• 专利附录
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    • 专利摘要:
    A turbine ring assembly comprising a plurality of CMC ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each ring sector (10) having a annular base portion (12) having, in the radial direction (DR) of the turbine ring (1), an outer face (12b) from which protrude in the radial direction (DR), a first and a second latching lug (14, 16) each having a free end (142, 162), each ring sector (10) including a third and a fourth latching lug (17, 18); extending each in the axial direction (DA) of the turbine ring (1) between the free end (142) of the first latching lug (14) and the free end (162) of the second leg hooking (16). Each ring sector (10) is attached to the ring support structure (3) by a screw (19) having a screw head (190) bearing against the ring support structure (3) and a thread cooperating with a tapping made in a plate (20), the plate (20) cooperating with the third and fourth latches (17, 18).
    公开号:FR3055146A1
    申请号:FR1657822
    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:

    (54) TURBINE RING ASSEMBLY.
    (57) a turbine ring assembly comprising a plurality of CMC ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each ring sector (10 ) having an annular base portion (12) having, in the radial direction (D R ) of the turbine ring (1), an external face (12b) from which protrude in the radial direction (D R ), a first and a second hooking lugs (14,16) each having a free end (142, 162), each ring sector (10) comprising a third and a fourth hooking lugs (17 , 18) each extending, in the axial direction (D A ) of the turbine ring (1), between the free end (142) of the first hooking lug (14) and the free end ( 162) of the second attachment tab (16).
    Each ring sector (10) is fixed to the ring support structure (3) by a screw (19) having a screw head (190) bearing against the ring support structure (3) and a thread cooperating with a thread produced in a plate (20), the plate (20) cooperating with the third and fourth attachment tabs (17, 18).

    Invention background
    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.
    The documents 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. , while allowing the ring sector, and by extension to the ring, to deform under the effects of temperature rises and pressure variations, and in particular independently of the metal parts at the interface.
    An object of the invention provides a turbine ring assembly comprising a plurality of ring sectors of composite material with ceramic matrix 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 project, in the radial direction of the turbine ring, a first and a second hooking lugs each having a first end integral with the external face and a second free end , each ring sector comprising a third and a fourth hooking tabs each extending, in the axial direction of the turbine ring, between the second end of the first hooking tab and the second end of the second hooking tab.
    According to a general characteristic of the object, each ring sector is 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 internal thread made in a fixing plate, the fixing plate cooperating with the third and fourth hooking lugs.
    Each ring sector is thus maintained at a single point in the radial direction of the turbine ring. Indeed, the only radial fixing point is defined by the assembly formed by the screw and the fixing plate cooperating on one side with the support structure of the ring and on the other side with the first and second legs. hooking of the ring sector.
    The solution defined above for the ring assembly 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 allowing the ring sector, and by extension to the ring, to deform under the effect of temperature and pressure, in particular independently of the metallic parts at the interface.
    According to a first aspect of the turbine ring assembly, each ring sector can comprise at least two pins arranged on either side of said fixing screw and each having a first and a second end, the first end of each pin being fixed on the ring support structure and the second end of each pin bearing against the ring sector.
    The pins extending between the ring support structure and the ring sector make it possible to block the ring sector radially outward, that is to say in a direction moving away from the axis of revolution of the turbine ring. The pins make it possible to provide a radial support perfectly adapted to the ring, which avoids having a play or a tightening due to the geometric dispersions of the different parts.
    According to a variant of the first aspect of the turbine ring assembly, the ring assembly may comprise an annular shim disposed between the ring and the ring support structure and comprising, for each ring sector, an orifice through which the fixing screw passes, at least a first part bearing in the radial direction against the ring support structure and at least a second part bearing in the radial direction against the ring sector, the annular shim being in one piece or sectorized in a plurality of sectorized shims.
    The annular shim may have a form of annular flange extending between the ring support structure and the ring makes it possible to block the ring sectors radially outward, that is to say in one direction moving away from the axis of revolution of the turbine ring. The annular wedge thus offers an alternative radial blocking outwards to the pins, reducing the number of parts used and avoiding drilling the housing for inserting the pins.
    According to a second aspect of the turbine ring assembly, the fixing plate may include first and second ends opposite one another in the circumferential direction of the turbine ring and respectively in contact with the third hooking tab and the fourth hooking tab, the first end having a first shoulder bearing against the third hooking tab and the second end comprising a second shoulder bearing against the fourth hooking tab, and the first and the second shoulders extending in said cutting plane defined by the axial direction and the radial direction of the turbine ring.
    The first and second shoulders of the fixing plate make it possible to provide stops preventing tangential rotation of the ring, or of the ring sector, around its axis.
    Preferably, for each pin, at least a part of the pin is positioned opposite the first or second end of the fixing plate to have a part of the third or fourth hooking tab caught in a vice between the fixing plate and the pawn.
    Bringing the pins of the supports closer together between the connecting plate and the corresponding hooking tab makes it possible to limit the deflection effect as much as possible. The additional hot stresses are therefore low.
    In a variant, the ring sector comprises, on each side of the connection plate, at least one platform for supporting the pins arranged in the same plane as the contact plane between the connection plate and the third and fourth legs attachment, the contact plane being orthogonal to the planes in which extend said first and second shoulders.
    Thus, the supports between the ring sector and the pins, on the one hand, and between the connecting plate and the ring sector, on the other hand, lie in the same plane. When hot, if a curve sees its radius increase, a straight line remains straight. Consequently, the effects of de-cambering are nonexistent and no mechanical stress is just added when hot. By using this solution, there is less need to be precise in the radial maintenance.
    According to a third aspect of the turbine ring assembly, the ring support structure may include first and second annular flanges, the first annular flange being upstream of the second annular flange relative to the direction of flow d air intended to pass through the turbine ring assembly, and the first and second hooking lugs of each ring sector being maintained between the two annular flanges of the ring support structure, the second annular flange comprising a portion thinner than the rest of the second annular flange, the thinner portion being disposed between a portion bearing against the second hooking tab and a portion of junction with the rest of the ring support structure.
    The first and second annular flanges of the ring support structure maintain the position of the ring sector in the axial direction of the turbine ring.
    In addition, the reduction in the thickness of the second annular flange, that is to say the downstream flange, makes it possible to provide flexibility to the secondary flange and thus not to overly constrain 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.
    According to a fourth aspect of the turbine ring assembly, the ring support structure may comprise a first annular flange and a second annular flange fixed to the first annular flange, the first and second annular flanges therefore being removable from the first annular flange, the first annular flange being in abutment against the first hooking tab, and the second annular flange having a first free end and a second end coupled to the first annular flange, the first end being distant, in the axial direction of the turbine ring, of the first annular flange.
    The removable nature of the first 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 press against the second annular flange, before screwing each of the ring sectors on the ring support structure using the screw and the fixing plate, then fix the first annular flange on the first annular flange .
    During the operation of fixing the turbine ring to the support structure of the ring, it is possible to use a tool comprising, on the one hand, a cylinder or a ring on which the ring sectors during their crown assembly, and, on the other hand, a shovel for each of the fixing plates. Each shovel is configured to be inserted in the free space between a pair of third and fourth hooking lugs and keep the fixing plate in abutment against the third and fourth hooking lugs before it is fixed to the structure ring support via the associated screw.
    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.
    According to a fifth aspect of the turbine ring assembly, each ring sector may include rectilinear bearing surfaces mounted on the faces of the first and second hooking lugs in contact respectively with the second annular flange and the first annular flange.
    The rectilinear supports allow controlled sealing zones. More precisely, having supports on radial planes makes it possible to overcome the effects of decambrage in the turbine ring. This alignment of the contact zones on parallel rectilinear planes makes it possible in fact to retain 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 straight 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 second annular flange and of the first annular flange in contact with the first and second hooking lugs respectively 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 third hooking lug and the fourth hooking lug can each be cut into two independent portions, each of the third and fourth hooking lugs comprising a first coupled portion to the first hooking tab and a second portion coupled to the second hooking tab.
    The realization of each of the third and fourth hooking lugs in the form of two independent portions coupled respectively to the first and second hooking lugs allows the upstream and downstream parts of each ring sector, and therefore of the turbine ring , to be mechanically dissociated and thus not to force one another.
    According to a seventh aspect of the turbine ring assembly, the third and fourth hooking tabs are preferably each coupled to the first and second hooking tabs respectively by a first and a second projecting ends extending in the radial direction of the turbine ring, in the extension of the first and second hooking tabs so as to raise the third and fourth hooking tabs relative to the second ends of the first and second hooking tabs.
    This difference in height between the third and fourth hooking tabs and the first and second hooking tabs of a ring sector allows the insertion of a tool under the fixing plate to hold in position said plate during the fixing the screw to the plate.
    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 first schematic perspective view of an embodiment of a turbine ring assembly according to the invention;
    - Figure 2 is a first schematic exploded perspective view of the turbine ring assembly of Figure 1;
    - Figure 3 is a second schematic perspective view of the turbine ring assembly of Figure 1 without part of the ring support structure;
    - Figure 4 is a third schematic perspective view of the turbine ring assembly of Figure 1 without the ring support structure.
    Detailed description of embodiments
    Figure 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 made 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 Dr 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 radial lugs for upstream and downstream attachment 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 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 confused 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 and a second portion 364. The first portion 363 extends between the first end 361 and the second portion 364, and the second portion 364 extends between the first portion 363 and the second end 364. The first portion 363 of the downstream 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 so as to give a certain flexibility to the downstream annular radial flange 36 and thus does not excessively constrain the ring turbine 1 in CMC.
    As illustrated in Figures 1 and 2, as well as in Figure 3 which shows a second schematic perspective view of the turbine ring assembly 1 of Figure 1 without part of the ring support structure 3, the ring support structure 3 further comprises a first and a second upstream flanges 33 and 34 each having a shape of a ring segment, the two upstream flanges 33 and 34 being fixed together on the upstream annular radial flange
    32.
    The first upstream flange 33 comprises a first free end 331 and a second end 332 in contact with the central crown 31, as well as a first portion 333 and a second portion 334, the first portion 333 extending between the first end 331 and the second portion 334, and the second portion 334 extending between the first portion 333 and the second end 332.
    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 radial 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 on the upstream annular radial flange 32 using screws 60 and nuts 61 for fixing, the screws 60 passing through the second portions 334 and 344 of the two upstream flanges 33 and 34 as well as 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.
    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.
    As illustrated in Figures 2 and 3 as well as in Figure 4 which shows a third schematic perspective view of the turbine ring assembly 1 of Figure 1 without the ring support structure 3, the sector ring 10 comprises two axial latching lugs 17 and 18 extending between the upstream and downstream latching radial lugs 14 and 16.
    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 axial latching lugs 17 and 18 extend more precisely, in the axial direction D A , between the second end 142 of the upstream radial latching lug 14 and the second end 162 of the downstream latching radial lug 16 .
    Each of the axial attachment tabs 17 and 18 comprises an upstream end, respectively 171 and 181, and a downstream end, respectively 172 and 182, the two ends, 171 and 172 on the one hand and 181 and 182 on the other hand, an axial hooking tab 17 or 18 being separated by a central part, 170 and 180. The upstream and downstream ends, 171 and 172 on the one hand and 181 and 182 on the other hand, of each hooking tab axial 17 and 18 extend in projection, in the radial direction Dr, from the second end 142, 162 of the radial lug 14, 16 to which they are coupled, so as to have a central part
    170 and 180 of the axial latching lug 17 and 18 raised relative to the second ends 142 and 162 of the upstream and downstream latching radial lugs 14 and 16.
    In the embodiment illustrated in FIGS. 1 to 4, each of the axial attachment tabs 17 and 18 is cut in half, forming an upstream part, respectively 173 and 183, and a downstream part, respectively 174 and 184.
    As illustrated in FIGS. 2 to 4, for each ring sector 10, the turbine ring assembly comprises a screw 19 and a fixing plate 20. The fixing plate 20 comprises a first and a second end 201 and 202 respectively in abutment against the first and second axial latching lugs 17 and 18.
    The first and second ends 201 and 202 of the fixing plate 20 each include a cutout forming a first stop, respectively 201a and 202a, in rotation, that is to say a stop in a direction orthogonal to the cutting plane comprising the axial direction D A and the radial direction Dr, and a second radial stop, respectively 201b and 202b, more particularly forming a stop in the radial direction D R in a direction going towards the center of the ring
    1. The cutout of each end 201 and 202 thus cooperates with a separate axial lug 17 or 18 to come to bear on the two sides at the same time of the same stop of the axial latch 17 or 18.
    The fixing plate 20 thus provides radial retention of the vein by exerting a radial force using the two radial stops 201b and 202b bearing on the internal face 17a and 18a, in the radial direction Dr, of each of the two legs axial attachment 17 and 18. The fixing plate 20 also blocks the ring sector 10, and therefore the ring 1, from any rotation around the axis of the turbine 1, using the two axial tabs attachment 17 and 18 each bearing on an opposite side of the fixing plate 20.
    The fixing plate 20 further comprises an orifice 21 provided with a tapping cooperating with a thread of the screw 19 to fix the fixing plate 20 to the screw 19. The screw 19 comprises a screw head 190 whose diameter is greater the diameter of an orifice 38 made in your central crown 31 of the support structure of the ring 3 through which the screw 19 is inserted before being screwed to the fixing plate 20.
    The radial securing 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 plate 20 screwed to the screw 19 and the ends 201 and 202 of which are in abutment against the axial latching lugs 17 and 18 of the ring sector 10, the screw head 190 and the ends 201 and 202 of the fixing plate exerting forces of opposite directions to hold the ring 1 and the ring support structure 3 together.
    To radially block the ring sector 10 in a direction opposite to that of the forces exerted by the second stops 201b and 202b of the ends 201 and 202 of the fixing plate 20 on the axial lugs 17 and 18, the assembly turbine ring comprises, in this embodiment, four pins 25 extending in the radial direction Dr between the central ring 31 of the ring support structure 3 and the axial lugs 17 and 18 of l 'ring 1. More specifically, the pins 25 include first ends 251 inserted by force into holes 35 made in the central ring 31 around the hole 38 receiving the screw 19 for fixing. In a variant, the pins could also be hooped in the orifices 35 by known metal assemblies such as adjustments H6-P6 or by contracting the pins in a cold fluid (for example nitrogen) before assembly or else held in said pins orifices by screwing, the pins 25 comprising in this case a thread cooperating with a thread formed in the orifices 35.
    The four pins 25 are distributed symmetrically with respect to the screw 19 so as to have two pins 25 extending between the first axial latching lug 17 and the ring support structure 3 and two pins 25 extending between the second axial latching lug 18 and the ring support structure 3. The pins 25 are dimensioned and installed so that a second end 252 of each pin 25, opposite the first end 251, comes to bear on the axial lugs associated attachment 17 or 18, more particularly on the corresponding external face 17b or 18b, thus blocking radially, with the aid of the fixing plate 20, the axial attachment tabs 17 and 18, and therefore the ring 1 , in both directions of the radial direction Dr of the 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 tab 14 and the first upstream annular flange 33, on the one hand, and between the downstream radial hooking tab 16 and the downstream annular radial flange 36 are included in the same rectilinear plane. Thus, when hot, there is no decambrage effect in the turbine ring 1 as can occur in the event of curvilinear bearings between the ring sectors and the ring support structure.
    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 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 wires made of ceramic fibers, for example wires made of SiC fibers such as those sold by the Japanese company Nippon Carbon under the name Hi-NicalonS, or wires made of carbon fibers.
    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 legs 14 and 16 from the sectors 10.
    The weaving can be of the interlock type, as illustrated. Other three-dimensional or multi-layer weave weaves can be used, such as 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 Inconei 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 fixing plates 20 are inserted in each of the free spaces extending between a first and a second axial lugs 17 and 18 for hooking a ring sector 10. Until it is screwed to the ring support structure 3, each plate fixing 20 is held in position in abutment against the axial latching lugs 17 and 18 of the associated ring sector using a holding lug mounted on the annular tool. The annular tool comprises a retaining lug for each fixing plate 20, that is to say for each ring sector 10. Each retaining lug is inserted between the two axial latching lugs 17 and 18 of a ring sector 10, on the one hand, and between the second end 162 of the downstream radial hooking tab 16 and the fixing plate 20. Each holding tab is then adjusted to hold the associated fixing plate 20 in bearing against the axial latching lugs 17 and 18. Each fixing screw 19 is then inserted into the orifice 38 associated with the central crown of the ring support structure 3 and screwed into the tapped hole 21 of the plate attachment 20 associated until the screw head 190 is in abutment against the central crown 31 and the pins 25, whose first end 251 has been forcibly inserted into the orifices 35, are in contact with the axial tabs of snap 17 and 18, so that the ring sector 10 has associated is held radially. The first and second flanges 33 and 34 are then fixed to the downstream annular radial flange 32 using screws 60 and nuts 61 to hold the turbine ring 1 axially, then the annular tool is removed.
    The invention thus provides a turbine ring assembly allowing the maintenance of each ring sector in a deterministic manner while allowing the ring sector, and by extension the ring, to deform under the effects of temperature. and pressure, in particular independently of the metal parts at the interface.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. 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 protrude, in the radial direction (D R ) of the turbine ring (1), a first and a 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), each ring sector (10) comprising a third and a fourth hooking lugs (17, 18) each extending in the direction ax ial (D A ) of the turbine ring (1), between the second end (142) of the first hooking lug (14) and the second end (162) of the second hooking lug (16), characterized in that each ring sector (10) is fixed to the ring support structure (3) by a fixing screw (19) comprising 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 (17,18).
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein each ring sector (10) comprises at least two pins (25) arranged on either side of said fixing screw (19) and each having a first and a second end (251, 252), the first end (251) of each pin (25) being fixed on the ring support structure (3) and the second end (252) of each pin (25) bearing against the sector ring (10).
    [3" id="c-fr-0003]
    3. The assembly of claim 1, comprising an annular shim disposed between the ring (1) and the ring support structure (3), and comprising, for each ring sector (10), an orifice through which the fixing screw (19), at least a first part bearing in the radial direction (Dr) against the ring support structure (3) and at least a second part bearing in the radial direction (Dr) against the sector ring (10), the annular shim being in one piece or sectorized in a plurality of sectorized shims.
    [4" id="c-fr-0004]
    4. Assembly according to one of claims 1 to 3, wherein the fixing plate (20) comprises first and second ends (201, 202) opposite to each other in the circumferential direction and respectively in contact with the third hooking tab and the fourth hooking tab (17, 18), the first end (201) comprising a first shoulder (201a) bearing against the third hooking tab (17) and the second end ( 202) comprising a second shoulder (202a) bearing against the fourth hooking tab (18), and the first and second shoulders (201a, 202a) each extending in the axial direction (D A ) and the radial direction (Dr) of the turbine ring (1).
    [5" id="c-fr-0005]
    5. Assembly according to one of claims 1 to 4, in which the ring support structure (3) comprises first and second annular flanges (32, 36), the first annular flange (32) being upstream of the second annular flange (36) relative to the direction of the air flow intended to pass through the turbine ring assembly, and the first and second hooking lugs (14, 16) of each ring sector (10 ) being held between the first and second annular flanges (32, 36) of the ring support structure (3), the second annular flange (36) comprising a tapered portion (364) relative to the rest of the second annular flange (36), the thinned portion (364) being disposed between a portion (363) bearing against the second attachment tab (16) and one end (362) of the second annular flange (36) integral with the rest of the structure ring support (3).
    [6" id="c-fr-0006]
    6. The assembly of claim 5, wherein the ring support structure (3) comprises a first annular flange (33) removable fixed to the first annular flange (32) and in abutment against the first hooking lug (14 ), and a second annular flange (34) having a first free end (341) and a second end (342) coupled to the first annular flange (32) and to the first annular flange (33), the first end (341) being distant, in the axial direction (D A ) from the turbine ring (1), from the first annular flange (33).
    [7" id="c-fr-0007]
    7. Assembly according to one of claims 5 or 6, 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 second annular flange (36) and the first annular flange (33).
    [8" id="c-fr-0008]
    8. An assembly according to claim 5 or 6, in which, for each ring sector (10), the faces of the second annular flange (36) and of the first annular flange (33) in contact respectively with the first and second hooking tabs (14, 16) comprise rectilinear bearing surfaces.
    [9" id="c-fr-0009]
    9. Assembly according to one of claims 1 to 8, in which the third hooking tab (17) and the fourth hooking tab (18) are each cut into two independent portions (173 and 174, 183 and 184) , each of the third and fourth hooking lugs (17, 18) comprising a first portion (173, 183) coupled to the first hooking lug (14) and a second portion (174, 184) coupled to the second lug d 'hooking (16).
    [10" id="c-fr-0010]
    10. Assembly according to one of claims 1 to 9, wherein the third and fourth hooking lugs (17, 18) are each coupled to the first and second hooking lugs (14, 16) respectively by a first and a second ends (171, and 172, 181 and 182) projecting, in the radial direction (Dr) of the turbine ring (1), in the extension of the first and second hooking lugs (14, 16 ) so as to raise the third and fourth hooking lugs (17, 18) relative to the second ends (142, 162) of the first and second hooking lugs (14,16).
    [11" id="c-fr-0011]
    11. Turbomachine comprising a turbine ring assembly (1) according to any one of claims 1 to 10.
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    同族专利:
    公开号 | 公开日
    US10502082B2|2019-12-10|
    US20180051581A1|2018-02-22|
    FR3055146B1|2020-05-29|
    引用文献:
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    US5653581A|1994-11-29|1997-08-05|United Technologies Corporation|Case-tied joint for compressor stators|
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    ES2398727T3|2009-03-09|2013-03-21|Snecma|Turbine ring set|
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    US10557365B2|2017-10-05|2020-02-11|Rolls-Royce Corporation|Ceramic matrix composite blade track with mounting system having reaction load distribution features|
    US11149563B2|2019-10-04|2021-10-19|Rolls-Royce Corporation|Ceramic matrix composite blade track with mounting system having axial reaction load distribution features|
    US11220925B2|2019-10-10|2022-01-11|Rolls-Royce North American Technologies Inc.|Turbine shroud with friction mounted ceramic matrix composite blade track|
    US11053817B2|2019-11-19|2021-07-06|Rolls-Royce Corporation|Turbine shroud assembly with ceramic matrix composite blade track segments and full hoop carrier|
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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
    FR1657822|2016-08-19|
    FR1657822A|FR3055146B1|2016-08-19|2016-08-19|TURBINE RING ASSEMBLY|FR1657822A| FR3055146B1|2016-08-19|2016-08-19|TURBINE RING ASSEMBLY|
    US15/680,465| US10502082B2|2016-08-19|2017-08-18|Turbine ring assembly|
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