• 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 turbine ring assembly comprising ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each ring sector (10) having, in accordance with a plane of a section defined by an axial direction (DA) and a radial direction (DR) of the ring (1), an annular base portion (12) with, in the radial direction (DR), an inner face (12a) and a outer surface (12b) from which project a first and a second attachment lugs (14, 16), said structure (3) having a central ferrule (31) from which projecting a first and a second radial flange (32, 36) between which are held the latching lugs (14, 16) of each ring sector (10). It comprises a first and a second annular flange (33, 34) removably attached to the first radial flange (32), the second annular flange (34) comprising a bearing ferrule (346) projecting to the first flange (34). upstream in the axial direction (DA) and having a radial bearing (348) in contact with the central shell (31).
    公开号:FR3064024A1
    申请号:FR1752151
    申请日:2017-03-16
    公开日:2018-09-21
    发明作者:Nicolas Paul TABLEAU；Sebastien Serge Francis CONGRATEL；Clement Jean Pierre DUFFAU；Noel Garin Fabrice Marcel；Lucien Henri Jacques QUENNEHEN
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    © Publication no .: 3,064,024 (to be used only for reproduction orders)
    ©) National registration number: 17 52151 ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY
    COURBEVOIE © IntCI 8 : F 01 D 25/24 (2017.01), F 01 D 11/00, 9/04, F 02 C 7/20
    A1 PATENT APPLICATION
    ©) Date of filing: 16.03.17.(© Priority: © Applicant (s): SAFRAN AIRCRAFT ENGINES -FR. ©) Date of public availability of the request: 21.09.18 Bulletin 18/38. @ Inventor (s): TABLE NICOLAS PAUL, CONGRATEL SEBASTIEN SERGE FRANCIS, DUFFAU CLEMENT JEAN PIERRE, GARIN FABRICE MARCEL, NOËL and QUENNEHEN LUCIEN HENRI JACQUES. ©) List of documents cited in the preliminary search report: See the end of this booklet (© References to other related national documents: ® Holder (s): SAFRAN AIRCRAFT ENGINES. ©) Extension request (s): © Agent (s): CABINET BEAU DE LOMENIE. © TURBINE RING SET.
    FR 3 064 024 - A1 (5/7 A turbine ring assembly comprising ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each sector of ring (10) having, according to a cutting plane defined by an axial direction (D A ) and a radial direction (D R ) of the ring (1), an annular base portion (12) with, in the radial direction (D R ), an internal face (12a) and an external face (12b) from which project first and second hooking lugs (14, 16), said structure (3) comprising a ferrule central (31) from which project first and second radial flanges (32, 36) between which the latching lugs (14, 16) of each ring sector (10) are held.
    It comprises first and second annular flanges (33, 34) removably attached to the first radial flange (32), the second annular flange (34) comprising a support ring (346) projecting towards the upstream in the axial direction (D A ) and having a radial support (348) in contact with the central ferrule (31).

    Background of the invention
    A turbine ring assembly includes a plurality of ring sectors of ceramic matrix composite material as well as 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.
    We also know 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.
    There is a need to improve the existing turbine ring assemblies and their mounting, and in particular the existing turbine ring assemblies using a CMC material in order to reduce the intensity of the mechanical stresses to which the ring sectors in CMCs are subject to the 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 forming a turbine ring and a ring support structure, each ring sector having, according to a cutting 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 ring and an external face to from which protrude first and second hooking lugs, the ring support structure comprising a central ferrule from which protrude first and second radial flanges between which the first and second attachment tabs of each ring sector.
    According to a general characteristic of the object, the turbine ring assembly comprises an annular flange in one piece removably attached to the central ferrule, the annular flange having a first free end, a second end coupled to the ferrule central, a first portion extending from the first end, a second portion extending between the first portion and the second end, the first portion of the flange having first and second separate legs, the first leg being in abutment against the first hooking tab and the second tab being spaced from the first tab in the axial direction, the second tab being upstream of the first tab relative to the direction of an air flow intended to pass through the ring assembly turbine, and the second portion of the annular flange comprising a support ring projecting downstream in the axial direction, the support ring having a radial support in contact with the central ferrule of the ring support structure.
    In a particular embodiment, the ring sectors can be made of a ceramic matrix composite material (CMC).
    The presence on the first portion of the annular flange of a second tab disposed upstream and separated from a first tab in contact with a latching tab upstream of the ring makes it possible to supply the turbine ring assembly an upstream leg of the annular flange dedicated to the resumption of the effort of the high pressure distributor (DHP). The second leg upstream of the first leg of the turbine ring and free from any contact with the ring is configured to pass the maximum axial force induced by the DHP directly into the ring support structure without passing by the ring which, when in CMC, has a low mechanical allowability.
    Indeed, leaving a space between the first and second legs of the annular flange allows to deflect the force received by the second leg, upstream of the first leg which is in contact with the turbine ring, and to make it pass directly towards the central ferrule of the ring support structure via the second portion of the annular flange, without impacting the first leg of the annular flange and therefore without impacting the turbine ring. The first leg of the annular flange does not undergo any force, the turbine ring is thus preserved from this axial force.
    The transit of the DHP effort via the second leg of the annular flange can induce its tilting. This tilting can cause uncontrolled contact between the lower parts, that is to say between the legs, of the annular flange, which would have the consequence of directly transmitting the force DH P to the ring.
    The downstream support ring provides higher resistance to tilting induced by the DHP force. The support ring takes up the significant tangential stresses caused by the DHH force on the upstream lug and thereby limits the tilting of the annular flange. The radial support of the support ring makes it possible to limit the tilting of the annular flange when the DHP force passes through the flange.
    In addition, the removable nature of the annular flange makes it possible 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 into support against the second radial flange, before fixing the annular flange on the central ferrule of the ring support structure.
    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 pressed or vented during their crown assembly.
    Having a one-piece annular flange, that is to say describing the whole of a 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.
    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 to 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 first annular radial flange forms a first rib projecting in the radial direction of the turbine ring towards the inside of the ring, and the second end of the flange annular comprises an axial stop extending in the radial direction of the turbine ring towards the outside of the ring, the axial stop being disposed upstream of said first annular radial flange and coming to bear in the axial direction of the turbine ring against said first annular radial flange.
    The axial stop makes it possible to press the annular flange on the first annular radial flange and thus to position the first leg of the annular flange axially with respect to the radial latch for hooking upstream of the ring.
    According to a second aspect of the turbine ring assembly, the central ferrule of the ring support structure may further comprise a second rib projecting in the radial direction of the turbine ring towards the interior of the ring and having a bearing surface on which the radial support of the support ring rests, the second rib being disposed between the first and the second radial flanges of the ring support structure.
    The second rib is a radial fulcrum which allows the ring support structure to retain the rocker of the second leg of the annular flange when the DHP force is applied. The large distance between the axial stop and the radial support of the support ferrule makes it possible to increase the arm of the lever and thus to induce a lesser radial force on the casing at the level of the contact of the radial support with the second rib of the ring support structure.
    The annular flange is fixed by means of two radial hoopings, a first hooping between the radial support and the second rib, and a second hooping between the surface of the axial stop extending in a plane comprising the axial direction and the central ferrule.
    According to a third aspect of the turbine ring assembly, the ring sector can have a section in Greek letter pi (π) inverted according to the cutting plane defined by the axial direction and the radial direction, and the assembly may comprise, for each ring sector, at least three pins for radially maintaining the ring sector in position, the first and second hooking lugs of each ring sector each comprising a first end integral with the external face of the annular base, a second free end, at least three ears for receiving said at least three pins, at least two ears projecting from the second end of one of the first or second lugs in the radial direction of the turbine ring and at least one ear projecting from the second end of the other hooking lug in the radial direction of the turbine ring, each receiving ear comprising an orifice for receiving one of the pawns.
    According to a fourth aspect of the turbine ring assembly, the ring sector can have a section having an elongated K shape along the cutting plane defined by the axial direction and the radial direction, the first and a second legs hook having an S shape.
    According to a fifth aspect of the turbine ring assembly, the ring sector may have, over at least one radial range of the ring sector, an O-section along the cutting plane defined by the axial direction and the radial direction, the first and second hooking tabs each having a first end secured to the external face and a second free end, and each ring sector comprising a third and a fourth hooking tabs each extending in the axial direction of the turbine ring, between a second end of the first hooking lug and a second end of the second hooking lug, each ring sector being fixed to the ring support structure by a fixing screw comprising a screw head bearing against the ring support structure and a thread cooperating with a thread produced in a fixing plate, the fixing plate cooperating with the three th and fourth hooking lugs.
    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 a first 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;
    - Figure 4 is a schematic sectional view of a second embodiment of the turbine ring assembly;
    - Figure 5 is a schematic sectional view of a third embodiment of the turbine ring assembly;
    - Figure 6 is a schematic sectional view of a fourth embodiment of the turbine ring assembly.
    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 Figures 2 and 3 which respectively show a schematic exploded perspective view and a sectional view of the turbine ring assembly of Figure 1, the sectional view being along a section plane comprising the radial direction Dr and the axial direction D A , each ring sector 10 has, according to a plane defined by the axial directions D A and radial Dr, a section substantially in the shape of the Greek letter π inverted. The section indeed includes an annular base 12 and radial lugs for upstream and downstream attachment, respectively 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 in FIG. 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 for example a K or O shape.
    The annular base 12 comprises, in the radial direction D R 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 terms internal and external are used here with reference to the radial direction Dr in the turbine.
    The upstream and downstream radial lugs 14 and 16 extend in projection, in the direction D R , 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 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 again over the entire circumferential length of the ring sector 10.
    As illustrated in FIGS. 1 to 3, the ring support structure 3 which is integral with a turbine casing comprises a central ferrule 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, as well as a first annular radial flange 32 and a second annular radial flange 36, the first annular radial flange 32 being positioned upstream of the second annular radial flange 36 which is therefore downstream of the first annular radial flange 32.
    The second annular radial flange 36 extends in the circumferential direction of the ring 1 and, in the radial direction Dr, from the central ferrule 31 towards the center of the ring 1. It comprises a first free end 361 and a second end 362 integral with the central ferrule 31. The second annular radial flange 36 has 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 second annular radial flange 36 is in contact with the radial flange of downstream attachment 16. The second portion 364 is thinned with respect to the first portion 363 and the third portion 365 so as to give a certain flexibility to the second radiating flange ale annulaire 36 and thus do not overly constrain the turbine ring 1 in CMC.
    The first annular radial flange 32 forms a first annular radial rib extending in the circumferential direction of the ring 1 as well as in the radial direction Dr of the ring from the central ferrule 31 towards the center of the ring 1.
    As illustrated in FIGS. 1 to 3, the turbine ring assembly 1 comprises a single removable annular flange 35 made in one piece and removably attached to the ring support structure 3 The removable flange 35 comprises a first free end 351 and a second end 352 shrunk radially to the central ferrule 31 of the annular support structure 3. The removable flange 35 further comprises a first portion 353 extending from the first end 351 and a second portion 354 s extending between the first portion 353 and the second end 352.
    The first portion 353 comprises a first tab 33 and a second tab 34 distinct from the first tab 33 and distant from the latter in the axial direction D A / the second tab 34 being upstream of the first tab 33 relative to the direction of flow of air F intended to pass through the turbine ring assembly 1. When the ring assembly is mounted, the first tab 33 of the removable flange 35 is in abutment against the upstream radial hooking tab 14 of each ring sectors 10 making up the turbine ring 1.
    The radial retention of the ring 1 is ensured by the first tab 33 of the annular flange 35 which is pressed against the upstream radial hooking tab 14 and by the first portion 363 of the second annular radial flange 36 which is pressed against the flange radial downstream attachment 16. The first tab 33 of the annular flange 35 seals between the vein cavity and the cavity outside the vein of the ring.
    The second tab 34 of the removable annular flange 35 is dedicated to the recovery of the force of the high pressure distributor (DHP) on the removable annular flange 35, on the one hand, by deforming, and, on the other hand, by making transit this force towards the casing line which is more mechanically robust, that is to say towards the line of the ring support structure 3 as illustrated by the force arrows E presented in FIG. 3.
    The first tab 33 and the second tab 34 of the removable annular flange 35 meet at the second portion 354 of the removable annular flange 35.
    In the first embodiment illustrated in FIGS. 1 to 3, the annular flange 35 comprises an axial stop 355 extending in the radial direction Dr from the second end 352 of the annular flange 35. The axial stop 355 extends from the second end 352 in the direction of the central ferrule 31 of the ring support structure 3. The axial stop 355 is fixed by hooping on the central ferrule 31.
    The axial stop 355 is disposed upstream of the first radial rib formed by the first annular radial flange 32, the latter therefore being downstream of the axial stop 355. The axial stop 355 has an upstream face 355a receiving the gas flow F and a downstream face 355b opposite the upstream face 355a and facing the first radial rib 312. The first radial rib 32, that is to say the first annular radial flange, has an upstream face 32a facing the axial stop 355 of the annular flange 35 and a downstream face 32b opposite the upstream face 32a and facing the second annular radial flange 36. When the turbine ring assembly is mounted, the downstream face 355b of the axial stop 355 is in bearing against the upstream face 32a of the first radial rib 32 of the central ferrule 31 of the ring structure.
    The axial stop 355 has two uses. It allows, on the one hand, the axial position of the annular flange 35 which allows to precisely adjust the axial position of the first tab 33 relative to the radial lug for upstream attachment 14 of the ring, to ensure contact controlled axial between the two parts. The axial stop 355 makes it possible, on the other hand, to limit the tilting of the second tab 34 and to make the DHP force transit axially on the central ferrule 31 of the ring support structure 3.
    In addition, the second end 352 of the annular flange 35 comprises a support ring 356 projecting downstream in the axial direction D A.
    In other words, the annular flange 35 has an upstream face 35a receiving the gas flow F and a downstream face 35b opposite the upstream face 35a and facing the first annular radial flange 32 and the upstream radial hooking tab. 14. The second portion 354 of the annular flange 35 comprises a support ring 356 extending in the axial direction D A from the downstream face 35b of the annular flange 35.
    The support ring 356 has an internal face 356a and an external face 356b opposite the internal face 356a, a first free end 3561, and a second end 3562 secured to the downstream face 35b of the annular flange 35, the first end 3561 being downstream of the second end 3562 when the turbine ring assembly is mounted. The support ferrule 356 comprises, on its first end 3561, a radial support 358 projecting from the external face 356b of the support ferrule 356.
    In the embodiment illustrated in FIGS. 1 to 3, the central ferrule 31 of the ring support structure 3 further comprises a second radial rib 314 disposed between the first annular radial flange 32 and the second annular radial flange 36 and extending projecting in the radial direction Dr from the central ferrule 31. The second radial rib 314 extends in the direction of the ring 1, that is to say in the direction of the radial support 358 of the ferrule support 356. The second radial rib 314 has at its free end an internal radial face 314a opposite the radial support 358. The radial support 358 has, at its free end, an external radial face 358b opposite the second rib radial 314 of the central ferrule 31 of the ring support structure 3.
    When the turbine ring assembly is mounted, the external radial face 358b of the radial support 358 bears against the internal radial face 314a of the second radial rib 314.
    The support ring 356 provides higher resistance to tilting induced by the DHP force. The support ferrule 356 takes up the significant tangential stresses caused by the DHP force and thereby limits the tilting of the annular flange 36.
    In Figure 4 is presented a sectional view of a second embodiment of the turbine ring assembly.
    The second embodiment illustrated in Figure 4 differs from the first embodiment illustrated in Figures 1 to 3 in that the ring sector 10 has, in the plane defined by the axial directions D a and radial Dr, a section K-shaped instead of an inverted π-shaped section.
    Figures 5 and 6 are respectively shown a schematic sectional view of a third embodiment of the turbine ring assembly and a schematic sectional view of a fourth embodiment of the ring assembly turbine.
    The third and fourth embodiments illustrated in FIGS. 5 and 6 differ from the first embodiment illustrated in FIGS. 1 to 3 in that the ring sector 10 has in the plane defined by the axial directions D A and radial Dr, on a part of the ring sector 10, an O-shaped section instead of an inverted π-shaped section, the ring section 10 being fixed to the ring support structure 3 at the using a screw 19 and a fixing piece 20, the screws 38 being removed.
    In each of the embodiments of the invention illustrated in FIGS. 1 to 6, in the axial direction D A , the second annular radial flange 36 of the ring support structure 3 is separated from the first tab 33 of the annular flange 35 by a distance corresponding to the spacing of the upstream and downstream hooking radial tabs 14 and 16 so as to maintain the latter between the first tab 33 of the annular flange 35 and the second annular radial flange 36.
    In the first embodiment illustrated in Figures 1 to 3, to maintain in position the ring sectors 10, and therefore the turbine ring 1, with the ring support structure 3, the ring assembly comprises two first pins 119 cooperating with the upstream hooking tab 14 and the first tab 33 of the annular flange 35, and two second pins 120 cooperating with the downstream hooking tab 16 and the second annular radial flange 36.
    In the first embodiment, for each corresponding ring sector 10, the second portion 354 of the annular flange 35 comprises two orifices 3540 for receiving the first two pins 119, and the third portion 365 of the annular radial flange 36 comprises two orifices 3650 configured to receive the two second pawns 120.
    For each ring sector 10, each of the upstream and downstream hooking radial lugs 14 and 16 comprises a first end, 141 and 161, secured to 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 119. 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 120. 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.
    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 circular radial hole on a radial attachment flange and two oblong tangential holes on the other radial attachment flange , and a second drilling scheme, for a case with at least four ears, would include a circular orifice and an oblong orifice by radial hooking flange facing each other. Other ancillary cases can also be envisaged.
    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.
    As illustrated in FIG. 4, in the second embodiment, each ring sector 10 has, in a plane defined by the axial directions D A and radial D R , a substantially K-shaped section comprising an annular base 12 with , in the radial direction Dr of the ring, an internal face 12a coated with a layer 13 of abradable material forming a thermal and environmental barrier and which defines the flow stream of gas flow in the turbine. Radial hooking lugs upstream and downstream 140, 160 substantially S-shaped extend, in the radial direction Dr, from the outer face 12b of the annular base 12 over the entire width thereof and au- above the upstream and downstream circumferential end portions 121 and 122 of the annular base 12.
    The radial hooking lugs 140 and 160 have a first end, referenced respectively 1410 and 1610, secured to the annular base 12 and a second free end, referenced respectively 1420 and 1620. The free ends 1420 and 1620 of the radial hooking lugs upstream and downstream 140 and 160 extend either parallel to the plane in which the annular base 12 extends, that is to say in a circular plane, or in a rectilinear manner while the lugs 140 and 160 s 'extend annularly. In this second configuration where the ends are rectilinear and the annular hooking lugs, in the event of a possible tilting of the ring during operation, the surface supports then become linear supports, which offers greater sealing than in the case of ad hoc supports. The second end 1620 of the downstream radial hooking tab 160 is held between a portion 3610 of the second annular radial flange 36 projecting in the axial direction D A from the first end 361 of the second annular radial flange 36 in the direction opposite to the direction of flow F and the free end of the associated screw 38, that is to say the screw opposite to the screw head. The second end 1410 of the upstream radial lug 140 is held between a portion 3310 of the first lug 33 of the annular flange 35 projecting in the axial direction D A from the first end 331 of the first lug 33 in the direction of flow F and the free end of the associated screw 38.
    In the third embodiment illustrated in FIG. 5, the ring sector 10 comprises an axial latching lug 17 'extending between the upstream and downstream latching lugs 14 and 16. The axial latching lug 17 'extends more precisely, in the axial direction D a , between the second end 142 of the upstream radial hooking lug 14 and the second end 162 of the downstream radial hooking lug 16.
    The axial latching tab 17 ′ comprises an upstream end 171 ′ and a downstream end 172 ′ separated by a central part 170 ′. The upstream and downstream ends 171 ′ and 172 ′ of the axial hooking lug 17 ′ extend in projection, in the radial direction Dr, from the second end 142, 162 of the radial hooking lug 14, 16 to which they are coupled, so as to have a central portion 170 ′ of axial latching lug 17 ′ raised relative to the second ends 142 and 162 of the radial latching lugs upstream and downstream 14 and 16.
    For each ring sector 10, the turbine ring assembly comprises a screw 19 and a fixing piece 20. The fixing piece 20 is fixed on the axial lug 17 '.
    The fixing piece 20 further comprises an orifice 21 provided with a thread cooperating with a thread of the screw 19 to fix the fixing piece 20 to the screw 19. The screw 19 comprises a screw head 190 whose diameter is greater the diameter of an orifice 39 produced in the central ferrule 31 of the support structure of the ring 3 through which the screw 19 is inserted before being screwed to the fixing part 20.
    The support ferrule 356 further comprises an orifice 3560 through which the screw 19 and a part of the fixing part 20 pass. The orifice 3560 has a diameter greater than that of the fixing part 20.
    The radial connection of the ring sector 10 with the ring support structure 3 is carried out using the screw 19, the head 190 of which rests on the central ring 31 of the ring support structure 3, and of the fixing piece 20 screwed to the screw 19 and fixed to the axial hooking lug 17 ′ of the ring sector 10, the screw head 190 and the fixing piece 20 exerting forces of opposite directions for hold ring 1 and ring support structure 3 together.
    In Figure 6 is shown a schematic sectional view of a fourth embodiment of the turbine ring assembly.
    The fourth embodiment illustrated in FIG. 6 is a variant of the third embodiment illustrated in FIG. 5. In this variant, the central ferrule 31 of each ring sector 10 does not include an orifice 39.
    In the fourth embodiment, the ring sector 10 is fixed directly to the support ring 356 using the screw 19 and the fixing piece 20. the support ring 356 comprises an orifice 3560 passed through by screw 19. The orifice 3560 has a diameter smaller than that of the screw head 190.
    The radial connection of the ring sector 10 with the ring support structure 3 is carried out using the screw 19, the head 190 of which rests on the support ferrule 356 of the annular flange 35, and of the fastener 20 screwed to the screw 19 and fixed to the axial lug 17 'of the ring sector 10, the screw head 190 and the fastener 20 exerting forces of opposite directions to hold the ring 1 and the ring support structure 3.
    In each of the embodiments of the invention illustrated in FIGS. 1 to 6, each ring sector 10 further comprises rectilinear bearing surfaces 110 mounted on the faces of the upstream and downstream hooking radial tabs 14 and 16 in contact respectively with the first tab 33 of the annular flange 35 and the second annular radial flange 36, that is to say on the upstream face 14a of the upstream radial hooking tab 14 and on the downstream face 16b of the tab radial downstream attachment 16. In a variant, the rectilinear supports could be mounted on the first tab 33 of the annular flange 35 and on the second annular radial downstream flange 36.
    The rectilinear supports 110 make it possible to have controlled sealing zones. In fact, the bearing surfaces 110 between the upstream radial hooking tab 14 and the first tab 33 of the annular flange 35, on the one hand, and between the downstream radial hooking tab 16 and the second 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.
    We will now describe a process for producing a turbine ring assembly corresponding to that shown in FIG. 1, that is to say according to the first embodiment illustrated in FIGS. 1 to 3.
    Each ring sector 10 described above is made of a 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 preforms corresponding to the lugs 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, the 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.
    Then the two second pins 120 are inserted into the two orifices 3650 provided in the third part 365 of the second 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 120 into each of the orifices 180 of the second ears 18 of the downstream radial attachment flanges 16 of each ring sector 10 making up the ring 1.
    All the first pins 119 are then placed in the holes 170 provided in the first ears 17 of the radial latching lug 14 of the ring 1.
    Then the annular flange 35 is fixed to the ring support structure 3 and to the ring 1. The annular flange 35 is cold mounted on the ring support structure 3 in contact with the stop 32. When the temperature rise of the annular flange 35, the hooping takes place at the level of the two radial contacts.
    To keep the ring 1 in a radially position, the annular flange 35 is fixed to the ring by inserting each first pin 119 in each of the orifices 170 of the first ears 17 of the upstream radial lugs 14 of each ring sector 10 making up the ring 1.
    The ring 1 is thus held in an axial position using the first tab 33 of the annular flange 35 and the second annular radial flange 36 bearing respectively upstream and downstream on the support surfaces 110 rectilinear of the radial tabs upstream and downstream 16 hooks respectively. When installing the annular flange 35, an axial prestress can be applied to the first tab 33 of the annular flange 35 and to the upstream radial lug 14 to offset the effect differential expansion between the CMC material of the ring 1 and the metal of the ring support structure 3. The first tab 33 of the annular flange 35 is maintained in axial stress by mechanical elements placed upstream as illustrated in dotted in Figure 3.
    The ring 1 is held in position radially using the first and second pins 119 and 120 cooperating with the first and second ears 17 and 18 and the orifices 3540 and 3650 of the annular flange 35 and of 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, to 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 by simplifying manipulations and reducing their number for mounting the ring assembly.
    In addition, the invention provides a turbine ring assembly comprising an upstream annular flange dedicated to the recovery of the DHP force and thus to induce low levels of force in the CMC ring, a contact stop between the annular flange dedicated to the resumption of the DHP force and the annular flange used to maintain the ring, the stop making it possible to ensure the non-contact of the lower parts of the two flanges during the tilting of the upstream flange. The turbine ring assembly according to the invention also makes it possible to control the rigidity at the level of the upstream and downstream axial contacts between the CMC ring and the metal casing. Therefore sealing is ensured in all circumstances, without inducing excessive axial forces on the ring.
    权利要求:
    Claims (7)
    [1" id="c-fr-0001]
    1. A turbine ring assembly comprising a plurality of ring sectors (10) 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 (D R ) 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 project first and second legs of attachment (14, 16), the ring support structure (3) comprising a central ferrule (31) from which project first and second radial flanges (32, 36) between which are maintained the first and second attachment tabs (14,16) of each ring sector (10), characterized in that it comprises an annular flange (35) in a single piece e removably attached to the central ferrule (31), the annular flange (35) comprising a free first end (351), a second end (352) coupled to the central ferrule (31), a first portion (353) s extending from the first end (351), a second portion (354) extending between the first portion (353) and the second end (352), the first portion (353) has first and second legs (33, 34) separate, the first tab (33) being in abutment against the first hooking tab (14) and the second tab (34) being distant from the first tab (33) in the axial direction (D A ), the second leg (34) being upstream of the first leg (33) relative to the direction of an air flow (F) intended to pass through the turbine ring assembly (1), the second portion (354) of the annular flange (35) comprising a support ring (356) projecting downstream in the axial direction (D A ), the support ring (35 6) comprising a radial support (358) in contact with the central ferrule (31) of the ring support structure (3).
    [2" id="c-fr-0002]
    2. The assembly as claimed in claim 1, in which the first annular radial flange (32) forms a first rib projecting in the radial direction (Dr) of the turbine ring (1) towards the inside of the ring, and the second end (352) of the annular flange (35) has an axial stop (355) extending in the radial direction (Dr) of the turbine ring (1) towards the outside of the ring, the axial stop (355) being arranged upstream of the first annular radial flange (32) and bearing in the axial direction (D A ) of the turbine ring against the first annular radial flange (32).
    [3" id="c-fr-0003]
    3. Assembly according to one of claims 1 or 2, wherein the central ferrule (31) of the ring support structure (3) further comprises a second rib (314) projecting in the radial direction (Dr) of the turbine ring (1) towards the inside of the ring and having a support surface (314a) on which the radial support (358) of the support ring (356) rests, second rib (314) being disposed between the first and second radial flanges (32, 36) of the ring support structure (3).
    [4" id="c-fr-0004]
    4. Assembly according to one of claims 1 to 3, in which the ring sector (10) has a section in Greek letter pi (π) inverted according to the cutting plane defined by the axial direction (D A ) and the radial direction (D R ), and the assembly comprises, for each ring sector (10), at least three pins (119, 120) for radially holding the ring sector (10) in position, the first and second hooking lugs (14, 16) of each ring sector (10) each comprising a first end (141, 161) integral with the external face (12b) of the annular base (12), a second end (142, 162) free, at least three ears (17, 18) for receiving said at least three pins (119,120), at least two ears (17) projecting from the second end (142, 162) of one of the first or second attachment tabs (14, 16) in the radial direction (Dr) of the turbine ring (1) and at least one lug (18) projecting from the second end (162, 142) of the other hooking tab (16, 14) in the radial direction (Dr) of the turbine ring (1), each receiving lug (17, 18) having an orifice (170,180 ) receiving one of the pawns (119,120).
    [5" id="c-fr-0005]
    5. Assembly according to one of claims 1 to 3 Z wherein the ring sector (10) has a section having an elongated K shape along the cutting plane defined by the axial direction (D A ) and the radial direction (Dr), the first and second attachment tabs (14,16) having an S shape.
    [6" id="c-fr-0006]
    6. Assembly according to one of claims 1 to 3, in which the ring sector (10) has, on at least one radial range of the ring sector, an O-section according to the cutting plane defined by the direction axial (D A ) and the radial direction (Dr), the first and second hooking lugs (14, 16) each having a first end (141, 161) integral with the external face (12b) and a second free end (142, 162), and each ring sector (10) comprising a third and a fourth hooking lugs (17 ') each extending in the axial direction (D A ) of the turbine ring (1 ), between a second end (142) of the first hooking lug (14) and a second end (162) of the second hooking lug (16), each ring sector (10) being fixed to the structure ring support (3) by a fixing screw (19) having a screw head (190) bearing against the ring support structure (3) and a thread cooperating with a thread produced in a fixing plate (20), the fixing plate (20) cooperating with the third and fourth hooking lugs (17 ').
    [7" id="c-fr-0007]
    7. Turbomachine comprising a turbine ring assembly (1) according to any one of claims 1 to 6.
    1/6
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    引用文献:
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    ES2398727T3|2009-03-09|2013-03-21|Snecma|Turbine ring set|
    FR2955898B1|2010-02-02|2012-10-26|Snecma|UPPER SEALING OF A CMC RING IN A TURBOMACHINE TURBINE|
    US8740552B2|2010-05-28|2014-06-03|General Electric Company|Low-ductility turbine shroud and mounting apparatus|
    US8905709B2|2010-09-30|2014-12-09|General Electric Company|Low-ductility open channel turbine shroud|
    FR2978197B1|2011-07-22|2015-12-25|Snecma|TURBINE AND TURBINE TURBINE TURBINE DISPENSER HAVING SUCH A DISPENSER|
    FR2981602B1|2011-10-25|2017-02-17|Snecma Propulsion Solide|PROCESS FOR MANUFACTURING TURBINE DISPENSER SECTOR OR COMPRESSOR RECTIFIER OF COMPOSITE MATERIAL FOR TURBOMACHINE AND TURBINE OR COMPRESSOR INCORPORATING A DISPENSER OR RECTIFIER FORMED OF SUCH SECTORS|
    WO2014158286A1|2013-03-12|2014-10-02|Thomas David J|Turbine blade track assembly|
    FR3033826B1|2015-03-16|2018-11-23|Safran Ceramics|TURBINE RING ASSEMBLY COMPRISING A PLURALITY OF RING SECTIONS IN CERAMIC MATRIX COMPOSITE MATERIAL|
    FR3055148B1|2016-08-19|2020-06-05|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3055146B1|2016-08-19|2020-05-29|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3055147B1|2016-08-19|2020-05-29|Safran Aircraft Engines|TURBINE RING ASSEMBLY|US10697314B2|2016-10-14|2020-06-30|Rolls-Royce Corporation|Turbine shroud with I-beam construction|
    US10557365B2|2017-10-05|2020-02-11|Rolls-Royce Corporation|Ceramic matrix composite blade track with mounting system having reaction load distribution features|
    FR3076578B1|2018-01-09|2020-01-31|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3091550B1|2019-01-08|2021-01-22|Safran Aircraft Engines|Method of assembly and disassembly of a turbine ring assembly|
    US11149563B2|2019-10-04|2021-10-19|Rolls-Royce Corporation|Ceramic matrix composite blade track with mounting system having axial reaction load distribution features|
    法律状态:
    2018-02-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-09-21| PLSC| Publication of the preliminary search report|Effective date: 20180921 |
    2019-02-20| PLFP| Fee payment|Year of fee payment: 3 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 5 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1752151|2017-03-16|
    FR1752151A|FR3064024B1|2017-03-16|2017-03-16|TURBINE RING ASSEMBLY|FR1752151A| FR3064024B1|2017-03-16|2017-03-16|TURBINE RING ASSEMBLY|
    US16/494,059| US11028720B2|2017-03-16|2018-03-13|Turbine ring assembly|
    PCT/FR2018/050589| WO2018172655A1|2017-03-16|2018-03-13|Turbine ring assembly|
    CN201880028328.0A| CN110573695A|2017-03-16|2018-03-13|Turbine ring assembly|
    EP18714568.5A| EP3596315B1|2017-03-16|2018-03-13|Seal shroud assembly|
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