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    • 专利摘要:
    A turbine ring assembly comprising ring sectors forming a turbine ring (1) and a ring support structure (3), each sector, according to a sectional plane 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 an outer face (12b) from which projecting first and second lugs (14, 16), said structure (3) having a ferrule (31) from which project first and second radial flanges (32, 36) between which the first and second legs (14, 16) are held. It comprises an annular flange (33) having a first portion bearing against the first leg (14), and a second portion removably attached to the first radial flange (32), the first portion comprising radial slots open at a free end the annular flange (33) and delimiting first portion sectors.
    公开号:FR3076578A1
    申请号:FR1850151
    申请日:2018-01-09
    公开日:2019-07-12
    发明作者:Nicolas Paul TABLEAU；Sebastien Serge Francis CONGRATEL；Antoine Claude Michel Etienne Danis；Clement Jean Pierre DUFFAU；Clement Jarrossay
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Background of the Invention The invention relates to a turbine ring assembly comprising a plurality of ring sectors made 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 FR 2 540 939, GB 2 480 766, EP 1 350 927, US 2014/0271145, US 2012/082540 and FR 2 955 898 which disclose turbine ring assemblies are also known.
    There is a need to improve the existing turbine ring assemblies 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.
    OBJECT 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 avoid that it starts to vibrate, 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 metal parts at the interface, and, on the other hand, while improving the seal between the non-vein sector and the vein sector, in particular the seal of the cavity located at the radially upper part of the ring. All this by simplifying handling and reducing their number for mounting the ring assembly. The invention further aims to propose a set of turbine rings provided with an upstream flange making it possible, on the one hand, to ensure optimal sealing of the cavity defined by the ring, and, on the other hand , to efficiently accommodate the different axial lengths of each CMC ring sector that makes up the ring crown. In other words for this second point, the rectilinear contact between the upstream part of the ring and the tab of the upstream flange must be effective for each sector of the ring, although these have different widths, these widths being indeed impacted by manufacturing tolerances.
    An object of the invention provides a turbine ring assembly comprising a plurality of ring sectors of ceramic matrix composite material forming a turbine ring and a ring support structure, each ring sector having, according to a section plane defined by an axial direction and a radial direction of the turbine ring, a part forming an annular base with, in the radial direction of the turbine ring, a radially internal face defining the internal face of the turbine ring and a radially outer face from which project first and second hooking lugs, the ring support structure comprising a central ferrule from which project first and second a second radial flanges from which the first and second hooking lugs of each ring sector are maintained.
    According to a general characteristic of the object, the turbine ring assembly comprises a first annular flange disposed upstream of the turbine ring and of the first radial flange relative to the direction of an air flow intended to pass through the turbine ring assembly. The first annular flange has a first free end, a second end opposite the first end, a first portion extending from the first end, and a second portion extending between the first portion and the second end, the first portion of the first flange being in abutment against the first hooking tab of the turbine ring. The second portion of the first flange is attached to the first radial flange of the central ferrule of the ring support structure, and the first portion of the first annular flange includes a plurality of radial slots which open at the first end of the first annular flange delimiting sectors of the first portion of the first annular flange. Said first portion sectors extend in a circumferential direction of the turbine ring.
    Integrating a first fully sectored upstream annular flange would allow each sector of the first upstream sectorized flange to adapt to the width of the CMC ring which is opposite, that is to say the axial length of each ring sector. Thus the axial leaks, in particular at the level of the rectilinear supports, between the ring and the first upstream flange are canceled. However, such a solution would cause significant leaks in the sectors between each sectored flange. And this, even if devices such as sealing tabs are put in place to mitigate these leaks towards the external cavities of the ring.
    Directly integrating a first annular flange in a single piece, in other words not sectorized, would ensure axial sealing between the ring sectorized in CMC and the annular casing, in particular by avoiding inter-sector leaks compared to a case where the first upstream flange is segmented. However, the continuity of the first upstream annular flange, in particular at the level of the rectilinear supports facing the ring sectors which do not all have the same width (because of manufacturing tolerances) would cause significant leaks at the level rectilinear supports. The first upstream annular flange would not accommodate the ring sectors which have different widths well enough.
    The first portion of the first annular flange according to the invention thus makes it possible, by its annular conformation without sectorization, to ensure axial sealing between the turbine ring sectorized in CMC and the annular casing. And the sectoring of the second portion of the first annular flange according to the invention makes it possible to accommodate each sector of the second portion of the first annular flange with a sector of the turbine ring opposite. In this way, the leak at the axial supports of the CMC turbine ring is canceled. The turbine ring assembly thus provided with a first semi-sectored annular flange therefore makes it possible overall to reduce leaks between the cavity of the turbine ring and the outside.
    Preferably, the second portion of the first flange is removably attached to the first radial flange of the central ferrule of the ring support structure.
    According to a first aspect of the turbine ring assembly, the first annular flange may comprise, for each radial slot, a discharge orifice, and each radial slot opens firstly at the first end of the first annular flange and d elsewhere in the discharge port. In other words, each radial slot may include a first end open to the first end of the first annular flange and a second end opposite to said first end of the radial slot and open to the discharge orifice.
    The transition between the second sectored portion and the first annular portion of the first flange is hereinafter called the groove bottom. The bottom of the groove constitutes the seat of tangential stress concentrations when the first semi-sectored annular flange is subjected to a radial temperature gradient. These concentrations of tangential stresses at the bottom of the groove can initiate cracks and thus decrease the life of the first annular flange.
    The discharge orifices make it possible to significantly reduce the stress concentrations by diffusing the stresses around the discharge orifice.
    According to a second aspect of the turbine assembly, the discharge orifices can be circular orifices having a diameter between 0.1 mm and 8 mm and preferably between 1 mm and 5 mm.
    The diameter of the circular discharge orifice plays a key role in reducing stress, as shown in the graph in FIG. 1 representing the evolution of the stress rate as a function of the diameter of the discharge orifice, the rate being determined with respect to a first upstream annular flange without discharge port. On this graph, we can see that the addition of a discharge hole up to a diameter of 5 mm makes it possible to lower the maximum stress level by 62%. The addition of these discharge orifices therefore makes it possible to ensure the structural integrity of the first annular flange when it is subjected to a radial temperature gradient.
    In a variant, the discharge orifices can be oblong radial orifices, that is to say orifices having an oblong shape having a length extending in the radial direction and a width in a direction orthogonal to the radial direction, the length being greater than the width of the oblong opening.
    In another variant, the discharge orifices may be tangential oblong orifices, that is to say orifices having an oblong shape having a width extending in the radial direction and a length in a direction orthogonal to the radial direction , in other words a width extending in a tangential direction, the length being greater than the width of the oblong orifice.
    According to a third aspect of the turbine assembly, the turbine ring assembly further includes an inter-sector seal for each radial slot of the first annular flange, each radial slot having first and second surfaces parallel in direction radial and in the axial direction, the first surface comprising a first groove and the second surface comprising a second groove extending opposite the first groove symmetrically to the first groove with respect to a plane extending in the axial direction and in the radial direction along the radial slot.
    The inter-sector joints, or sealing tongues, inserted in the radial slots make it possible to reduce leaks at the level of the cavity of the ring.
    According to a fourth aspect of the turbine ring assembly, the ring assembly further comprises a second annular flange disposed upstream of the first annular flange relative to the direction of the air flow intended to pass through the assembly d turbine ring, the second annular flange having a first free end and a second end opposite the first end, the first end of the second annular flange being spaced from the first end of the first annular flange in the axial direction, the second ends of the first and second annular flanges being removably attached to the first radial flange of the central ferrule of the ring support structure.
    The second annular flange separated from the first annular flange at its free end makes it possible to provide the turbine ring assembly with an upstream flange dedicated to the recovery of the force of the high pressure distributor (DHP). The second annular flange upstream 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 through the ring which, when in CMC, has low mechanical allowability.
    Indeed, leaving a space between the first ends of the first and second annular flanges allows to deflect the force received by the second flange, upstream of the first annular flange which is in contact with the turbine ring, and to do so pass directly to the central ferrule of the ring support structure via the second end of the second annular flange, without impacting the first annular flange and therefore without impacting the turbine ring. The first end of the first 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 annular flange can induce its tilting. This tilting can cause uncontrolled contact between the lower parts, that is to say the first ends, of the second annular flange and of the first annular flange in contact with the turbine ring, which would have the consequence of transmitting directly DHH effort at the ring.
    Alternatively, the second end of the first flange and the second end of the second flange can be separated by a contact stop. The contact stop provided between the second ends of the first and second annular flanges makes it possible to avoid contact between the lower part of the second annular flange, disposed upstream of the first flange, and that of the first annular flange, following this tilting. The direct transit of DHH effort to the ring is therefore avoided.
    In addition, the removable nature of the annular flanges 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 in 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 supported or vented during their crown assembly.
    The solution defined above for the ring assembly thus makes it possible to maintain each ring sector in a deterministic manner, that is to say to control its position and to prevent it from vibrating, while by improving the seal 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, notably independently of the metallic parts at the interface.
    According to a fifth aspect of the turbine ring assembly, the first flange may have a thickness in the axial direction less than the thickness in the axial direction of the second flange.
    The fineness of the second end of the first annular flange provides flexibility to the upstream part of the support structure intended to be in contact with the ring.
    According to a sixth aspect of the turbine ring assembly, the second radial flange of the ring support structure has a first free end and a second end integral with the central ferrule of the ring support structure, the first end of the second radial flange being in contact with the second hooking tab of the turbine ring and having a thickness in the axial direction greater than the thickness of the first end of the first annular flange.
    Controlling the rigidity at the level of the axial contacts of the ring support structure with the ring ensures that the seal is maintained in all circumstances, without however inducing too high axial forces on the ring. The increased thickness of the downstream part of the ring support structure, in particular of the first end of the second radial flange, the free end, makes it possible to offer greater rigidity to the downstream part of the ring structure. ring support relative to its upstream part comprising the first annular radial flange and the first and second annular flanges. This increased rigidity makes it possible to reduce the downstream axial leaks between the ring and the casing, that is to say the ring support structure, in the case of a rectilinear support.
    According to a seventh aspect of the turbine ring assembly, the ring sector may 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 include, for each ring sector, at least three pins for radially maintaining the ring sector in position, the first and second lugs for hooking 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 u n receiving hole of one of the pawns.
    According to an eighth 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 ninth aspect of the turbine ring assembly, the ring sector can 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 me and fourth legs hanging. The ring sector also comprises radial pins extending between the central ferrule and the third 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, already presented, presents a graph of revolution of the maximum stress exerted on the first annular flange as a function of the diameter of the discharge orifice; - Figure 2 is a schematic perspective view of a first embodiment of a turbine ring assembly according to the invention; - Figure 3 is a schematic exploded perspective view of the turbine ring assembly of Figure 2; - Figure 4 is a schematic sectional view of the turbine ring assembly of Figure 2; - Figures 5A and 5B are respectively a partial schematic perspective view of the first upstream annular flange of Figure 2 and a zoom in on part of the first upstream annular flange; - Figure 6 is a schematic sectional view of the first upstream annular flange of Figure 5A along the section plane VI-VI; - Figure 7 is a schematic sectional view of a second embodiment of the turbine ring assembly; - Figure 8 shows a schematic sectional view of a third embodiment of the turbine ring assembly.
    Detailed description of embodiments
    FIG. 2 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 blades rotary (not shown). The turbine ring 1 is formed from a plurality of ring sectors 10, FIG. 2 being a view in radial section. The arrow DA 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 ring turbine 1 which is actually a complete ring.
    As illustrated in Figures 3 and 4 which respectively show a schematic exploded perspective view and a sectional view of the turbine ring assembly of Figure 2, the sectional view being along a section plane comprising the radial direction Dr and the axial direction DA, each ring sector 10 has, according to a plane defined by the axial directions DA and radial 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 hooking upstream and downstream, 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 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 to define 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 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 even over the entire circumferential length of the ring sector 10.
    In FIGS. 2 and 3 the portion of the turbine ring 1 shown comprises a complete ring sector 10 surrounded by two half ring sectors 10. For a better understanding, the complete ring sector is referenced 10a and the half ring sectors are referenced 10b in FIG. 3.
    As illustrated in FIGS. 2 to 4, the ring support structure 3 which is integral with a turbine casing comprises a central ferrule 31, extending in the axial direction DA, and having an axis of revolution combined 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 hooking 16. The first portion 363 and the third portion 365 have an increased thickness compared to that of the second portion 364 to provide increased rigidity to the second radial flange relative to the upstream part comprising in particular the first radial flange 32, so as to reduce the axial leaks of the ring in the case of a rectilinear support.
    The first annular radial flange 32 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 321 and a second end 322 secured to the central ferrule 31.
    As illustrated in FIGS. 1 to 3, the turbine ring assembly 1 comprises a first annular flange 33 and a second annular flange 34, the two annular flanges 33 and 34 being detachably fixed on the first radial flange annular 32. The first and second annular flanges 33s and 34 are arranged upstream of the turbine ring 1 relative to the direction F of flow of the gas flow in the turbine.
    The first annular flange 33 is arranged downstream of the second annular flange 34. The first annular flange 33 is in one piece while the second annular flange 34 can be sectorized into a plurality of annular sectors of the second flange 34 or be in a single room.
    The first annular flange 33 has a first free end 331 and a second end 332 removably attached to the ring support structure 3, and more particularly to the first annular radial flange 32. In addition, the first annular flange 33 has 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 annular flange 34 has a first free end 341 and a second end 342 opposite the first end 341 and in contact with the central crown 31. The second end 342 of the second annular flange 34 is also detachably fixed to the structure of ring support 3, and more particularly to the first annular radial flange 32. The second annular flange 34 further comprises a first portion 343 and a second portion 344, the first portion 343 extending between the first end 341 and the second portion 344, and the second portion 344 extending between the first portion 343 and the second end 342.
    The first portion 333 of the first upstream flange 33 is in abutment on the upstream hooking lug 14 of the ring sector 10. The first and second upstream flanges 33 and 34 are shaped to have the first portions 333 and 343 distant from it. one from the other and the second portions 334 and 344 in contact, the two flanges 33 and 34 being detachably fixed on the upstream annular radial flange 32 using screws 60 and nuts 61 for fixing, the screws 60 passing through orifices 3340, 3440 and 320 provided respectively in the second portions 334 and 344 of the two upstream flanges 33 and 34 as well as in the upstream annular radial flange 32.
    When the ring assembly 1 is mounted, the first portion 333 of the first annular flange 33 is in abutment against the upstream radial hooking lug 14 of each of the ring sectors 10 making up the turbine ring 1, and the second portion 334 of the first annular flange 34 is in abutment against at least part of the first annular radial flange 32.
    The first and second upstream annular flanges 33 and 34 are shaped to have the first portions 333 and 343 distant from each 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 orifices 3340, 3440 and 320 provided respectively in the second portions 334 and 344 of the two upstream flanges 33 and 34 as well as in the upstream annular radial flange 32.
    The second annular flange 34 is dedicated to the recovery of the force of the high pressure distributor (DHP) on the ring assembly 1 by passing this force towards the casing line which is more mechanically robust, that is to say say towards the line of the ring support structure 3 as illustrated by the force arrows E shown in FIG. 4. The residual force, which passes through the first upstream flask 33 is reduced since the first portion 333 of the first upstream flange 33 has a reduced section, and is therefore more flexible, which makes it possible to apply a minimum of force to the ring 1 CMC.
    In the axial direction DA, the downstream annular radial flange 36 of the ring support structure 3 is separated from the first upstream annular flange 33 by a distance corresponding to the spacing of the upstream and downstream hooking radial lugs 14 and 16 so as to maintain the latter between the downstream annular radial flange 36 and the first upstream flange 33.
    To keep the ring sectors 10, and therefore the turbine ring 1, in position with the ring support structure 3, the ring assembly comprises, for each ring sector 10, two first pins 119 cooperating with the upstream hooking lug 14 and the first annular flange 33, and two second pins 120 cooperating with the downstream hooking lug 16 and the second annular radial flange 36.
    For each corresponding ring sector 10, the first portion 333 of the first annular flange 33 comprises two orifices 3330 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, integral with the external face 12b of the annular base 12 and a second end, 142 and 162, free. The second end 142 of the upstream radial lug 14 comprises two first ears 17 each comprising an orifice 170 configured to receive a first pin 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 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 with a 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.
    Each ring sector 10 further comprises rectilinear bearing surfaces 110 mounted on the faces of the first annular flange 33 and of the second annular radial flange 36 in contact respectively with the upstream radial lug 14 and the radial lug d downstream attachment 16, that is to say on the downstream face of the first annular flange 33 and on the upstream face of the second annular radial flange 36.
    The rectilinear supports 110 are located under the orifices 3330 for receiving the first two pins 119, that is to say inside the orifices 3330 in the radial direction.
    In a variant, the rectilinear supports could be 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.
    The rectilinear supports 110 make it possible to have controlled sealing zones. Indeed, the bearing surfaces 110 between the first upstream annular flange 33 and the upstream radial hooking tab 14, on the one hand, and between the downstream annular radial flange 36 and the downstream radial hooking tab 16 are included in the same rectilinear plane.
    More specifically, having supports on radial planes makes it possible to overcome the effects of axial tilting of the turbine ring 1. In fact, during the tilting of the ring in operation, the rectilinear support makes it possible to maintain a complete sealing line.
    The radial maintenance of the ring 1 is ensured by the first annular flange 33 which is pressed against the first annular radial flange 32 of the ring support structure 3 and on the upstream radial hooking lug 14. The first annular flange 33 seals between the vein cavity and the cavity outside the vein of the ring.
    The second annular flange 34 provides the connection between the downstream part of the DHP, the ring support structure 3, or casing, by radial surface contact, and the first annular flange 33 by axial surface contact.
    The ring support structure 3 further comprises radial pins 38 which enable the ring to be pressed in the low radial position, that is to say towards the vein, in a deterministic manner. There is indeed a clearance between the axial pins and the bores on the ring to compensate for the differential expansion between the metal and the CMC elements which takes place when hot. The radial pins 38 cooperate with orifices 380 produced in the radial direction Dr in the central ring 31 of the ring support structure 3.
    FIGS. 5A and 5B respectively illustrate a partial schematic perspective view of the first upstream annular flange 33 of FIG. 2 and a zoom of a part of the first upstream annular flange 33.
    As illustrated in FIGS. 5A and 5B, the first portion 333 of the first annular flange 33 has a plurality of radial slots 336 extending from the first end 331. The radial slots 336 have a first end 3361 and a second end 3362 opposite the first end 3361, the first end 3361 being inside the second end 3362 in the radial direction Dr. The first ends 3361 of the radial slots 36 are open on the first end 331 of the first annular flange 33. Each slot radial 336 has first and second surfaces 3364 parallel in the radial direction Dr and in the axial direction Da, the distance between the first and the second surface 3364, which corresponds to the tangential thickness of the grooves, can be between 0, 1 mm and 1 mm. The radial length of the slots can be between 10 and 90% of the complete radial length of the upstream flange. A short radial length of slit promotes the reduction of leaks, but degrades the capacity of accommodation of the sectors of the flange vis-à-vis the sectors of ring. A high radial slot length promotes accommodation of the flange sectors with respect to the ring sectors but increases the level of leakage.
    Each pair of adjacent radial slots 336 thus delimits, between the two adjacent radial slots 336, a sector of first portion 337 of the first annular flange 33. Each sector of first portion 337 has a shape of ring sector, that is to say - say a solid formed by two arcs of concentric circles and of different radii and two segments of lines each corresponding to a segment of the radius of the large arc of circle included between the small arc of circle and the large arc of circle. Each first portion sector 337 is independent of the other first portion sectors 337 since the radial slots 36 are open at their first end 3361.
    The first annular flange 33 further comprises discharge orifices 338, and more particularly a discharge orifice 338 by radial slot 336. Each discharge orifice 338 communicates with the second end 3362 of a radial slot 36. In other words, each orifice discharge 338 is formed in the first annular flange 33 at the second end 3362 of a radial slot so that the second end 3362 of a radial slot is open on the corresponding discharge port 338.
    In the first embodiment illustrated in FIGS. 2 to 5B, the discharge orifices 338 are circular orifices having a diameter between 1 mm and 5 mm.
    In FIG. 6 is illustrated a schematic sectional view of the first upstream annular flange of FIG. 5A according to the cutting plane VIVE
    The section plane VI-VI comprises the radial direction Dr and the axial direction DA and passes through a radial slot 336 of the first annular flange 33.
    As illustrated in FIG. 6, the first annular flange 33 comprises an inter-sector seal 339 for each radial slot 336.
    Each radial slot 336 has first and second surfaces 3364 on either side of the radial slot 336. FIG. 6 being a section made through a radial slot 336, only a surface 3364 of radial slot 336 is shown . The first and second surfaces 3364 of a radial slot 336 are parallel, that is to say that they are arranged opposite one another over the entire radial length of the radial slot 336.
    The first surface 3364 comprises a first groove 3365 extending mainly in the radial direction Dr. Likewise, the second surface comprises a second groove extending mainly in the radial direction Dr. The second groove extends opposite the first groove 3365 symmetrically to the first groove 3365 relative to the section plane VI-VI.
    The first and second grooves 3365 of a radial slot 336 are shaped to receive the inter-sector seal 339, or sealing strip. The inter-sector joint thus ensures a seal between the sectors of the first portion 333 of the first annular flange 33.
    In Figure 7 is presented a schematic sectional view of a second embodiment of the turbine ring assembly.
    The second embodiment illustrated in Figure 7 differs from the first embodiment illustrated in Figures 2 to 6 in that the ring sector 10 has, in the plane defined by the axial directions Da and radial Dr, a section in K-shape 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 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 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 a greater seal than in the case of ad hoc support. The second end 1620 of the downstream radial lug 160 is held between a portion 3610 of the second annular radial flange 36 projecting in the axial direction DA 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 hooking lug 140 is held between a portion 3310 of the first annular flange 33 projecting in the axial direction DA from the first end 331 of the first annular flange 33 in the direction of flow F and the free end of the associated screw 38.
    In Figure 8 is presented a schematic sectional view of a third embodiment of the turbine ring assembly.
    The third embodiment illustrated in FIG. 8 differs from the first embodiment illustrated in FIGS. 2 to 6 in that the ring sector 10 has in the plane defined by the axial directions Da and radial Dr, over 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 using a screw 19 and a fixing part 20, the screws 38 being eliminated.
    In the third embodiment illustrated in FIG. 8, 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 DA, between the second end 142 of the upstream radial latching lug 14 and the second end 162 of the downstream latching radial lug 16.
    The axial latching tab 17 'includes an upstream end 171' and an 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 part 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 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 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 a variant, the radial retention of the ring down can be ensured by means of four radial pins pressed on the axial lug 17 ', and the radial retention upwards of the ring can be ensured by a pick head, secured to the screw 19, placed under the ring in the cavity between the axial latching lug 17 ′ and the external face 12b of the annular base.
    In the second and third embodiments illustrated in FIGS. 7 and 8, the second end 342 of the second annular flange 34 comprises a contact stop 340 projecting in the axial direction Da between the second annular flange 34 and the first annular flange 33. The contact stop 340 makes it possible to maintain a distance between the first end 331 of the first annular flange 33 and the first end 341 of the second annular flange 34 during the tilting of the second annular flange 34 induced by the DHP force.
    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. 2 to 6.
    Each ring sector 10 described above is made of ceramic matrix composite material (CMC) by forming a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix. .
    For the production of the fiber preform, it is possible to use wires made of ceramic fibers 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 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 multilayer 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 itself. 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 an alloy based on nickel, cobalt or titanium.
    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 holes 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 support structure. ring 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 first annular flange 33 is positioned by placing the second portion 334 of the first annular flange 33 in abutment against the first radial flange and the rectilinear supports 110 of the first portion 333 of the first annular flange 33 in abutment against the first tab d hooking 14 by adjusting the first annular flange 33 so that the first pins 117 are inserted into the orifices 3330 of the first portion 333 of the first annular flange 33.
    The second annular flange 34 is then positioned against the first annular flange 33, then, to fix the two upstream flanges 33 and 34 together to the ring support structure 3, screws 60 are inserted into the holes 3440, 3340 and 320 , coaxial, provided in the second portion 344 of the second upstream flange 34, in the second portion 334 of the first flange and in the upstream annular radial flange 32 and each of the screws 60 is tightened with a nut 61. The ring 1 is thus held in axially position using the first annular flange 33 and the second annular radial flange 36 bearing respectively upstream and downstream on their respective rectilinear support surfaces 110. When installing the first annular flange 33, an axial preload can be applied to the first annular flange 33 and to the upstream radial hooking lug 14 in order to compensate for the effect of differential expansion between the CMC material of the ring 1 and the metal of the ring support structure 3. The first annular flange 33 is held in axial stress by mechanical elements placed upstream as shown in dotted lines in FIG. 3. The ring 1 is held in the radially position using the first and second pins 119 and 120 cooperating with the first and second ears 17 and 18 and the holes 3340 and 3650 of the first annular flange 33 and the annular radial flange 36. The invention thus provides a set of turbine ring 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 in particular independently of the metal parts at the interface, and, on the other hand, while improving the sealing between the non-vein sector and the vein sector, in particular the sealing of the cavity located at the radially upper part of the ring. All this by simplifying handling and reducing their number for mounting the ring assembly. The invention further provides a turbine ring assembly provided with an upstream flange making it possible, on the one hand, to ensure optimum sealing of the cavity defined by the ring, and, on the other hand, to efficiently accommodate the different axial lengths of each CMC ring sector that makes up the ring crown. In other words for this second point, the rectilinear contact between the upstream part of the ring and the tab of the upstream flange must be effective for each sector of the ring, although these have different widths, these widths being indeed impacted by manufacturing tolerances.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. A turbine ring assembly comprising a plurality of ring sectors (10) of ceramic matrix composite material forming a turbine ring (1) and a ring support structure (3), each ring sector (10) having, according to a cutting plane defined by an axial direction (DA) and a radial direction (DR) of the turbine ring (1), an annular base portion (12) with, in the radial direction ( DR) of the turbine ring (1), a radially internal face (12a) defining the internal face of the turbine ring (1) and a radially external face (12b) from which project a first and second hooking lugs (14, 16), the ring support structure (3) comprising a central ferrule (31) from which project first and second radial flanges (32, 36) from which the first and second hooking lugs (14, 16) of each ring sector (10) are maintained, characterized ized that it comprises a first annular flange (33) disposed upstream of the turbine ring (1) and the first radial flange (32) relative to the direction of an air flow (F) intended to pass through the turbine ring assembly (1) and having in the radial direction (Dr) a first free end (331), a second end (332) opposite the first end (331), a first portion (333) extending from the first end (331), and a second portion (334) extending between the first portion (333) and the second end (332), the first portion (333) of the first flange (33) being in bearing against the first hooking tab (14), the second portion (334) of the first flange (33) being fixed to the first radial flange (32) of the central ferrule (31) of the ring support structure ( 3), and the first portion (333) of the first annular flange (33) comprising a plurality of radial slots (336) opening at the first re end (331) of the first annular flange (33) and which delimit sectors of the first portion (337) of the first annular flange (33).
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein the first annular flange (33) comprises, for each radial slot (336), a discharge opening (338), and each radial slot (336) opens firstly to the first end (331) of the first annular flange (33) and on the other hand in the discharge orifice (338).
    [3" id="c-fr-0003]
    3. Assembly according to claim 2, in which the discharge orifices (338) are circular orifices having a diameter between 0.5 mm and 8 mm and preferably between 1 mm and 5 mm.
    [4" id="c-fr-0004]
    4. Assembly according to one of claims 1 to 3, further comprising an inter-sector joint (339) for each radial slot (336) of the first annular flange (33), each radial slot (336) having a first and a second surfaces (3364) parallel in the radial direction (Dr) and in the axial direction (DA), the first surface (3364) comprising a first groove (3365) and the second surface comprising a second groove extending symmetrically to the first groove (3365) relative to a plane extending in the axial direction (DA) and in the radial direction (DR) along the radial slot (336), a first portion of the inter-sector joint (339) being inserted in the first groove (3365) and a second portion of the intersector seal (339) being inserted in the second groove.
    [5" id="c-fr-0005]
    5. Assembly according to one of claims 1 to 4, further comprising a second annular flange (34) disposed upstream of the first annular flange (33) relative to the direction of the air flow (F) intended to pass through the turbine ring assembly (1) and having a first free end (341) and a second end (342) opposite the first end (341), the first end (341) of the second annular flange (34) being distant from the first end (331) of the first annular flange (33) in the axial direction (DA), the second ends (332, 342) of the first and second annular flanges (33, 34) being removably attached to the first radial flange (32) of the central ferrule (31) of the ring support structure (3).
    [6" id="c-fr-0006]
    6. The assembly of claim 5, wherein the first flange (33) has a thickness in the axial direction (DA) less than the thickness in the axial direction (DA) of the second flange (34).
    [7" id="c-fr-0007]
    7. Assembly according to one of claims 5 or 6, wherein the second radial flange (36) of the ring support structure (3) has a first end (361) free and a second end (362) integral with the central ferrule (31) of the ring support structure (3), the first end (361) of the second radial flange (36) being in contact with the second hooking lug (16) of the ring turbine (1) and having a thickness in the axial direction (DA) greater than the thickness of the first end (331) of the first annular flange (33).
    [8" id="c-fr-0008]
    8. Assembly according to one of claims 1 to 7, in which the ring sector has a section in π according to the cutting plane defined by the axial direction (DA) and the radial direction (Dr), 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 free end (142, 162), 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 leg e hooking (16, 14) in the radial direction (Dr) of the turbine ring (1), each receiving lug (17, 18) having an orifice (170, 180) for receiving one of the pins (119, 120).
    [9" id="c-fr-0009]
    9. Assembly according to one of claims 1 to 7, in which the ring sector has a section in K according to the cutting plane defined by the axial direction (DA) and the radial direction (Dr) the first and a second hooking lugs (14,16) having an S shape.
    [10" id="c-fr-0010]
    10. Assembly according to one of claims 1 to 7, wherein the ring sector has an O-section along the cutting plane defined by the axial direction (DA) and the radial direction (Dr), the first and the second attachment tabs (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 fourth attachment tabs (17 ', 170') each extending in the axial direction (DA) of the turbine ring (1), between a second end (142) of the first tab hooking (14) and a second end (162) of the second hooking tab (16), each ring sector (10) being 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 plate fixing (20), the fixing plate (20) cooperating with the third and fourth hooking lugs (17 ', 170').
    [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
    WO2019138168A1|2019-07-18|
    US20200355088A1|2020-11-12|
    FR3076578B1|2020-01-31|
    US11078804B2|2021-08-03|
    CN111630252A|2020-09-04|
    EP3737837A1|2020-11-18|
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    FR3064023B1|2017-03-16|2019-09-13|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3076578B1|2018-01-09|2020-01-31|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3080146B1|2018-04-17|2021-04-02|Safran Aircraft Engines|CMC DISTRIBUTOR WITH EFFORT RELIEF|
    FR3080145B1|2018-04-17|2020-05-01|Safran Aircraft Engines|DISTRIBUTOR IN CMC WITH RESUMPTION OF EFFORT BY A WATERPROOF CLAMP|FR3076578B1|2018-01-09|2020-01-31|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    法律状态:
    2018-12-18| PLFP| Fee payment|Year of fee payment: 2 |
    2019-07-12| PLSC| Publication of the preliminary search report|Effective date: 20190712 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 3 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 4 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1850151A|FR3076578B1|2018-01-09|2018-01-09|TURBINE RING ASSEMBLY|
    FR1850151|2018-01-09|FR1850151A| FR3076578B1|2018-01-09|2018-01-09|TURBINE RING ASSEMBLY|
    US16/960,726| US11078804B2|2018-01-09|2018-12-24|Turbine shroud assembly|
    EP18842450.1A| EP3737837A1|2018-01-09|2018-12-24|Turbine shroud assembly|
    PCT/FR2018/053546| WO2019138168A1|2018-01-09|2018-12-24|Turbine shroud assembly|
    CN201880085687.XA| CN111630252A|2018-01-09|2018-12-24|Turbine shroud assembly|
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