two attachment tabs (14, 16) extend between two radial tabs of the structure (3). The assembly comprises, for each sector (10), at least two pins (19, 20) cooperating with one of the attachment tabs (14, 16) and the corresponding radial tab, and at least one peg (20, 19) cooperating with the other hooking lug (16, 14) and the corresponding radial lug. The first radial tab comprises a first annular radial portion (32) integral with the structure (3), a second removable annular radial portion extending radially towards the center of the ring (1) on a larger portion than said first portion radial ring (32), the portion extending beyond the first annular radial portion (32) having orifices (3350) for receiving one of the pins (19).
    公开号:FR3055147A1
    申请号:FR1657826
    申请日:2016-08-19
    公开日:2018-02-23
    发明作者:Lucien Henri Jacques QUENNEHEN；Sebastien Serge Francis CONGRATEL；Clement Jean Pierre DUFFAU；Nicolas Paul TABLEAU
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    © Publication no .: 3055147 (use only for reproduction orders)
    ©) National registration number: 16 57826 ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY
    COURBEVOIE © Int Cl 8 : F 01 D 25/24 (2017.01), F 01 D 11/08, 11/18, 9/04
    A1 PATENT APPLICATION
    ©) Date of filing: 19.08.16. © Applicant (s): SAFRAN AIRCRAFT ENGINES (© Priority: Simplified joint stock company - FR. @ Inventor (s): QUENNEHEN LUCIEN HENRI JACQUES, CONGRATEL SEBASTIEN SERGE (43) Date of public availability of the FRANCIS, DUFFAU CLEMENT JEAN PIERRE and request: 23.02.18 Bulletin 18/08. NICOLAS PAUL PAINTING. ©) List of documents cited in the report preliminary research: Refer to end of present booklet (© References to other national documents ® Holder (s): SAFRAN AIRCRAFT ENGINES Company related: by simplified actions. ©) Extension request (s): © Agent (s): CABINET BEAU DE LOMENIE.
    FR 3 055 147 - A1 (04 TURBINE RING ASSEMBLY.
    ©) A turbine ring assembly comprising ring sectors (10) in CMC forming a ring (1) and a ring support structure (3), each sector (10) having an annular base (12) with, in a radial direction (D r ), an internal face (12a) and an external face (12b) from which extend two attachment tabs (14, 16) held between two radial tabs of the structure (3) . The assembly includes, for each sector (10), at least two pins (19,20) cooperating with one of the hooking lugs (14, 16) and the corresponding radial tab, and at least one pin (20, 19) cooperating with the other hooking tab (16, 14) and the corresponding radial tab.
    The first radial tab comprises a first annular radial portion (32) integral with the structure (3), a second removable annular radial portion extending radially towards the center of the ring (1) over a larger part than said first portion radial annular (32), the part extending beyond the first annular radial portion (32) having orifices (3350) for receiving one of the pins (19).

    Invention background
    A turbine ring assembly includes a plurality of ring sectors of ceramic matrix composite material and a ring support structure.
    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.
    In the case of entirely metallic turbine ring assemblies, it is necessary to cool all the elements of the assembly and in particular the turbine ring which is subjected to the hottest flows. This cooling has a significant impact on engine performance since the cooling flow used is taken from the main flow of the engine. In addition, the use of metal for the turbine ring limits the possibilities of increasing the temperature at the turbine, which would however improve the performance of aeronautical engines.
    In order to try to solve these problems, it has been envisaged to produce turbine ring sectors in ceramic matrix composite material (CMC) in order to dispense with the use of a metallic material.
    CMC materials have good mechanical properties making them suitable for constituting structural elements and advantageously retain these properties at high temperatures. The use of CMC materials has advantageously made it possible to reduce the cooling flow to be imposed during operation and therefore to increase the performance of the turbomachines. In addition, the use of CMC materials advantageously makes it possible to reduce the mass of the turbomachines and to reduce the effect of hot expansion encountered with metal parts.
    However, the existing solutions proposed can implement an assembly of a CMC ring sector with metal attachment parts of a ring support structure, these attachment parts being subjected to the hot flow. Consequently, these metal attachment parts undergo hot expansion, which can lead to mechanical stressing of the ring sectors in CMC and to embrittlement of the latter.
    The documents FR 2 540 939, GB 2 480 766, EP 1 350 927, US 2014/0271145, US 2012/082540 and FR 2 955 898 which disclose turbine ring assemblies are also known.
    There is a need to improve the existing turbine ring assemblies using CMC material in order to reduce the intensity of the mechanical stresses to which the CMC ring sectors are subjected during operation of the turbine.
    Subject and summary of the invention
    The invention aims to propose a set of turbine rings allowing the maintenance of each ring sector in a deterministic manner, that is to say so as to control its position and prevent it from vibrating. on the one hand, while allowing the ring sector, and by extension to the ring, to deform under the effects of temperature rises and pressure variations, and this in particular independently of the metal parts at the interface, and , on the other hand, while improving the seal between the non-vein sector and the vein sector and simplifying handling and reducing their number for mounting the ring assembly.
    An object of the invention provides a turbine ring assembly comprising a plurality of ring sectors of ceramic matrix composite material forming a turbine ring and a ring support structure, each ring sector having, according to a section plane defined by an axial direction and a radial direction of the turbine ring, an annular base portion with, in the radial direction of the turbine ring, an internal face defining the internal face of the turbine and an external face from which extend a first and a second hooking tabs, the ring support structure comprising a first and a second radial tabs between which the first and second hooking tabs are held each ring sector, and the ring assembly comprising, for each ring sector, at least three pins for radially maintaining the ring sector in position, at least two of the pins cooperating with ec one of the first or second latching lugs of the ring sector and the corresponding first or second radial lug of the ring support structure, and at least one of the pins cooperating with the other latching lug of the ring sector and the corresponding radial tab of the ring support structure.
    According to a general characteristic of the object, the first radial lug comprises a first annular radial portion secured to the ring support structure, a second removable annular radial portion extending radially towards the center of the turbine ring on a part larger than said first annular radial portion, the part extending beyond the first annular radial portion comprising orifices for receiving a pin.
    The removable nature of the second annular radial portion of the first the second annular radial portion relative to the first annular radial portion secured to the ring support structure allows to have axial access to the cavity of the turbine ring . This makes it possible to assemble the ring sectors together outside of the ring support structure and then to axially slide the assembly thus assembled into the cavity of the ring support structure until it comes in support against the second annular radial lug, before fixing the second annular radial portion on the first annular radial portion.
    During the operation of fixing the turbine ring to the ring support structure, it is possible to use a tool comprising a cylinder or a ring on which the ring sectors are supported or vented during their crown assembly.
    The solution defined above for the ring assembly thus makes it possible to maintain each ring sector in a deterministic manner, that is to say to control its position and prevent it from vibrating, while improving sealing between the non-vein sector and the vein sector, simplifying handling and reducing their number for mounting the ring assembly, and allowing the ring to deform under the effects of temperature and pressure especially independently of the metallic parts at the interface.
    According to a first aspect of the turbine ring assembly, the second removable annular radial portion comprises a first annular flange comprising a first portion bearing against the first latching lug of the ring, a second portion bearing against fixed removably to the first annular radial portion, and a third portion positioned between the first and the second portions and comprising the orifices for receiving a pin, the first portion and the third portion of the first annular flange extending beyond of the first annular radial portion of the first radial tab.
    Since the first portion and the third portion of the first annular flange extend beyond the first annular radial portion of the first radial tab, the space remaining free when the flange is removed allows axial insertion of the ring in the ring support structure.
    According to a second aspect of the turbine ring assembly, the first annular flange is an annular flange in one piece.
    Having a one-piece annular flange, that is to say describing the entire ring over 360 °, makes it possible, in relation to a sectored annular flange, to limit the passage of the air flow between the non-vein sector and the vein sector, insofar as all inter-sector leaks are eliminated, and therefore to control the seal.
    According to a third aspect of the turbine ring assembly, the first and second hooking lugs of each ring sector each comprise a first end secured to the external face of the annular base, a second free end, at least a receiving ear of a pin, each ear projecting from the second end of one of the first or second hooking lugs in the radial direction of the turbine ring, each receiving ear having a orifice receiving a pawn.
    The ears made projecting radially from the free ends of the first and second hooking lugs make it possible to offset the holding zone of the hooking lugs relative to the support zones comprised between the two ends of the hooking lugs and intended to produce a tight contact, on the one hand, with the first portion of the first annular flange, and, on the other hand, with the second radial tab of the ring support structure.
    According to a fourth aspect of the turbine ring assembly, the second tab of the ring support structure comprises an annular flange comprising a first portion bearing against the second hooking tab, a second portion thinned relative to the first portion, and a third portion positioned between the first and the second portion and comprising orifices for receiving a pin.
    The reduction in the thickness of the second portion of the annular flange, that is to say the downstream flange, makes it possible to provide flexibility to the secondary flange and thus not to overstress the ceramic matrix composite material of the ring area.
    It is also possible to realize an axial prestress of the second annular flange by making an interference of a few tenths of a millimeter. This makes it possible to take up the differences in expansion between the elements of composite material with a ceramic matrix and the metallic elements.
    In addition, separating the receiving area of the pins and the support areas of the lugs for hooking the ring against the annular flange, on the one hand, and against the annular flange, on the other hand, makes it possible to optimize sealing by reducing cuts in the support area.
    According to a fifth aspect of the turbine ring assembly, each ring sector comprises rectilinear bearing surfaces mounted on the faces of the first and second hooking lugs in contact respectively with the annular flange and the first annular flange .
    The rectilinear supports make it possible to have controlled sealing zones because pressing on a continuous line makes it possible to have no leaks. More specifically, having supports on radial planes makes it possible to overcome the effects of de-cambering in the turbine ring. This alignment of the contact zones on parallel rectilinear planes indeed makes it possible to maintain sealing lines in the event of the ring toppling and to keep the same contact zones both cold and hot.
    In operation, the ring sectors tilt around an axis corresponding to the normal to the plane formed between the axial direction and the radial direction of the turbine ring. In the case of a curvilinear support, as in the prior art, the lugs of the ring sectors are in contact with the ring support structure at only one or two points while, in the present invention, the supports the legs of each ring sector allow support on an entire line, which improves the seal between the ring sectors and the ring support structure.
    In a variant, for each ring sector, the faces of the annular flange and of the first annular flange in contact respectively with the first and second hooking lugs comprise rectilinear bearing surfaces.
    In one aspect of this variant, each rectilinear bearing surface may include a groove hollowed out over the entire length of the bearing surface and a seal inserted into the groove to improve the seal.
    According to a sixth aspect of the turbine ring assembly, the first radial tab of the ring support structure further comprises a second annular flange comprising a first portion and a second portion, the second portion being coupled to the first radial annular portion and to the second portion of the first annular flange, the first portion of the second annular flange being spaced, in the axial direction of the turbine ring, from the first portion of the first annular flange.
    The second annular flange is dedicated to the resumption of the effort of the high pressure distributor, also noted DHP. This annular flange allows this effort to be taken up, on the one hand, by deforming, and, on the other hand, by passing this effort towards the casing line which is more mechanically robust.
    Indeed, leaving a space between the first portion of the second annular flange and the first portion of the first annular flange makes it possible to deflect the force received by the second annular flange, upstream of the first annular flange relative to the direction of the gas flow, and to pass it directly to the central ring of the ring support structure via the second portion of the second annular flange, without impacting the first portion of the first annular flange bearing against the first latching tab of the ring. The first portion of the first annular flange does not undergo any effort, the turbine ring is thus preserved from this axial effort.
    According to a seventh aspect of the turbine ring assembly,
    The ring assembly may further comprise, for each ring sector, at least one fixing screw passing through the first and second annular flanges and the first annular radial portion, and at least one fixing nut cooperating with said at least a fixing screw for fixing the first and second annular flanges to the first annular radial portion.
    Another object of the invention provides a turbomachine comprising a turbine ring assembly 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 perspective view of an embodiment of a turbine ring assembly according to the invention;
    - Figure 2 is a schematic exploded perspective view of the turbine ring assembly of Figure 1;
    - Figure 3 is a schematic sectional view of the turbine ring assembly of Figure 1;
    FIG. 4 is a schematic perspective view of the first upstream flange of the turbine ring assembly of FIG. 1.
    Detailed description of embodiments
    Figure 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 of ceramic matrix composite material (CMC) and a metal ring support structure
    3. The turbine ring 1 surrounds a set of rotating blades (not shown). The turbine ring 1 is formed from a plurality of ring sectors 10, FIG. 1 being a view in radial section. The arrow D A indicates the axial direction of the turbine ring 1 while the arrow D R indicates the radial direction of the turbine ring 1. For reasons of simplification of presentation, FIG. 1 is a partial view of the 'turbine ring 1 which is actually a complete ring.
    As illustrated in FIG. 2 which presents a schematic exploded perspective view of the turbine ring assembly of FIG. 1, each ring sector 10 has, according to a plane defined by the axial directions D A and radial directions Dr, a section substantially in the shape of the Greek letter π inverted. The section in fact comprises an annular base 12 and upstream and downstream hooking radial lugs 14 and 16. The terms upstream and downstream are used here with reference to the direction of flow of the gas flow in the turbine represented by the arrow F on Figure 1. The legs of the ring sector 10 could have another shape, the section of the ring sector having a shape other than π, such as a k shape.
    The annular base 12 comprises, in the radial direction Dr of the ring 1, an internal face 12a and an external face 12b opposite one another. The internal face 12a of the annular base 12 is coated with a layer 13 of abradable material forming a thermal and environmental barrier and defines a flow stream for gas flow in the turbine.
    The upstream and downstream radial lugs 14 and 16 extend in projection, in the direction Dr, from the external face 12b of the annular base 12 at a distance from the upstream and downstream ends 121 and 122 of the annular base 12 The upstream and downstream hooking radial lugs 14 and 16 extend over the entire width of the ring sector 10, that is to say over the entire arc of a circle described by the ring sector 10, or else over the entire circumferential length of the ring sector 10.
    As illustrated in FIGS. 1 and 2, the ring support structure 3 which is integral with a turbine casing 30 comprises a central ring 31, extending in the axial direction D A , and having an axis of revolution coincides with the axis of revolution of the turbine ring 1 when they are fixed together. The ring support structure 3 further comprises an upstream annular radial flange 32 and a downstream annular radial flange 36 which extend, in the radial direction Dr, from the central ring 31 towards the center of the ring 1 and in the circumferential direction of the ring 1.
    As illustrated in FIGS. 1 and 2, the downstream annular radial flange 36 comprises a first free end 361 and a second end 362 integral with the central crown 31. The downstream annular radial flange 36 comprises a first portion 363, a second portion 364, and a third portion 365 between the first portion 363 and the second portion 364. The first portion 363 extends between the first end 361 and the third portion 365, and the second portion 364 extends between the third portion 365 and the second end
    362. The first portion 363 of the annular radial flange 36 is in contact with the downstream radial hooking lug 16. The second portion 364 is thinned relative to the first portion 363 and the third portion 365 so as to give a certain flexibility to the annular radial flange 36 and thus do not overly constrain the turbine ring 1 in CMC.
    As illustrated in Figures 1 and 2, as well as in Figure 3 which shows a sectional view of the turbine ring assembly of Figure 1 along a plane comprising the axial direction D A of the ring turbine 1 and the radial direction Dr of the turbine ring 1, the ring support structure 3 further comprises a first and a second upstream flanges 33 and 34 each having, in this embodiment, a ring shape , the two upstream flanges 33 and 34 being fixed together on the upstream annular radial flange 32. FIG. 4 presents a perspective view of the first upstream flange 33 produced in a single annular piece. Alternatively, the first and second upstream flanges 33 and 34 could be segmented into a plurality of ring sections.
    The first upstream flange 33 includes a first free end 331 and a second end 332 in contact with the central crown
    31. The first upstream flange 33 further comprises a first portion 333 extending from the first end 331, a second portion 334 extending from the second end 332, and a third portion 335 extending between the first portion 333 and the second portion 334.
    The second upstream flange 34 comprises a first free end 341 and a second end 342 in contact with the central crown 31, as well as a first portion 343 and a second portion 344, the first portion 343 extending between the first end 341 and the second portion 344, and the second portion 344 extending between the first portion 343 and the second end 342.
    The first portion 333 of the first upstream flange 33 is in abutment on the upstream hooking lug 14 of the ring sector 10. The first and second upstream flanges 33 and 34 are shaped to have the first portions 333 and 343 distant from it. one from the other and the second portions 334 and 344 in contact, the two flanges 33 and 34 being detachably fixed to the upstream annular radial flange 32 using screws 60 and nuts 61 for fixing, the screws 60 through orifices 3340, 3440 and
    320 provided respectively in the second portions 334 and 344 of the two upstream flanges 33 and 34 as well as in the upstream annular radial flange 32.
    The second upstream flange 34 is dedicated to the resumption of the effort of the high pressure distributor (DHP), on the one hand, by deforming, and, on the other hand, by passing this effort towards the casing line which is more mechanically robust, i.e. towards the line of the ring support structure 3 as illustrated by the force arrows E shown in FIG. 3.
    In the axial direction D A , the downstream annular radial flange 36 of the ring support structure 3 is separated from the first upstream flange 33 by a distance corresponding to the spacing of the upstream and downstream hooking radial lugs 14 and 16 so as to maintain the latter between the downstream annular radial flange 36 and the first upstream flange 33.
    To keep the ring sectors 10, and therefore the turbine ring 1, in position with the ring support structure 3, the ring assembly comprises two first pins 19 cooperating with the upstream hooking lug 14 and the first upstream flange 33, and two second pins 20 cooperating with the downstream hooking lug 16 and the downstream annular radial flange 36.
    For each corresponding ring sector 10, the third portion 335 of the first upstream flange 33 comprises two orifices 3350 for receiving the first two pins 19, and the third portion 365 of the annular radial flange 36 comprises two orifices 3650 configured to receive the two second pawns 20.
    For each ring sector 10, each of the upstream and downstream hooking radial lugs 14 and 16 comprises a first end, 141 and 161, integral with the external face 12b of the annular base 12 and a second end, 142 and 162, free. The second end 142 of the upstream radial lug 14 comprises two first ears 17 each comprising an orifice 170 configured to receive a first pin 19. Similarly, the second end 162 of the downstream radial lug 16 comprises two second ears 18 each comprising an orifice 180 configured to receive a second pin 20. The first and second ears 17 and 18 extend projecting in the radial direction Dr from the turbine ring 1 respectively from the second end 142 of the tab upstream radial attachment 14 and the second end 162 of the downstream radial attachment tab 16.
    For each ring sector 10, the first two lugs 17 are positioned at two different angular positions relative to the axis of revolution of the turbine ring 1. Similarly, for each ring sector 10, the two seconds ears 18 are positioned at two different angular positions relative to the axis of revolution of the turbine ring 1.
    Each ring sector 10 further comprises rectilinear bearing surfaces 110 mounted on the faces of the upstream and downstream hooking radial lugs 14 and 16 in contact respectively with the first upstream annular flange 33 and the downstream annular radial flange 36, that is to say on the upstream face 14a of the upstream radial latching lug 14 and on the downstream face 16b of the downstream latching lug 16. In a variant, the rectilinear supports could be mounted on the first upstream annular flange 33 and on the downstream annular radial flange 36.
    The rectilinear supports 110 make it possible to have controlled sealing zones. Indeed, the bearing surfaces 110 between the upstream radial hooking lug 14 and the first upstream annular flange 33, on the one hand, and between the downstream radial hooking lug 16 and the downstream annular radial flange 36 are included in the same rectilinear plane.
    More precisely, having supports on radial planes makes it possible to overcome the effects of decambrage in the turbine ring 1.
    A method of producing a set of turbine rings corresponding to that shown in FIG. 1 will now be described.
    Each ring sector 10 described above is made of ceramic matrix composite material (CMC) by forming a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix. .
    For the production of the fiber preform, it is possible to use ceramic fiber yarns, for example SiC fiber yarns such as those sold by the Japanese company Nippon Carbon under the name Hi-NicalonS, or carbon fiber yarns.
    The fibrous preform is advantageously produced by three-dimensional weaving, or multilayer weaving with the arrangement of unbinding zones making it possible to separate the parts of preform corresponding to the tabs 14 and 16 from the sectors 10.
    The weaving can be of the interlock type, as illustrated. Other three-dimensional or multi-layer weaving weaves can be used, for example multi-canvas or multi-satin weaves. Reference may be made to document WO 2006/136755.
    After weaving, the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, densification being able to be carried out in particular by chemical gas infiltration (CVI) which is well known in oneself. In a variant, the textile preform can be hardened a little by CVI so that it is rigid enough to be handled, before making liquid silicon rise by capillary action in the textile to make densification (“Melt Infiltration”).
    A detailed example of manufacturing ring sectors in CMC is described in particular in document US 2012/0027572.
    The ring support structure 3 is made of a metallic material such as a Waspaloy® or inconel 718® or C263® alloy.
    The production of the turbine ring assembly continues with the mounting of the ring sectors 10 on the ring support structure
    3.
    For this, the ring sectors 10 are assembled together on an annular tool of the “spider” type comprising, for example, suction cups configured to each maintain a ring sector 10. The assembly of the ring sectors 10 is carried out by inserting intersectoral sealing tabs between each pair of ring sectors.
    Then the two second pins 20 are inserted into the two orifices 3650 provided in the third part 365 of the annular radial flange 36 of the ring support structure 3.
    The ring 1 is then mounted on the ring support structure 3 by inserting each second pin 20 into each of the orifices 180 of the second ears 18 of the downstream radial lugs 16 of each ring sector 10 making up the ring 1.
    The holes 170 and 180 can be circular or oblong. Preferably the set of orifices 170 and 180 comprises a portion of circular orifices and a portion of oblong orifices. The circular orifices allow the rings to be tangentially indexed and to prevent them from being able to move tangentially (in particular in the event of contact by the blade). The oblong holes make it possible to accommodate the differential expansions between the CMC and the metal. CMC has a much lower coefficient of expansion than that of metal. When hot, the lengths in the tangential direction of the ring sector and of the housing portion opposite will therefore be different. If there were only circular orifices, the metal casing would impose its displacements on the ring in CMC, which would be a source of very high mechanical stresses in the ring sector. Having oblong holes in the ring assembly allows the pin to slide in this hole and avoid the over-stress phenomenon mentioned above. Therefore, two drilling patterns can be imagined: a first drilling pattern, for a case with three ears, would include a oblong radial hole on a radial hooking tab and two oblong tangential holes on the other radial hooking tab , and a second drilling scheme, for a case with at least four ears, would include a circular orifice and an oblong orifice by radial lug for hooking facing each other. Other ancillary cases can also be envisaged.
    The annular tool is then removed and all the first pins 19 are placed in the holes 3350 provided in the third part 335 of the first upstream flange 33, and the first upstream flange 33 is mounted on the ring assembly by engaging the first pins 19 in the holes 170 of the first ears of the upstream hooking lug 14 until the first portion 333 of the first upstream flange 33 is in abutment against the bearing surface 110 of the upstream face 14a of the lug upstream attachment 14 of the ring 1 and that the second portion 334 of the first upstream flange 33 is in abutment against the upstream annular radial flange 32.
    The second upstream flange 34 is then placed on the turbine ring assembly by pressing the second portion 344 of the second upstream flange 34 against the second portion 334 of the first upstream flange 33.
    To fix the two upstream flanges 33 and 34 together to the ring support structure 3, screws 60 are inserted into the orifices 3440, 3340 and 320, coaxial, provided in the second portion 344 of the second upstream flange 34, in the second portion 334 of the first flange and in the upstream annular radial flange 32 and each of the screws 60 is tightened using a nut 61.
    The ring 1 is thus held in an axial position by means of the first upstream flange 33 and the annular radial flange 36 bearing respectively upstream and downstream on the support surfaces 110 rectilinear of the respectively upstream radial hooking lugs 14 and downstream 16. And the ring 1 is held in position radially using the first and second pins 19 and 20 cooperating with the first and second ears 17 and 18 and the orifices 3350 and 3650 of the first upstream flange 33 and the annular radial flange 36.
    The invention thus provides a turbine ring assembly allowing the maintenance of each ring sector in a deterministic manner while allowing, on the one hand, the ring sector, and by extension to the ring, deform under the effects of temperature rises and pressure variations, and this independently of the metal parts at the interface, and, on the other hand, while improving the seal between the non-vein sector and the vein sector and simplifying manipulations and reducing their number for mounting the ring assembly.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A turbine ring assembly comprising a plurality of ring sectors (10) of ceramic matrix composite material forming a turbine ring (1) and a ring support structure (3), each ring sector (10) having, according to a cutting plane defined by an axial direction (D a ) and a radial direction (Dr) of the turbine ring (1), an annular base portion (12) with, in the radial direction (D R ) of the turbine ring (1), an internal face (12a) defining the internal face of the turbine ring (1) and an external face (12b) from which extend a first and a second hooking lugs (14, 16), the ring support structure (3) comprising a first and a second radial lugs between which are held the first and second hooking lugs (14, 16) of each sector ring (10), and the ring assembly comprising, for each ring sector (10), at least three pins (19, 20) to maintain radial ment the ring sector (10) in position, at least two of the pins (19, 20) cooperating with one of the first or second hooking lugs (14,16) of the ring sector (10) and the first or second corresponding radial tab of the ring support structure (3), and at least one of the pins (20, 19) cooperating with the other hooking tab (16, 14) of the ring sector (10 ) and the other corresponding radial tab of the ring support structure (3), characterized in that the first radial tab comprises a first annular radial portion (32) integral with the ring support structure (3), a second removable annular radial portion extending radially towards the center of the turbine ring (1) over a larger portion than said first annular radial portion (32), the portion extending beyond the first annular radial portion (32) comprising orifices (3350) for receiving one of the pins (19).
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein the second removable annular radial portion comprises a first annular flange (33) having a first portion (333) bearing against the first hooking lug (14), a second portion (334) removably attached to the first annular radial portion (32), and a third portion (335) positioned between the first and the second portions (333 and 334) and comprising the orifices (3350) for receiving one of the pins (19 ), the third portion (335) and the first portion (333) of the first annular flange (33) extending beyond the first annular radial portion (32).
    [3" id="c-fr-0003]
    3. The assembly of claim 2, wherein said first annular flange (33) is an annular flange in one piece.
    [4" id="c-fr-0004]
    4. Assembly according to one of claims 1 to 3, wherein the first and second hooking lugs (14, 16) of each ring sector (10) each comprise a first end (141, 161) integral with the external face (12b) of the annular base (12), a second free end (142, 162), at least one ear (17,18) for receiving one of the pins (19, 20), each ear (17, 18) projecting from the second end (142, 162) of one of the first or second hooking lugs (14, 16) in the radial direction (Dr) of the turbine ring (1), each receiving ear (17, 18) comprising an orifice (170, 180) for receiving one of the pins (19, 20).
    [5" id="c-fr-0005]
    5. Assembly according to one of claims 1 to 4, wherein the second leg of the ring support structure (3) comprises an annular flange (36) having a first portion (363) bearing against the second leg d 'hooking (16), a second portion (364) thinned relative to the first portion (363), and a third portion (365) positioned between the first and the second portion (363 and 364) and having orifices (3650) receiving one of the pawns (20).
    [6" id="c-fr-0006]
    6. The assembly of claim 5 when combined with claim 2, wherein each ring sector (10) comprises rectilinear bearing surfaces (110) mounted on the faces of the first and second hooking lugs ( 14, 16) in contact respectively with the annular flange (36) and the first annular flange (33).
    [7" id="c-fr-0007]
    7. The assembly of claim 5 when combined with claim 2, wherein, for each ring sector (10), the faces of the annular flange (36) and the first annular flange (33) in contact respectively with the first and second attachment tabs (14,16) comprise rectilinear bearing surfaces.
    [8" id="c-fr-0008]
    8. Assembly according to one of claims 3 to 7 when combined with claim 2, wherein the first radial tab of the ring support structure (3) further comprises a second annular flange (34) comprising a first portion (343) and a second portion (344), the second portion (344) being coupled to the first annular radial portion (32) and to the second portion (334) of the first annular flange (33), the first portion (343) of the second annular flange (34) being spaced, in the axial direction (Da) of the turbine ring (1), from the first portion (333) of the first annular flange (33).
    [9" id="c-fr-0009]
    9. The assembly of claim 8, comprising, for each ring sector (10), at least one fixing screw (60) passing through the first and second annular flanges (33, 34) and the first annular radial portion (32) , and at least one fixing nut (61) cooperating with said at least one fixing screw (60) for fixing the first and second annular flanges (33, 34) to the first annular radial portion (32).
    [10" id="c-fr-0010]
    10. Turbomachine comprising a turbine ring assembly (1) according to any one of claims 1 to 9.
    1/3 oc
    Q
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    同族专利:
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    法律状态:
    2017-05-17| PLFP| Fee payment|Year of fee payment: 2 |
    2018-02-23| PLSC| Search report ready|Effective date: 20180223 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 3 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1657826|2016-08-19|
    FR1657826A|FR3055147B1|2016-08-19|2016-08-19|TURBINE RING ASSEMBLY|FR1657826A| FR3055147B1|2016-08-19|2016-08-19|TURBINE RING ASSEMBLY|
    US15/680,934| US10619517B2|2016-08-19|2017-08-18|Turbine ring assembly|
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