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  • 专利说明
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    • 专利摘要:
    The present invention relates to a turbine ring assembly comprising a plurality of ring sectors (110) and a ring support structure (13), the ring assembly further comprising, for each ring sector a distribution member (150) of the cooling air attached to the ring support structure (13) and positioned in a first cavity (151) defined between the turbine ring and the ring support structure .
    公开号:FR3056633A1
    申请号:FR1758747
    申请日:2017-09-21
    公开日:2018-03-30
    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:

    Holder (s): SAFRAN AIRCRAFT ENGINES Simplified joint-stock company.
    Agent (s): CABINET BEAU DE LOMENIE.
    FR 3 056 633 - A1 (54) TURBINE RING ASSEMBLY INCLUDING COOLING.
    (© The present invention relates to a turbine ring assembly comprising a plurality of ring sectors (110) and a ring support structure (13), the ring assembly further comprising, for each sector d ring, a cooling air distribution element (150) fixed to the ring support structure (13) and positioned in a first cavity (151) delimited between the turbine ring and the support structure d 'ring.
    AN AIR DISTRIBUTION ELEMENT
    Invention background
    The invention relates to a turbine ring assembly comprising a plurality of ring sectors made of ceramic matrix composite material (CMC material) or metallic material.
    The field of application of the invention is in particular that of aeronautical gas turbine engines. The invention is however applicable to other turbomachinery, for example industrial turbines.
    In aeronautical gas turbine engines, improving efficiency and reducing certain polluting emissions lead to the search for operation at ever higher temperatures. 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 very hot flows. The cooling of a metal turbine ring requires the use of a large amount of cooling air, which has a significant impact on the performance of the engine since the cooling flow used is taken from the main flow of the engine.
    The use of ring sectors made of CMC material has been proposed in order to limit the ventilation required for cooling the turbine ring and thus increase the performance of the engine.
    However, even if CMC ring sectors are used, it is still necessary to use a significant amount of cooling air. The turbine ring is, in fact, confronted with a hot source (the vein in which the flow of hot gas flows) and a cold source (the cavity delimited by the ring and the casing, designated below by the expression "ring cavity"). The ring cavity must be at a pressure higher than that of the vein in order to prevent gas coming from the vein from going up in this cavity and coming to burn the metallic parts. This overpressure is obtained by taking "cold" air from the compressor, which has not passed through the combustion chamber, and routing it to the ring cavity. Maintaining such an overpressure therefore makes it impossible to completely cut off the “cold” air supply to the ring cavity.
    In addition, studies carried out by the Applicant have shown that a ring, made of CMC or metallic material, cooled by known cooling systems can have penalizing thermal gradients which generate unfavorable mechanical stresses. In addition, the cooling technologies used for a metal ring may not be easily transposable to a ring made of CMC material.
    Whatever the nature of the material used for the ring sectors, it would therefore be desirable to improve the existing cooling systems in order to limit the unfavorable thermal gradients in the cooled ring sectors and therefore the generation of unfavorable stresses. It would also be desirable to improve the existing cooling systems in order to optimize the quantity of cooling air actually used for cooling the ring, in particular by limiting the leakage of the cooling air.
    The invention specifically aims to meet the aforementioned needs.
    Subject and summary of the invention
    To this end, the invention proposes, according to a first aspect, a turbine ring assembly comprising a plurality of ring sectors of composite material with ceramic matrix or of metallic material forming a turbine ring and a support structure d ring, each ring sector having, according to a cutting plane defined by an axial direction and a radial direction of the turbine ring, an annular base portion with, in the radial direction of the turbine ring, a internal face defining the internal face of the turbine ring and an external face from which extend a first and a second hooking lugs, the ring support structure comprising a first and a second radial lugs between which the first and second hooking lugs of each ring sector are maintained, as well as a plurality of cooling air supply orifices, the turbine ring assembly further comprising, for each ring sector, a cooling air distribution element fixed to the ring support structure and positioned in a first cavity delimited between the turbine ring and the ring support structure, said element distribution comprising a body defining an internal volume for distributing the cooling air and comprising a multi-perforated plate communicating with the internal volume and opening into a second cavity delimited between the turbine ring and the multi-perforated plate, l distribution element further comprising at least a cooling air guide portion extending from the body and defining an internal channel in communication with one of the cooling air supply orifices and opening into the internal volume distribution of cooling air.
    The axial direction of the turbine ring corresponds to the direction along the axis of revolution of the turbine ring as well as to the direction of flow of the gas flow in the stream. The radial direction corresponds, for its part, to the direction along a radius of the turbine ring (straight line connecting the center of the turbine ring to its periphery).
    The implementation, for each ring sector, of a cooling air distribution element as described above has several advantages.
    First, the inner channel defined by the guide portion of the distribution element is located in the extension of the cooling air supply orifice of the ring support structure, which allows optimize the fraction of the cooling air actually transferred into the internal distribution volume of the cooling air. In this way, the quantity of cooling air transmitted to the multi-perforated plate is maximized which, after crossing this plate, is transmitted to the ring sectors. This thus optimizes the cooling of the ring sectors. In particular, the implementation of the distribution element makes it possible to use the cooling air more efficiently than a traditional multi-perforated metal sheet, welded to the ring sector, and devoid of the guide portion described more high. Indeed, with such a multi-perforated sheet and despite the welding, the cooling air, due to other leaks, will not pass entirely through the sheet. A significant part of the cooling potential of the ring sectors is therefore lost when the guide portion is omitted. The implementation of the distribution element thus makes it possible to optimize the amount of cooling air actually used for cooling the ring by limiting leaks.
    In addition, when such a multi-perforated metal sheet is welded to ring sectors of CMC material, the seal at the weld can be affected during operation due to the differences in degree of expansion between the metal sheet. and the ring area. The expansion differences can even, in certain cases, lead to a rupture of the weld leading to a separation between the metal sheet and the ring sector. Thus, by fixing the element for distributing the cooling air to the ring support structure, it is advantageous to overcome these problems which can be encountered with multi-perforated sheet.
    Finally, the inventors have determined that it is advantageous to obtain at the level of the ring sectors a thermal gradient as radial as possible, and therefore to limit, even to eliminate, the axial and tangential thermal gradient. The implementation of the distribution element described above which is provided with a multi-perforated plate is useful concerning this aspect. In fact, the cooling air is accelerated when it passes through the multi-perforated plate and, therefore, the heat exchange with the ring sector located opposite the plate is optimized. This makes it possible to limit the axial and tangential thermal gradients and therefore to limit the appearance of unfavorable mechanical stresses in the ring sectors.
    In one embodiment, the body of the distribution element extends along a circumferential direction of the turbine ring and the multi-perforated plate opens out between the first and second hooking lugs of the sector. ring.
    In one embodiment, the distribution element comprises at least one holding element extending along the radial direction of the turbine ring and coming to bear against the ring sector so as to maintain the latter in position in the radial direction.
    Such a characteristic is advantageous because it makes it possible to take advantage of the presence of the distribution element in order to achieve not only effective cooling of the turbine ring but also to improve the holding in position of the latter during operation.
    In one embodiment, the distribution element is fixed to the ring support structure by at least one insert cooperating with an orifice defined by the guide portion of the cooling air and extending along the axial direction and / or by at least one insert cooperating with a housing defined by the body of the distribution element and extending along the radial direction.
    The invention can in particular be applied to three advantageous examples of turbine ring assemblies which will now be described.
    First example of a turbine ring assembly
    This first example of a turbine ring assembly is such that it comprises, for each ring sector, at least three pins to radially maintain the ring sector in position, at least two of the pins cooperating with one first or second hooking tabs of the ring sector and the corresponding first or second radial tab of the ring support structure, and at least one of the pins cooperating with the other hooking tab of the ring sector and the corresponding radial tab of the ring support structure, the first radial tab comprising a first annular radial portion integral with the ring support structure and a second removable annular radial portion extending radially towards the center of the turbine ring on a part larger than said first annular radial portion, the part extending beyond the first annular radial portion comprising first orifices for receiving one of said pio ns.
    The removable nature of the second annular radial portion relative to the first annular radial portion secured to the ring support structure allows to have axial access to the cavity of the turbine ring. This simplifies the mounting of the ring sectors.
    The first example of a turbine ring assembly advantageously makes it possible to maintain each ring sector in a deterministic manner, that is to say to control its position and prevent it from starting to vibrate. This ring assembly makes it possible to improve the seal between the non-vein sector and the vein sector, to simplify the manipulations by reducing their number for the assembly of the ring assembly, and to allow the ring to deform under the effects of temperature and pressure, especially independently of the metallic parts at the interface.
    According to a first embodiment of this first example, the second removable annular radial portion comprises an annular flange comprising a first portion bearing against the first hooking lug, a second portion removably fixed to the first annular radial portion and a third portion positioned between the first and second portions and comprising the first receiving orifices of one of said pins, the third portion and the first portion of the annular flange extending beyond the first annular radial portion.
    Since the first portion and the third portion of the first annular flange extend beyond the first annular radial portion of the first radial tab, the space remaining free when the flange is removed allows axial insertion of the sectors of ring in the ring support structure.
    According to a second embodiment of this first example, the annular flange is in one piece.
    The fact of having an annular flange in one piece, that is to say describing the entirety of a ring over 360 °, makes it possible, in relation to a segmented annular flange, to limit the passage of the air flow between the non-vein sector and the vein sector, insofar as all inter-sector leaks are eliminated, and therefore optimize sealing.
    According to a third embodiment of the first example of a turbine ring assembly, the first and second attachment tabs of each ring sector each include a first end secured to the external face of the annular base, a second end free, at least one lug receiving ear, each ear projecting from the second end of one of the first or second hooking lugs in the radial direction of the turbine ring, each receiving ear comprising a hole for receiving a pawn.
    The ears made projecting radially from the free ends of the first and second hooking lugs make it possible to offset the holding zone of the hooking lugs relative to the support zones comprised between the two ends of the hooking lugs and intended to produce a tight contact, on the one hand, with the first portion of the annular flange, and, on the other hand, with the second radial tab of the ring support structure. In addition, separating the reception area of the pins from the support zones makes it possible to optimize the seal by reducing the discontinuities of the support zones.
    According to a fourth embodiment of this first example, the second removable annular radial portion comprises, for each ring sector, at least a second and a third orifice each receiving an added element, the added element received in the second through orifice the first annular radial portion and the added element received in the third orifice being housed in an orifice defined by the guide portion of the element for distributing the cooling air so as to ensure the fixing of said distributing element to the ring support structure.
    According to a fifth embodiment of the first example of a turbine ring assembly, the second radial tab of the ring support structure comprises an annular flange having a first portion bearing against the second hooking tab, a second portion thinned with respect to the first portion and a third portion positioned between the first and the second portions and comprising orifices for receiving a pin.
    The reduction in the thickness of the second portion of the downstream annular flange makes it possible to provide flexibility to this flange and thus not to overly constrain the ring sectors.
    It is also possible to carry out an axial prestressing of the annular flange of the second radial tab by making an interference of a few tenths of a millimeter. This allows the differences in expansion between the metallic elements and the CMC ring sectors to be taken up when the latter are used.
    According to a sixth embodiment of the first example of a turbine ring assembly, each distribution element comprises at least two perforated blocks each extending in the axial direction and offset along a circumferential direction of the ring of turbine, said blocks being positioned radially outwards with respect to the first and second hooking lugs of the ring sector, the openings of these blocks each receiving a pin extending along the radial direction and making it possible to maintain in position the first and second hooking lugs of the ring sector in the radial direction.
    Such a characteristic is advantageous because it makes it possible to take advantage of the presence of the distribution element in order to achieve not only effective cooling of the turbine ring but also to improve the holding in position of the latter during operation.
    According to a seventh embodiment of the first example of a turbine ring assembly, each ring sector comprises rectilinear bearing surfaces present on the faces of the first and second hooking lugs in contact respectively with the annular flange and the annular flange.
    The rectilinear supports make it possible to have controlled sealing zones because pressing on a continuous line makes it possible to have no leaks. More specifically, having supports on radial planes makes it possible to overcome the effects of de-cambering in the turbine ring.
    Furthermore, the rings in operation tilt around a normal to the plane comprising the axial direction and the radial direction of the turbine ring. A curvilinear support would generate contact between the ring and the metal ring support structure at one or two points. Conversely, a rectilinear support allows support on a line.
    In a variant, for each ring sector, the faces of the annular flange and of the annular flange in contact with the first and second attachment tabs comprise rectilinear bearing surfaces. 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. The seal and the groove may be present on the first and second attachment tabs of each ring sector or, alternatively, on the annular flange and on the annular flange.
    According to an eighth embodiment of the first example of a turbine ring assembly, the first radial tab of the ring support structure may further comprise a second annular flange comprising a first portion and a second portion, the second portion being coupled to the first annular radial portion and to the second portion of the first annular flange, the first portion of the second annular flange being spaced, in the axial direction of the turbine ring, from the first portion of the first annular flange.
    The second annular flange is dedicated to the resumption of the effort of the high pressure distributor, also noted DHP. This annular flange allows this effort to be taken up, on the one hand, by deforming, and, on the other hand, by passing this effort towards the casing line which is more mechanically robust.
    Indeed, leaving a space between the first portion of the second annular flange and the first portion of the first annular flange makes it possible to deflect the force received by the second annular flange, upstream of the first annular flange relative to the direction of the gas flow, and to pass it directly to the central ring of the ring support structure via the second portion of the second annular flange, without impacting the first portion of the first annular flange in abutment against the first latching tab of the ring. The first portion of the first annular flange does not undergo any effort, the turbine ring is thus preserved from this axial effort.
    According to a ninth embodiment of the first example of a turbine ring assembly, the ring assembly may further comprise, for each ring sector, at least one fixing screw passing through the first and second annular flanges and the first annular radial portion, and at least one fixing nut cooperating with said at least one fixing screw for fixing the first and second annular flanges to the first annular radial portion.
    Second free of turbine ring assembly
    This second example of a turbine ring assembly is such that the first and second hooking lugs extend in the radial direction of the turbine ring and each have a first end secured to the external face and a second end free, 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 tab attachment, 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 made in a plate fixing, the fixing plate cooperating with the third and fourth hooking lugs.
    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 effects of temperature and pressure in particular independently of the metallic parts in interface.
    According to a first embodiment of this second example, the fixing plate comprises first and second ends opposite one another in the circumferential direction and respectively in abutment against the third hooking tab and the fourth tab d hooking, 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, the first and second shoulders each extending in the directions axial and radial.
    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.
    According to a second embodiment of this second example, the ring support structure may comprise first and second annular flanges, the first annular flange being upstream of the second annular flange relative to the direction of the air flow intended through the turbine ring assembly, and the first and second hooking lugs of each ring sector being held between the two annular flanges of the ring support structure, the second annular flange having a thinned portion relative to the rest of the second annular flange, the thinned portion being disposed between a portion bearing against the second hooking tab and one end of the second annular flange secured to 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, reducing 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 ring sector.
    According to a third embodiment of this second example, 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 ring of turbine, 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 simplifies the mounting of the ring sectors.
    According to a fourth embodiment of this second example, each ring sector can comprise rectilinear bearing surfaces present on the faces of the first and second hooking lugs in contact respectively with the second annular flange and the first annular flange.
    As mentioned above for the first example, the rectilinear supports make it possible to have controlled sealing zones.
    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 comprise rectilinear bearing surfaces.
    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. The seal and the groove may be present on the first and second attachment tabs of each ring sector or, alternatively, on the second annular flange and on the first annular flange.
    According to a fifth embodiment of this second example, the third attachment tab and the fourth attachment tab can each be cut into two independent portions, each of the third and fourth attachment tabs comprising a first portion coupled to the first hooking tab and a second portion coupled to the second hooking tab.
    The realization of each of the third and fourth lugs in the form of two independent portions respectively coupled to the first and second 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 each other.
    According to a sixth embodiment of this second example, the third and fourth hooking lugs are each coupled to the first and second hooking lugs respectively by a first and a second ends projecting, 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.
    According to a seventh embodiment of this second example, the distribution element comprises a fixing portion located radially outward relative to the multi-perforated plate and integral with the fixing plate.
    Third free of turbine ring assembly
    This third example of a turbine ring assembly is such that each ring sector has, in section along the plane defined by the axial and radial directions, a K shape, the first and second hooking lugs each having a shape of S, the first radial tab comprising a first and a second retaining element on which the inner face rests in the radial direction of the first latching tab of each ring sector, the outer face in the radial direction of the ring turbine of said first hooking lug of each ring sector being in contact with first and second clamping elements integral with the ring support structure, the first and second clamping elements being respectively opposite -vis the first and second holding elements in the radial direction, the second radial tab comprising a third holding element on which the internal face rests in the radial irection of the second fastening tab of each ring sector, the external face in the radial direction of the turbine ring of said second fastening tab of each ring sector being in contact with a third element tightening integral with the ring support structure, the third clamping element being opposite the third holding element in the radial direction.
    The solution proposed in this third example makes it possible to maintain the ring sectors without play at the level of their cold mounting on the ring support structure, the ring sectors being maintained, on the one hand, by the contact between the inner face of the legs of the ring sectors and the holding elements integral with the annular flanges of the ring support structure and, on the other hand, by the contact between the outer face of the legs of the ring sectors and the clamping elements integral with the ring support structure.
    According to a first embodiment of this third example, the first and second holding elements of the first radial tab are present in the vicinity of the circumferential ends of each ring sector while the third holding element of the second radial tab is present in the vicinity of the middle part of each ring sector.
    This ensures balanced maintenance of each ring sector while having a significantly reduced overall bearing surface on the ring sectors, which makes it possible to reduce the mass of the turbine ring assembly and to reduce the areas of application of any constraints on the ring sectors during thermal expansion.
    According to a second embodiment of this third example, the internal face in the radial direction of the turbine ring of the second leg of each ring sector also rests on a fourth holding element integral with the second annular radial leg , the outer face in the radial direction of the turbine ring of said second leg of each ring sector being in contact with a fourth clamping element integral with the ring support structure, the fourth clamping element being in vis-à-vis the fourth retaining element in the radial direction of the turbine ring, and in which the first and second retaining elements secured to the first annular radial lug and the third and fourth retaining elements secured to the second Annular radial lugs are present in the vicinity of the circumferential ends of each ring sector.
    In this case, a balanced maintenance of each ring sector is also ensured while having a significantly reduced overall bearing surface on the ring sectors, which makes it possible to reduce the mass of the turbine ring assembly. and reduce the areas of application of possible stresses on the ring sectors during thermal expansion.
    According to a third embodiment of this third example, the first, second, third and possibly fourth clamping elements are formed respectively by first, second, third and possibly fourth pins integral with the ring support structure. The pins can in particular be screwed or shrunk into the ring support structure to keep them in position.
    According to a fourth embodiment of this third example, the first and second hooking lugs of each ring sector extend in a rectilinear direction while the annular base of each ring sector extends in the circumferential direction of the ring.
    Thus, the ring has rectilinear supports at the level of contact with the ring support structure. This allows for controlled sealing zones.
    According to a fifth embodiment of this third example, the contact zones between the retaining elements and the latching tabs are included in the same rectilinear plane and the contact zones between the latching lugs and the clamping elements are included in the same rectilinear plane.
    This alignment of the contact zones on parallel rectilinear planes makes it possible to maintain sealing lines in the event of the ring tipping.
    According to a sixth embodiment of this third example, the ring assembly further comprises an upstream flange mounted on the first radial tab, the upstream flange comprising a plurality of first and second holding elements distributed uniformly over the face of the flange opposite the first legs of the ring sectors.
    As a variant, the ring assembly comprises an upstream flange mounted on the second radial tab, the upstream flange comprising at least a plurality of third holding elements distributed uniformly on the face of the flange facing the second legs of the ring sectors .
    The use of a flange makes it easier to mount the ring sectors on the ring support structure.
    According to a seventh embodiment of this third example, the second radial tab is elastically deformable. This allows not to exert too great constraints on the ring sectors.
    The present invention also relates to a turbomachine comprising a turbine ring assembly as described above.
    Brief description of the drawings
    Other characteristics and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of nonlimiting examples, with reference to the appended drawings, in which:
    FIG. 1 is a schematic perspective view of an embodiment of a turbine ring assembly according to the first example mentioned above,
    FIG. 2 is a schematic exploded perspective view of the turbine ring assembly of FIG. 1,
    FIG. 3 is a perspective sectional view of the distribution element used in the turbine ring assembly of FIGS. 1 and 2,
    FIG. 4 is a schematic and partial perspective view of a variant of a turbine ring assembly according to the first example mentioned above,
    FIG. 5 is a schematic perspective view of an embodiment of a turbine ring assembly according to the second example mentioned above,
    FIGS. 6 and 7 are schematic exploded perspective views of the turbine ring assembly of FIG. 5,
    FIG. 8 is a schematic and partial perspective view of a turbine ring assembly according to the third example mentioned above,
    FIG. 9 is a sectional view along IX-IX of the turbine ring assembly of FIG. 8,
    FIG. 10 is a partial perspective view of the turbine ring assembly of FIG. 8, and
    FIG. 11 represents the upstream flange used in the turbine ring assembly of FIG. 8.
    Detailed description of embodiments
    Description of a first embodiment of the first example of a turbine ring assembly
    Figure 1 shows a high pressure turbine ring assembly comprising a turbine ring 11 of ceramic matrix composite material (CMC) or metallic material and a metallic ring support structure 13. When the ring 11 is in CMC, the ring support structure 13 is made of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the material constituting the ring sectors. The turbine ring 11 surrounds a set of rotary blades (not shown). The turbine ring 11 is formed of a plurality of ring sectors 110. The arrow D a indicates the axial direction of the turbine ring 11 while the arrow Dr indicates the radial direction of the turbine ring 11 The arrow D c indicates the circumferential direction of the turbine ring 11. For reasons of simplification of presentation, FIG. 1 is a partial view of the turbine ring 11 which is in reality 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 110 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 sector 110 in fact comprises an annular base 112 and radial upstream and downstream hooking lugs 114 and 116. The terms upstream and downstream are used here with reference to the direction of flow of the gas flow in the turbine which takes place along the axial direction D A.
    The annular base 112 comprises, in the radial direction Dr of the ring 11, an internal face 112a and an external face 112b opposite one another. The internal face 112a of the annular base 112 is coated with a layer 113 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 114 and 116 extend in projection, in the direction Dr, from the external face 112b of the annular base 112 at a distance from the upstream and downstream ends 1121 and 1122 of the annular base 112 The upstream and downstream hooking radial lugs 114 and 116 extend over the entire circumferential length of the ring sector 110, that is to say over the entire arc of a circle described by the ring sector 110 .
    As illustrated in FIGS. 1 and 2, the ring support structure 13 which is integral with a turbine casing 130 comprises a central ring 131, extending in the axial direction D A , and having an axis of revolution coincides with the axis of revolution of the turbine ring 11 when they are fixed together. The ring support structure 13 further comprises an upstream annular radial flange 132 and a downstream annular radial flange 136 which extend, in the radial direction D R , from the central ring 31 towards the center of the ring 11 and in the circumferential direction of the ring 11.
    As illustrated in FIG. 2, the downstream annular radial flange 136 comprises a first free end 1361 and a second end 1362 secured to the central crown 131. The downstream annular radial flange 136 comprises a first portion 1363, a second portion 1364, and a third portion 1365 lying between the first portion 1363 and the second portion 1364. The first portion 1363 extends between the first end 1361 and the third portion 1365, and the second portion 1364 extends between the third portion 1365 and the second end 1362. The first portion 1363 of the annular radial flange 136 is in contact with the downstream radial hooking lug 116. The second portion 1364 is thinned relative to the first portion 1363 and the third portion 1365 so as to give a some flexibility to the annular radial flange 136 and thus not to overly constrain the turbine ring 11.
    As illustrated in Figures 1 and 2, the ring support structure 13 further comprises first and second upstream flanges 133 and 134 each having, in the example illustrated, an annular shape. The two upstream flanges 133 and 134 are fixed together on the upstream annular radial flange 132. Alternatively, the first and second upstream flanges 133 and 134 could be segmented into a plurality of ring sections.
    The first upstream flange 133 comprises a first free end 1331 and a second end 1332 in contact with the central crown 131. The first upstream flange 133 further comprises a first portion 1333 extending from the first end 1331, a second portion 1334 s extending from the second end 1332, and a third portion 1335 extending between the first portion 1333 and the second portion 1334.
    The second upstream flange 134 comprises a first free end 1341 and a second end 1342 in contact with the central crown 131, as well as a first portion 1343 and a second portion 1344, the first portion 1343 extending between the first end
    1341 and the second portion 1344, and the second portion 1344 extending between the first portion 1343 and the second end 1342.
    The first portion 1333 of the first upstream flange 133 is supported on the upstream radial latching lug 114 of the ring sector 110. The first and second upstream flanges 133 and 134 are shaped to have the first portions 1333 and 1343 distant from it. one from the other and the second portions 1334 and 1344 in contact, the two flanges 133 and 134 being detachably fixed on the upstream annular radial flange 132 by means of screws 160 and nuts 161 for fixing, the screws 160 passing through holes 13340, 13440 and 1320 provided respectively in the second portions 1334 and 1344 of the two upstream flanges 133 and 134 as well as in the upstream annular radial flange 132. The nuts 161 are in turn secured to the support structure ring 13, being for example fixed by crimping thereto.
    The second upstream flange 134 is dedicated to the resumption of the effort of the high pressure distributor (DHH), on the one hand, by deforming, and, on the other hand, by passing this effort towards the casing line which is more mechanically robust, i.e. towards the line of the ring support structure 13.
    In the axial direction D A , the downstream annular radial flange 136 of the ring support structure 13 is separated from the first upstream flange 133 by a distance corresponding to the spacing of the upstream and downstream hooking radial lugs 114 and 116 so as to maintain the latter between the downstream annular radial flange 136 and the first upstream flange 133. It is possible to carry out an axial prestressing of the flange 136. This makes it possible to take up the differences in expansion between the metallic elements and the sectors of CMC ring when these are used.
    To further maintain in position the ring sectors 110, and therefore the turbine ring 11, with the ring support structure 13, the ring assembly comprises, in the example illustrated, two first pins 119 cooperating with the upstream hooking lug 114 and the first upstream flange 133, and two second pins 120 cooperating with the downstream hooking lug 116 and the downstream annular radial flange 136.
    For each corresponding ring sector 110, the third portion 1335 of the first upstream flange 133 comprises two orifices 13350 for receiving the first two pins 119, and the third portion 1365 of the annular radial flange 136 comprises two orifices 13650 configured to receive the two second pawns 120.
    For each ring sector 110, each of the upstream and downstream hooking radial lugs 114 and 116 comprises a first end, 1141 and 1161, integral with the external face 112b of the annular base 112 and a second end, 1142 and 1162, free. The second end 1142 of the upstream radial lug 114 comprises two first ears 117 each comprising an orifice 1170 configured to receive a first pin 119. Similarly, the second end 1162 of the downstream radial lug 116 comprises two second ears 118 each comprising an orifice 1180 configured to receive a second pin 120. The first and second ears 117 and 118 extend projecting in the radial direction Dr from the turbine ring 11 respectively from the second end 1142 of the tab upstream radial latching 114 and the second end 1162 of the downstream radial latching lug 116.
    For each ring sector 110, the first two ears 117 are positioned at two different angular positions relative to the axis of revolution of the turbine ring 11. Likewise, for each ring sector 110, the two seconds ears 118 are positioned at two different angular positions relative to the axis of revolution of the turbine ring 11.
    Each ring sector 110 further comprises rectilinear bearing surfaces 1110 mounted on the faces of the upstream and downstream hooking radial lugs 114 and 116 in contact respectively with the first upstream annular flange 133 and the downstream annular radial flange 136, that is to say on the upstream face 114a of the upstream radial hooking tab 114 and on the downstream face 116b of the downstream radial hooking tab 116. In a variant, the rectilinear supports could be mounted on the first upstream annular flange 133 and on the downstream annular radial flange 136.
    The 1110 rectilinear supports allow controlled sealing zones. Indeed, the bearing surfaces 1110 between the upstream radial hooking lug 114 and the first upstream annular flange
    133, on the one hand, and between the downstream radial hooking lug 116 and the downstream annular radial flange 136 are included in the same rectilinear plane.
    More precisely, having supports on radial planes makes it possible to overcome the effects of de-cambering in the turbine ring 11. Furthermore, the rings in operation tilt around a normal to the plane (D A , Dr). A curvilinear support would generate contact between the ring 11 and the ring support structure 13 at one or two points. Conversely, a rectilinear support allows support on a line.
    As mentioned above, the ring assembly further comprises, for each ring sector 110, a cooling air distribution element 150. This distribution element 150 constitutes a diffuser allowing the impact of a cooling flow F R on the external face 112b of the ring sector 110. The element 150 is present in a first cavity 151 delimited between the turbine ring 11 and the ring support structure 13. The element of distribution 150 comprises a hollow body 153 which defines an internal volume V for distributing the cooling air as well as a multi-perforated plate 195 comprising a plurality of through perforations 197 which bring the internal volume V into communication with a second cavity 156 delimited between the turbine ring 11 and the plate 195. The multi-perforated plate 195 is located opposite (opposite) the external face 112b of the ring sector 110. The multi-perforated plate 195 present in exe mple illustrated an elongated shape along the circumferential direction D c of the turbine ring 11. The multi-perforated plate 195 also opens out between the first 114 and second 116 hooking lugs of the ring sector 110. No element third is present between the multi-perforated plate 195 and the external face 112b of the ring sector 110 so as not to slow down or disturb the flow of cooling air passing through the plate 195 and impacting the sector of ring 110. The multi-perforated plate 195 delimits the internal volume V and is located on the side of the ring sector 110 (radially inwards). The element 150 further comprises a portion for guiding the cooling air 157 which extends from the body 153 both in the radial direction Dr and in the axial direction D A. The guide portion 157 is positioned radially outward relative to the multi-perforated plate 195. This guide portion 157 defines an internal channel which is in communication with the cooling air supply orifices 192 and 190 respectively formed in the first 133 and second 134 upstream flanges. The flow of cooling air Fr taken upstream in the turbine is intended to pass through the orifices 190 and 192 with a view to being conveyed to the ring sector 110. The guide portion 157 defines an internal channel 194 that the cooling air flow F R is intended to pass through in order to be transferred to the internal volume V and to be distributed to the ring sector 110 following its passage through the multi-perforated plate 195. The internal channel 194 has an orifice inlet 191 which is located opposite (opposite) the feed port 192 and communicating with the latter. It may be advantageous for the inlet orifice 191 to be an extension of the feed orifice 192, the guide portion 157 in this case being in contact with or very little spaced from the first upstream flange 133. The inner channel 194 also opens into the internal volume V through the outlet orifice 193. The outlet orifice 193 opens, in the example illustrated, opposite the multi-perforated plate 195. The inner channel 194 of the portion of guide 157 has the role of channeling the cooling air Fr arriving through the orifice 192 in order to transfer it to the interior volume V then to the ring sector 110 and thus minimize the losses or leaks of this cooling air .
    The guide portion 157 defines a housing 158 passing through, in this case, but which could alternatively be blind. A fixing screw 163 is intended to cooperate with this housing 158 in order to secure the element 150 to the ring support structure. As can be seen in particular in FIG. 1, the distribution element 150 further comprises an additional holding portion 159 distinct from the guide portion 157 (the portion 159 does not necessarily define an internal channel for conveying the fluid cooling). The portions 157 and 159 of the same distribution element 150 are offset along the circumferential direction D c . The holding portion 159 also defines a housing 154 cooperating with a fixing screw 163 in order to allow the element 150 to be fixed to the ring support structure 13. In the example illustrated, the fixing screws 163 s 'extend along the axial direction D A of the turbine ring and pass through the first 133 and second 134 upstream flanges when they are housed in the housings 154 and 158.
    A method of producing a set of turbine rings corresponding to that shown in FIG. 1 will now be described.
    When the ring sectors 110 are made of CMC material, the latter are produced by forming a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix.
    For the production of the fiber preform, it is possible to use ceramic fiber threads, for example SiC fiber threads such as those sold by the Japanese company Nippon Carbon under the name Hi-Nicalon S, or carbon fiber threads.
    The fibrous preform is advantageously produced by three-dimensional weaving, or multi-layer weaving with the arrangement of unbinding zones making it possible to separate the parts of preforms corresponding to the legs 114 and 116 from the sectors 110.
    The weaving can be of the interlock type, as illustrated. Other three-dimensional or multi-layer weaving weaves can be used, for example multi-canvas or multi-satin weaves. Reference may be made to document WO 2006/136755.
    After weaving, the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, densification being able to be carried out in particular by chemical gas infiltration (CVI) which is well known in oneself. In a variant, the textile preform can be hardened a little by CVI so that it is rigid enough to be handled, before making liquid silicon rise by capillarity in the textile to make the densification.
    A detailed example of manufacturing ring sectors in CMC is described in particular in document US 2012/0027572.
    The manufacture of the ring sectors made of CMC material which has just been described is valid for the first, second or third example of a ring assembly mentioned above when this assembly implements a ring made of CMC material.
    When the ring sectors 110 are made of metallic material, the latter can for example be formed by one of the following materials: AMI alloy, C263 alloy or M509 alloy.
    The ring support structure 13 is made of a metallic material such as a Waspaloy® or Inconel 718 or even C263 alloy.
    The production of the turbine ring assembly continues with the mounting of the ring sectors 110 on the ring support structure 13. This mounting can be carried out ring sector by ring sector in the following manner .
    First place the first pins 119 in the holes 13350 provided in the third part 1335 of the first upstream flange 133, and mount the ring sector 110 on the first upstream flange 133 by engaging the first pins 119 in the holes 1170 of the first ears of the upstream hooking lug 114 until the first portion 1333 of the first upstream flange 133 is in abutment against the bearing surface 1110 of the upstream face 114a of the upstream hooking lug 114 of the sector ring 110.
    The second upstream flange 134 is then fixed to the first upstream flange 133 and to the element 150 present between the lugs 114 and 116 by positioning the fixing screws 163 through the orifices 13440, 13340, 154 and 158.
    Then the two second pins 120 are inserted into the two holes 13650 provided in the third part 1365 of the annular radial flange 136 of the ring support structure 13.
    The assembly comprising the ring sector 110, the flanges 133 and 134 and the element 150 previously obtained 1 is then mounted on the ring support structure 13 by inserting each second pin 120 in each of the orifices 1180 of the second ears 118 of the downstream attachment lugs 116 of the ring sector 110. During this mounting, the second portion 1334 of the first upstream flange 133 is pressed against the upstream annular radial flange 132.
    The assembly of the ring sector is then finalized by inserting the fixing screws 160 in the openings 13440, 13340 still free and 1320, coaxial, and each screw is tightened in the nuts 161 secured to the ring support structure .
    The embodiment which has just been described comprises, for each ring sector 110, two first pins 119 and two second pins 120. It is not, however, departing from the scope of the invention if for each ring sector, two first pawns 119 and a single second pawn 120 are used or a single first pawn 119 and two second pawns 120.
    Description of a second embodiment of the first example of a turbine ring assembly
    Figure 4 illustrates a second embodiment of the first turbine ring assembly. This second embodiment differs from the first embodiment previously described only in that each distribution element 1500 further comprises two perforated blocks 1510 and 1520 which each extend in the axial direction D A and which are offset along of the circumferential direction D c . The body of the distribution element has, in this example, two radial extensions 1514 and 1524 connected respectively to block 1510 and to block 1520. The first block 1510 has axial ends 1516a and 1516b which block the latching lugs 114 and 116 in a radial outward movement. The ends 1516a and 1516b of the first block each have a through aperture in which is received a pin 1512 extending radially and making it possible to maintain the hooking lugs 114 and 116 in the radial position. Similarly, the ends 1526a and 1526b each receive a pin 1522 having the same function.
    In a variant not illustrated, one could also use a distribution element 150 having the same structure as that described in FIGS. 1 to 3 (not including the blocks 1510 and 1520) and pins extending in the radial direction between the crown central 131 and the lugs 114 and 116 in order to maintain these lugs in the radial position. According to this variant, the ends of these pins are forcibly inserted into orifices made in the central ring 131 in order to maintain them. As a variant, these pins could be mounted with a play in the orifices of the central crown 131 and then be welded thereafter.
    Description of an embodiment of the second example of a turbine ring assembly
    In this second example of a turbine ring assembly, certain elements are common to the first example described above. The description of these common elements is not repeated for the sake of brevity. These common elements are referenced in this second example by the same reference with the exception that they begin with a "2" instead of a "1". Thus, for example, the screws referenced 160 in the first example will be referenced 260 in the second example.
    As illustrated in FIGS. 5 to 7, the ring sector 210 comprises, in this second example, two axial latching lugs 217 and 218 extending between the upstream and downstream latching lugs 214 and 216.
    Each of the upstream and downstream hooking radial lugs 214 and 216 comprises a first end, 2141 and 2161, integral with the external face 212b of the annular base 212 and a second end, 2142 and 2162, free. The axial latching lugs 217 and 218 extend more precisely, in the axial direction D A , between the second end 2142 of the upstream radial latching lug 214 and the second end 2162 of the downstream latching radial lug 216 .
    Each of the axial hooking lugs 217 and 218 comprises an upstream end, respectively 2171 and 2181, and a downstream end, respectively 2172 and 2182, the two ends, 2171 and 2172 on the one hand and 2181 and 2182 on the other hand, an axial hooking lug 217 or 218 being separated by a central part, 2170 and 2180. The upstream and downstream ends, 2171 and 2172 on the one hand and 2181 and 2182 on the other hand, of each hooking lug axial 217 and 218 extend in projection, in the radial direction Dr, from the second end 2142, 2162 of the radial lug 214, 216 to which they are coupled, so as to have a central part 2170 and 2180 of axial latching lug 217 and 218 raised relative to the second ends 2142 and 2162 of the upstream and downstream latching radial lugs 214 and 216.
    In the embodiment illustrated in FIGS. 5 to 7, each of the axial latching lugs 217 and 218 is cut in half, forming an upstream part, respectively 2173 and 2183, and a downstream part, respectively 2174 and 2184.
    As illustrated in FIGS. 5 to 7, for each ring sector 210, the turbine ring assembly comprises a screw 219 and a fixing plate 220. The fixing plate 220 comprises a first and a second end 2201 and 2202 respectively in abutment against the first and second axial latching lugs 217 and 218.
    The first and second ends 2201 and 2202 of the fixing plate 220 each comprise a cut forming a first stop, respectively 2201a and 2202a, in rotation, that is to say a stop in a direction orthogonal to the cutting plane comprising the axial direction Da and the radial direction Dr, and a second radial stop, respectively 2201b and 2202b, more particularly forming a stop in the radial direction Dr in a direction going towards the center of the ring 1. The cutting of each end 2201 and 2202 thus cooperates with a separate axial latching lug 217 or 218 to come to bear on both sides at the same time of the same edge of the axial latching lug 217 or 218.
    The fixing plate 220 thus provides radial retention of the vein by exerting a radial force using the two radial stops 2201b and 2202b bearing on the internal face 217a and 218a, in the radial direction Dr, of each of the two legs axial attachment 217 and 218. The fixing plate 220 also blocks the ring sector 210, and therefore the ring 21, from any rotation about the axis of the turbine, due to the support of the two legs axial hooking 217 and 218 on two opposite sides of the fixing plate 220.
    The fixing plate 220 further comprises an orifice 221 provided with a thread cooperating with a thread of the screw 219 for fixing the fixing plate 220 to the screw 219. The screw 219 comprises a screw head 2190 cooperating with an orifice 2234 produced in the central crown 231 of the support structure of the ring 23 through which the screw 219 is inserted before being screwed to the fixing plate 220.
    The radial connection of the ring sector 210 with the ring support structure 23 is carried out using the screw 219, the head 2190 of which rests on the central ring 231 of the ring support structure 23, and of the fixing plate 220 screwed to the screw 219 and the ends 2201 and 2202 of which bear against the axial latching lugs 217 and 218 of the ring sector 210.
    To radially block the ring sector 210 in a direction opposite to that of the forces exerted by the second stops 2201b and 2202b, the turbine ring assembly comprises, in this embodiment, four pins 225 extending in the radial direction Dr between the central ring 231 of the ring support structure 23 and the axial lugs 217 and 218 of the ring 21. More specifically, the pins 225 include first ends 2251 inserted by force into holes 225a produced in the central crown 231 around the orifice 2234 receiving the fixing screw 219. In a variant, the pins could also be hooped in the holes 225a 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 225 comprising in this case a thread cooperating with a thread formed in the orifices 225a. The pins 225 could also be mounted with a play in the holes 225a and be welded thereafter.
    The four pins 225 are distributed symmetrically with respect to the screw 219 so as to have two pins 225 extending between the first axial latching lug 217 and the ring support structure 23 and two pins 225 extending between the second axial latching lug 218 and the ring support structure 23. The pins 225 are dimensioned and installed so that a second end 2252 of each pin 225, opposite the first end 2251, comes to bear on the axial lug associated hooking 217 or 218, more particularly on the corresponding external face 217b or 218b, thus blocking radially, with the aid of the fixing plate 220, the axial hooking lugs 217 and 218, and therefore the ring 21 , in both directions of the radial direction Dr of the ring 21.
    The ring assembly further comprises, for each ring sector 210, a cooling air distribution element 250 having a function similar to the distribution element 150 described above. The element 250 here comprises a plurality of cooling air guide portions 257 which extend from the body 253 both in the radial direction Dr and in the axial direction D A. These guide portions 257 each define an inner channel which is in communication with the cooling air supply orifices 292 and 290 respectively formed in the first 233 and second 234 upstream flanges. The guide portions 257 define an internal channel which the cooling air flow is intended to pass through in order to be transferred to the internal volume and to be distributed to the ring sector 210 following its passage through the multi-perforated plate 295 The internal channel has an inlet orifice 291 which is situated opposite (opposite) the communicating orifice 292 and communicating with the latter. The internal channel also opens into the internal volume through an outlet orifice defined by the relief 257a. This outlet orifice opens out, in the example illustrated, opposite the multi-perforated plate 295. The guide portions 257 are fixed to the body by insertion of the reliefs 257a in the orifices 253a defined by the body 253. According to a variant, the guide portions 257 could be formed monolithically (in one piece) with the body 253.
    The distribution element 250 is here welded to the fixing plate 220 at the level of a fixing portion 253b situated radially outwards relative to the multi-perforated plate 295. The plate 295 also has an orifice 295a intended to cooperate with the fixing screw 219. In this second example, the distribution element 250 is fixed to the ring support structure 23 by an added element, constituted by the screw 219, which cooperates with a housing defined by the body 253 and the fixing plate 295 and which extends in the radial direction Dr.
    An example of how to mount ring sectors 210 on the ring support structure 23 will now be described.
    For this, the ring sectors 210 are assembled together on an annular tool of the “spider” type comprising, for example, suction cups configured to each maintain a ring sector 210. Then the fixing plates 220 welded to an element of 250 associated distribution are inserted in each of the free spaces extending between a first and a second axial latching lugs 217 and 218 of a ring sector 210. Until it is screwed to the support structure ring 23, each fixing plate 220 is held in position in abutment against the axial latching lugs 217 and 218 of the associated ring sector using a holding lug mounted on the annular tool. The annular tool comprises a retaining tab for each fixing plate 220, that is to say for each ring sector 210. Each retaining tab is inserted between the two axial latching tabs 217 and 218, d on the one hand, and between the second end 2162 of the downstream radial hooking lug 216 and the fixing plate 220 on the other hand. Each retaining lug is then adjusted to keep the associated fixing plate 220 in abutment against the axial latching lugs 217 and 218. Each fixing screw 219 is then inserted into the orifice 2234 associated with the central crown of the structure of ring support 23 and screwed into the tapped hole 221 of the associated fixing plate 220 and into the orifice 295a until the screw head 2190 is in abutment against the central crown 231. The pins 225 are also introduced so that the ring sector is held radially. The first and second flanges 233 and 234 are then fixed to the upstream annular radial flange 232 using the screws 260 to hold the turbine ring 1 axially, then the annular tool is removed.
    Description of an embodiment of the third example of a turbine ring assembly
    FIG. 8 shows a high pressure turbine ring assembly according to the third example comprising a turbine ring made of CMC material or of metallic material and a metal ring support structure 33. The turbine ring is formed of a plurality of ring sectors 310.
    Each ring sector 310 has, as illustrated in FIGS. 8 to 10 and along a plane defined by the axial directions DA and radial DR, a substantially K-shaped section comprising an annular base 312, upstream and downstream legs 314, 316 substantially S-shaped extend, in the direction DR, from the outer face of the annular base 312.
    The ring support structure 33 which is integral with a turbine casing 330 comprises an annular upstream radial flange 33 'and an annular downstream radial flange 36' which extend in the radial direction DR towards the center of the ring and in the circumferential direction of the ring. In the example described here, the ring support structure 33 further comprises an upstream flange 33 'having a ring shape, the upstream flange 33' being mounted on the upstream annular radial flange 32 '. For the sake of clarity, FIG. 8 shows only part of the turbine ring, of the ring support structure 33 and of the flange 33 ′, these elements actually extending in a complete annular shape, a a plurality of adjacent ring sectors 310 being disposed between the flanges 33 'and 36' of the ring support structure.
    The upstream and downstream tabs 314, 316 of each ring sector 310 extend in a rectilinear direction (in the axial direction DA) while the annular base 312 of each sector extends in the circumferential direction DC of the ring turbine.
    In the example described here, the internal face 314b in the radial direction DR of the turbine ring of the first tab 314 of each ring sector 310 rests on a first and second retaining elements integral with the upstream annular radial flange 32 ', corresponding here to first and second lugs 330' and 331 'projecting from the face 33'a of the upstream flange 33' (Figures 10 and 11) opposite the upstream tab 314 of the ring sectors 310.
    The first and second pins 330 'and 331' are distributed regularly over the flange 33 'at positions determined so as to be present in the vicinity of the circumferential ends 310a and 310b of each ring sector 310. The upstream flange 33' being mounted on the upstream annular radial flange 32 ', the lugs 330' and 331 'are integral with the upstream annular radial flange 32'.
    In addition, the external face 314a in the radial direction DR of the turbine ring of the upstream tab 314 of each ring sector 310 is in contact with a first and a second clamping elements integral with the support structure. ring 33, here first and second pins 40 'and 4Γ. The first and second pins 40 'and 41' are placed respectively opposite the first and second pins 330 'and 331' in the radial direction DR of the turbine ring. The pins 40 'and 41' are held respectively in orifices provided in the flange 32 '.
    The pins 40 'and 41' can be hooped in the orifices of the flange 32 'by known metal assemblies such as adjustments H6-P6 or other force assemblies, or even by contracting the pins by contacting with a cold fluid (liquid nitrogen) which allow these elements to be kept cold or maintained in said orifices by screwing. The pins 40 'and 41' in this case comprise a thread cooperating with a thread formed in the orifices of the flange 32 '.
    The internal face 316b in the radial direction DR of the turbine ring of the second tab 316 of each ring sector 310 rests on a third retaining element secured to the annular radial flange 36 ', corresponding here to a third lug 360 '(Figure 10) projecting from the face 36'a of the flange 36' opposite the downstream lug 316 of the ring sectors 310. The third lugs 360 'are distributed uniformly on the face 36'a of the radial flange annular 36 'at a position determined so as to be present in the vicinity of the middle part of each ring sector 310.
    In addition, the external face 316a in the radial direction DR of the turbine ring of the downstream tab 316 of each ring sector 310 is in contact with a third clamping element integral with the ring support structure 33, here a third 50 'pawn. The third pin 50 'is placed respectively opposite the third lug 360' in the radial direction DR of the turbine ring. The pin 50 'is held in an orifice 361' formed in a projection 362 'present on the face 36'a of the annular downstream radial flange 36' opposite the tabs 316 of the ring sectors 310.
    The pin 50 'can be shrunk into the orifice 361' by known metal assemblies as described above which allow this element to be kept cold or held in said orifice by screwing, the pins 50 'in this case comprising a thread cooperating with a thread formed in the orifice 36Γ.
    In the example described here, each ring sector 310 is held in the ring support structure at three holding points, a first holding point being formed by the lug 330 'and the pin 40' in opposite, a second point being formed by the lug 331 'and the pin 41' opposite and a third point being formed by the lug 360 'and the pin 50' facing screw as shown in Figure 10 in particular.
    The clamping elements, here the pins 40 ', 41' and 50 'can for example be made of metallic material.
    Thanks to the use of clamping elements, such as pins 40 ', 41' and 50 ', it is possible to adjust the cold supports between the ring sectors and the ring support structure. By "cold" is meant in the present invention, the temperature at which the ring assembly is found when the turbine is not operating, that is to say at an ambient temperature which can be for example of about 25 ° C. By "hot" here is meant the temperatures to which the ring assembly is subjected during operation of the turbine, these temperatures possibly for example being between 600 ° C. and 1500 ° C., for example between 600 ° C. and 900 ° C.
    In the example which has just been described, two holding elements and two clamping elements are present on the side of the upstream annular radial flange while a holding element and a clamping element are present on the side of the radial flange annular downstream. The invention also applies to a turbine ring assembly in which two holding elements and two clamping elements are present on the side of the annular downstream radial flange while a holding element and a clamping element are present on the side of the annular upstream radial flange.
    Thanks to the rectilinear shape of the legs of each ring sector, the supports or contact zones between the holding elements (for example pins) and the legs are included in the same rectilinear plane. Similarly, the supports or contact zones between the legs and the clamping elements (for example pins) are included in the same rectilinear plane. The rings in operation tilt around a normal to the plane (DA; DR). A curvilinear support would generate a ring sector / ring support structure contact on one or two points while a straight support is advantageous because it allows support on a line.
    FIGS. 8 and 9 further illustrate the fact that the ring assembly comprises a plurality of elements for distributing the cooling air 60 intended to allow the impact of a cooling flow on the internal face of the turbine ring. Each element 60 comprises a hollow body 61 delimiting an internal volume V. First and second legs 62 and 63 extend on each side of the body 61, the first leg 62 being held between the upstream annular radial flange 32 'of the structure of ring support 33 and the lug 314 of the ring sectors 310 while the second lug 63 is held between the annular downstream radial flange 36 'of the ring support structure 33 and the lug 316 of the ring sectors 310 Each element 60 is also held in position inside the ring support structure 33 by a pin 65 secured to a cap 66 fixed to the ring structure 33. The pin 65 exerts a support on a pin 65a passing through the body 61 in order to keep the element 60 in position.
    The distribution element 60 is also held in position by support of the legs 62 and 63 on the legs 314 and 316. The pin 65a extends in the radial direction DR and further comes to bear on the ring sector 310 of so as to keep the latter in position in the radial direction.
    The internal volume V is closed in its lower part by a plate 64 comprising a plurality of perforations 640. A flow of cooling air FR taken upstream in the turbine is guided as far as in the volume V by a guide portion 601 (figure 9). The flow FR then passes through the perforations 640 of the plate 64 in order to cool the internal face of the ring sectors 310 forming the turbine ring.
    An example of how to mount ring sectors 310 on the ring support structure 33 will now be described.
    The assembly consisting of a ring sector 310 and the element 60 is approached to the ring support structure 33 so as to place the internal face 316b of the tab 316 on the lug 360 '. The pin 50 'is then introduced so as to maintain the tab 316 on the flange 36'. The pins 40 'and 41' are positioned in the annular flange 32 '. The upstream flange 33 'is then mounted on the upstream annular radial flange 32'. Due to the significant aerodynamic forces, the distributor will push the flange 33 'and "press" it on the upstream flange 32'. Once the flange 33 ′ mounted, the internal face 314b of the lugs 314 of each sector 310 rests on the lugs 330 ′ and 33Γ. The pins 40 'and 41' will then allow the ring sector to be fixed. The assembly is then finalized by positioning the pins 65a and 65 as well as the cap 66.
    权利要求:
    Claims (7)
    [1" id="c-fr-0001]
    1. A turbine ring assembly comprising a plurality of ring sectors (210) of ceramic matrix composite material or of metallic material forming a turbine ring and a ring support structure (23), each sector of ring having, according to a cutting plane defined by an axial direction (D A ) and a radial direction (Dr) of the turbine ring, an annular base portion (212) with, in the radial direction of the ring of turbine, an internal face defining the internal face of the turbine ring and an external face from which extend a first (214) and a second (216) lugs, the ring support structure comprising first and second radial tabs between which the first and second hooking tabs of each ring sector are held, as well as a plurality of cooling air supply ports (290; 292) (F R ) , the turbine ring assembly further comprising , for each ring sector, a cooling air distribution element (250) fixed to the ring support structure and positioned in a first cavity (251) delimited between the turbine ring and the structure ring support, said distribution element comprising a body (253) defining an internal volume (V) for distributing the cooling air and comprising a multi-perforated plate (295) communicating with the internal volume and opening into a second cavity (258) delimited between the turbine ring and the multi-perforated plate, the distribution element further comprising at least one guide portion (257) of the cooling air extending from the body and defining an internal channel in communication with one of the cooling air supply orifices and opening into the internal volume for distributing the cooling air, the turbine ring assembly being such that the first ( 214) and second (216) lugs extend in the radial direction of the turbine ring and each have a first end (2141;
    2161) integral with the external face and a second free end (2142;
    2162), each ring sector comprising a third and a fourth hooking lugs (217; 218) each extending in the axial direction of the turbine ring between the second end (2142) of the first lug hooking (214) and the second end (2162) of the second hooking lug (216), each ring sector (210) being fixed to the ring support structure by a fixing screw (219) comprising a screw head (2190) bearing against the ring support structure (23) and a thread cooperating with a thread produced in a fixing plate (220), the fixing plate (220) cooperating with the third and fourth legs attachment (217; 218), and the turbine ring assembly being such that the distribution element (250) comprises a fixing portion (253b) located radially outward relative to the multi-plate perforated (295) and integral with the fixing plate (220).
    [2" id="c-fr-0002]
    2. Assembly according to claim 1, in which the body (253) of the distribution element extends along a circumferential direction (D c ) of the turbine ring and the multi-perforated plate (295) opens out between the first (214) and second (216) hooking lugs of the ring sector.
    [3" id="c-fr-0003]
    3. An assembly according to any one of claims 1 and 2, wherein the distribution element comprises at least one holding element extending along the radial direction (Dr) of the turbine ring and coming to bear against the ring sector so as to maintain the latter in position in the radial direction.
    [4" id="c-fr-0004]
    4. An assembly according to any one of claims 1 to 3, wherein the distribution element is fixed to the ring support structure by at least one insert cooperating with an orifice defined by the guide portion of the cooling air and extending along the axial direction (D A ) and / or by at least one insert (219) cooperating with a housing defined by the body (253) of the distribution element (250) and extending along the radial direction (D R ).
    [5" id="c-fr-0005]
    5. Assembly according to any one of claims 1 to 4, in which the fixing plate (220) comprises a first (2201) and a second (2202) ends opposite one another in the circumferential direction and respectively bearing against the third hooking tab (217) and the fourth hooking tab (218), the first end (2201) comprising a first shoulder (2201a) bearing against the third hooking tab (217) and the second end comprising a second shoulder (2202a) bearing against the fourth
    5 latching lug (218), the first and second shoulders each extending in the axial and radial directions.
    [6" id="c-fr-0006]
    6. An assembly according to any one of claims 1 to 5, wherein the third and fourth hooking lugs (217; 218) are
    10 each coupled to the first and second hooking lugs (214; 216) respectively by a first and a second end (2171; 2172; 2181; 2182) projecting, in the radial direction of the turbine ring, in the extension of the first and second hooking lugs so as to raise the third and fourth
    15 attachment tabs relative to the second ends (2142; 2162) of the first and second attachment tabs.
    [7" id="c-fr-0007]
    7. Turbomachine comprising a turbine ring assembly according to any one of claims 1 to 6.
    1 / S 3 ° S SS3 3
    2/8
    0¾ 6
    633
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    类似技术:
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    FR3056633A1|2018-03-30|TURBINE RING ASSEMBLY COMPRISING A COOLING AIR DISTRIBUTION ELEMENT
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    同族专利:
    公开号 | 公开日
    FR3056632B1|2020-06-05|
    GB201719002D0|2018-01-03|
    US20180087399A1|2018-03-29|
    US20180087400A1|2018-03-29|
    FR3056634A1|2018-03-30|
    GB2556217A|2018-05-23|
    GB2556217B|2021-09-15|
    GB2556216A|2018-05-23|
    FR3056634B1|2021-04-23|
    US10415427B2|2019-09-17|
    US10428688B2|2019-10-01|
    US20180087401A1|2018-03-29|
    GB2556193B|2021-03-17|
    GB201719103D0|2018-01-03|
    FR3056632A1|2018-03-30|
    US10415426B2|2019-09-17|
    GB2556193A|2018-05-23|
    GB201715651D0|2017-11-08|
    FR3056633B1|2021-04-23|
    GB2556216B|2021-08-11|
    引用文献:
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    US9587517B2|2014-12-29|2017-03-07|Rolls-Royce North American Technologies, Inc.|Blade track assembly with turbine tip clearance control|
    US9874104B2|2015-02-27|2018-01-23|General Electric Company|Method and system for a ceramic matrix composite shroud hanger assembly|
    FR3033825B1|2015-03-16|2018-09-07|Safran Aircraft Engines|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL|
    FR3034132B1|2015-03-23|2018-06-15|Safran Ceramics|TURBINE RING ASSEMBLY COMPRISING A PLURALITY OF RING SECTIONS IN CERAMIC MATRIX COMPOSITE MATERIAL|
    FR3036435B1|2015-05-22|2020-01-24|Safran Ceramics|TURBINE RING ASSEMBLY|
    FR3036432B1|2015-05-22|2019-04-19|Safran Ceramics|TURBINE RING ASSEMBLY WITH AXIAL RETENTION|
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    FR3045715B1|2015-12-18|2018-01-26|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITH COLD AND HOT HOLDING|
    FR3048016B1|2016-02-18|2018-03-16|Safran Ceramics|TURBINE RING SECTOR WITH ENVIRONMENTAL BARRIER DOPED BY AN ELECTRICALLY CONDUCTIVE ELEMENT|
    FR3068071B1|2017-06-26|2019-11-08|Safran Aircraft Engines|ASSEMBLY FOR THE PALLET CONNECTION BETWEEN A TURBINE HOUSING AND AN ANNULAR TURBOMACHINE ELEMENT|FR3033825B1|2015-03-16|2018-09-07|Safran Aircraft Engines|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL|
    FR3055148B1|2016-08-19|2020-06-05|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3055146B1|2016-08-19|2020-05-29|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3055147B1|2016-08-19|2020-05-29|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3056637B1|2016-09-27|2018-10-19|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITH COLD SETTING|
    US10577976B2|2017-10-30|2020-03-03|United Technologies Corporation|Mounting assembly with rotatable and/or translatable retainer pins|
    US10704408B2|2018-05-03|2020-07-07|Rolls-Royce North American Technologies Inc.|Dual response blade track system|
    US10858949B2|2018-09-12|2020-12-08|Rolls-Royce Corporation|Multi-piece carrier assembly for mounting ceramic matrix composite seal segments|
    FR3108367A1|2020-03-20|2021-09-24|Safran Aircraft Engines|Turbine and turbomachine assembly fitted with such an assembly|
    US11208911B2|2020-04-23|2021-12-28|Rolls-Royce Plc|Turbine shroud ring segments with ceramic matrix composite components|
    US11220928B1|2020-08-24|2022-01-11|Rolls-Royce Corporation|Turbine shroud assembly with ceramic matrix composite components and cooling features|
    US11208896B1|2020-10-20|2021-12-28|Rolls-Royce Corporation|Turbine shroud having ceramic matrix composite component mounted with cooled pin|
    法律状态:
    2017-09-27| PLFP| Fee payment|Year of fee payment: 2 |
    2018-05-18| PLSC| Search report ready|Effective date: 20180518 |
    2018-08-31| PLFP| Fee payment|Year of fee payment: 3 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1601411A|FR3056632B1|2016-09-27|2016-09-27|TURBINE RING ASSEMBLY INCLUDING A COOLING AIR DISTRIBUTION ELEMENT|
    FR1601411|2016-09-27|
    FR1758747A|FR3056633B1|2016-09-27|2017-09-21|TURBINE RING ASSEMBLY INCLUDING A COOLING AIR DISTRIBUTION ELEMENT|FR1758747A| FR3056633B1|2016-09-27|2017-09-21|TURBINE RING ASSEMBLY INCLUDING A COOLING AIR DISTRIBUTION ELEMENT|
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