• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    An assembly comprising ring sectors (20) made of a first material is concerned, these sectors being circumferentially arranged end to end and suspended from an outer casing, and radial positioning means (125) comprising at least one annular flange (26) of a different material, for fixing the ring sectors (20) with the outer casing, via an annular support (24). The radial positioning means (125) further comprise: pins (100) fixed with said at least one annular tab; passages (120) in the ring sectors (20), where the pieces are with at least a radial clearance, and - elastic return means (130,131) arranged radially between said one annular tab (26) and the ring sectors (20), to urge a support between an outer circumference portion of at least one said pin and an outer circumference portion of the passage in which said pin is mounted.
    公开号:FR3068072A1
    申请号:FR1755848
    申请日:2017-06-26
    公开日:2018-12-28
    发明作者:Gerard Claude Lepretre Gilles；Mathieu Paul Marsal David；Arnaud Gimat Matthieu；Guy Xavier Tesson Thierry
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Assembly for the flexible connection between a turbine casing and an annular element of a turbomachine
    On a gas turbomachine turbine for aircraft, the present invention relates to the connection between an annular leg, made of a first material, fixed to an annular outer casing of the turbine and an annular sectored element, made of a second material having a coefficient of thermal expansion. different from the first material.
    The sectored annular element may in this description typically include one of:
    ring sectors, which are arranged circumferentially end to end and suspended from the outer casing, and sectors of the outer platform of blades of a distributor of said turbine, the two being therefore made of said second material.
    As a segmented annular element, the turbine rings make it possible to define a part of the external vein of the turbine, in particular of the HP turbine (high pressure), since on in particular the turbofan turbofan engines, the turbines comprise a turbine HP followed by a BP turbine (low pressure).
    HP turbine rings, which are parts subjected to very hot fluxes, are typically metallic elements which need to be cooled. This has a significant impact on the performance of the turbomachine since the required cooling flow is taken from the main gas flow. In addition, the use of metal limits the possibilities of increasing the temperature at the location of the turbine, which could however have made it possible to improve the performance of the turbomachine.
    In addition, the fact that the coefficients of thermal expansion of the first and second materials are different implies that they deform differently, in particular under the effect of thermal fields, which has an impact on the play at the level of the aforementioned vein. and therefore on the performance of the turbine. Games between rooms are to be managed accordingly.
    Comparable differential expansion problems exist in the outer platform areas of the HP turbine distributor vanes, but also on the first stage of the BP turbine distributor (DBP1).
    Minimizing the radial clearances between a so-called annular turbine leg and the sectorized annular element concerned is therefore important, for safety and for improving the efficiency of the turbomachine.
    Assembling the segmented annular element with a topology in Ρί (Π), called “piontée”, that is to say with pawns linking this element and the external casing, via said intermediate annular support is supposed to imply a positioning radial and control over time of this assembly, cold, therefore stopped, as well as at different engine operating temperatures. The mounting between the metal pins and their receiving holes should be done with harmful clearance, this so that the segmented annular element is well maintained and that the vein where it is placed is located radially in the right place. Indeed, the constitution of this vein, at the desired dimensions, contributes significantly to the performance of the turbine. However, at least two aspects do not allow this assembly to be performed with zero clearance:
    the manufacturing tolerances both on the pin (a priori metallic) and on the drilling in the second material: strength assembly in many cases, with local deterioration of the support, the differential expansions between the first and second hot materials; there may be matting and material damage. To overcome at least part of the above problems, a set is proposed comprising:
    an annular outer casing of a turbine of a gas turbomachine for aircraft, a segmented annular element, made of a first material, comprising one of:
    - ring sectors which are arranged end to end circumferentially and are suspended from said casing,
    - outer platform sectors of blades of a distributor of said turbine, radial positioning means comprising at least one annular tab, made of a second material having a coefficient of thermal expansion different from that of the first material, for:
    - fix the ring sectors with said outer casing, by means of an annular support, or
    - radially positioning, relative to said annular tab, the sectors of the outer platform of distributor vanes, this assembly being characterized in that the radial positioning means further comprise:
    pins fixed with said at least one annular tab, passages in the sectorized annular element, in which the pins are mounted with at least one radial clearance, and elastic return means disposed radially between said at least one annular tab and the 'annular sectorized element, to request support between an outer circumference portion of at least one pin and an outer circumference portion of the passage in which said pin is mounted.
    With such with a flexible intermediate piece (s) (the elastic return means), we will avoid possible radial clearance openings which would be linked to differential expansions. If, for example, the thermal paths of the various parts in question are different (which is always the case in real operation), said flexible intermediate part makes it possible to compensate for the differences obtained.
    In this way, we will also be able to minimize the ventilation necessary for the operation of the segmented annular element and thus limit the samples to be taken from the main flow of the engine, in the aforementioned vein. In addition, we will be able to better manage the shape of this vein in order to further improve the efficiency of the turbine, especially since the proposed solution therefore also applies to the radially external fixing part of a turbine distributor.
    On this subject, in the present application: radial has the direction perpendicular to the axis X around which the turbine blades rotate, for example, circumferential has the direction extending around the axis X, outside and inside (or outside and internal) respectively have a radially external and radially internal direction, axial has a direction parallel to the axis of rotation X already mentioned, and upstream and downstream are axial positions, with reference to the direction of overall displacement of the gases in the turbomachine.
    Preferably, the elastic return means will be designed and mounted to permanently stress radially, at different temperatures between -30 ° C and 600 ° C, the support between the outer circumference portion of at least one said pin and the outer circumference portion of the passage in which said pin is mounted.
    Thus, by establishing cold (approximately 20 ° C) an initial clearance between a said pin carried by said annular tab and the holes made in the sectored annular elements, it will be possible to compensate for the effects due to differential expansions. Indeed this game almost cancels in operation (hot) and then becomes compatible with the initial specifications, which are of the order of 1 to a few 100th of mm. We reduce the cold play, by acting on a flexible system (elastic return) put under stress so as to press the annular elements on the top of the pins, almost canceling the relative play.
    The proposed assembly makes it possible to significantly reduce (ideally to cancel) the radial cold clearance between the sectored annular elements and said annular tab, this clearance being moreover controlled under hot conditions by the relative swelling of the pins in the holes of these elements, as soon as the preload of the flexible element (elastic return means) will tend to cancel out when hot. The added flexible element also makes it possible to ensure contact without constraining the manufacture of the segmented annular elements.
    Among the advantages of the proposed assembly, we can note the interest of the device of the vice system used. The pin is mounted with a play in the hole. This play persists when hot, which makes it possible to overcome manufacturing tolerances and differential expansions which can damage the second material; The pin is pressed against the upper surface of the hole; In order to maintain this position (the position cannot be maintained in a natural way, due to the pawn / drilling assembly set) an element opposite the pawn is used to create the vice system with the top of the pawn.
    In addition, in the solution presented here, there are two complementary parts: a stop on the segmented annular element linked to the casing, and at least one intermediate piece (elastic return means), such as the flexible blade. The contacting is done by "compressing" these elastic return means. The use of flexible elements ensures that contact is possible when cold, with this contact being maintained throughout the engine operating phases.
    By providing that said elastic return means comprise curved blades, it will also be possible to distribute the supports in an adapted manner and this precisely, in the preferred locations, thereby favoring control of the constraints.
    On the same subject, it is also advised, in a first possible embodiment, that, circumferentially, the elastic return means be individually mounted between two circumferentially successive pins.
    In this case, circumferentially, a said elastic return means may be in contact with the sectorized annular element concerned and request said support circumferentially between said two successive pins, while it will also be in contact with the annular tab substantially at right of said two circumferentially successive pawns. Thus, the length of each elastic return means will be optimized and the internal stresses will be reduced.
    Regarding this support located between said two successive pins, it will then be favorably biased by said elastic return means via a radial support against an outer surface of the segmented annular element.
    By circumferentially centering this radial support, it will further promote a good balance of stresses, and this is easy to implement. We can even lighten the segmented annular element by forming a wedging groove of the elastic return means concerned in said outer surface.
    In a second possible embodiment, it is proposed that, circumferentially, said elastic return means be in contact with the sectored annular element and urge said support substantially in line with two said pins circumferentially distant from each other , while the elastic return means will then be in contact with said annular tab between said two pins circumferentially distant from each other. Several (at least two) of these intermediate contacts with the annular tab can thus be favored, this being able to be as favorable to the balance of the stresses, because carried out on a larger radius than in the case of the previous solution.
    In this case, provision may be made for a third said pin to be circumferentially interposed between said two pins circumferentially distant from each other, the contact of the elastic return means with said annular tab being situated substantially in line with the third said pin. .
    We can thus refine the guidance of moving parts and therefore the balance of forces.
    For the same purpose, and whatever version is chosen, it may also be advantageous for at least some of the pawns (a priori said two successive pawns) to be mounted in the passages which receive them with also a circumferential clearance.
    Guidance and balance will come together.
    Given the preferred applications targeted, it is expected that in particular 5:
    the first material of said annular turbine leg is a metal or a metal alloy, and the second material of the sectorized annular element contains a ceramic matrix composite.
    In fact, the difference in thermal expansion coefficients between these two materials can be critical under certain temperature and / or pressure conditions.
    In addition to the above assembly, there is also concerned a gas turbomachine for an aircraft comprising this assembly, with all or some of the characteristics mentioned above.
    The invention will be better understood if necessary and other details, characteristics and advantages of the invention may appear on reading the following description given by way of nonlimiting example with reference to the accompanying drawings in which:
    - Figure 1 shows schematically, in axial partial section (axis X), an aeronautical turbomachine part to be mounted on an aircraft, Figure 2 shows schematically, in perspective and same section plane II as that of Figure 3, the embodiment shown in Figure 3, FIG. 3 shows in local section along the same section plane as FIG. 1, an embodiment according to the invention in zone III of FIG. 1 with, as in all of FIGS. 2-7, an annular tab (26 or 26 'below) of which only the radially inner part is shown, Figure 4 is a section along line IV-IV of Figure 3, with three local enlargements, Figures 5-7 show an alternative embodiment and assembly in accordance to the invention, according to the same views as those of FIGS. 24, respectively, FIGS. 8, 9 schematize, according to the same views as those of FIGS. 2 and 5, two other embodiments according to the invention in zone X or XI of Figure 1 with another pa annular head (260 or 260 ’below) of which only the radially inner part is shown, and FIG. 10 shows one of the elastic return means, here a curved blade, in two states: solid line, compressed state; dotted, free state.
    Figure 1 shows schematically a part of a known turbomachine 1, such as a turbojet or an airplane turboprop comprising a high-pressure turbine (HP) 10 disposed axially (axis X) downstream (AV) of a combustion 12, and upstream (AM) of a low-pressure turbine (BP) 14 of the turbomachine.
    The combustion chamber 12 comprises an external wall of revolution 50 connected at its downstream end to a radially internal end of a frustoconical wall 58 which comprises at its radially external end a radially external annular flange 60 for fixing to a corresponding annular flange 62 d 'an external casing 64 of the chamber. The high-pressure turbine 10 comprises in the example a single turbine stage comprising a distributor 16 formed by an annular row of fixed straightening vanes, and an impeller 18 rotatably mounted downstream of the distributor
    16. The low-pressure turbine 14 comprises several turbine stages, each of these stages also comprising a distributor and an impeller. Only the distributor 47 of the upstream low-pressure stage is visible in FIG. 2. Its blades are those of the first stage of distributors, or DBP1. The rotor vanes 18 and the distributors 16, 47 extend in the gas stream 12a to which the combustion chamber 12 is connected downstream. The wheel 18 of the high-pressure turbine 10 rotates around the longitudinal axis. X of the turbomachine, inside a substantially cylindrical assembly of ring sectors 20 which are arranged circumferentially end to end and suspended from an external turbine casing 22 by means of an annular support 24. This support annular 24 comprises at its internal periphery means 26 for hooking the ring sectors 20, also called annular tab 26, and comprises a wall 28 which extends upstream and outward and which is connected to its radially external end to a radially external annular flange 30 for fixing to the external turbine casing 22. A flange 60 is interposed axially between the flange 30 and a flange 62 of the turbine casing 22 and is clamped axially between these flanges by appropriate means of the screw-nut type 7.
    At the outer periphery, the attachment means 26 comprise (first) radial annular walls 31, 33, respectively upstream and downstream, which define flanges (here oriented downstream), which cooperate with (are suspended from) hooks circumferentials 310,330 provided at the internal periphery of a part of the wall 28 of the annular support 24.
    The annular tab 26 further comprises, on the internal periphery, two other (or second) radial annular walls 34, 36, respectively upstream and downstream, which define flanges (here oriented downstream), which cooperate with circumferential hooks 340,360 provided at the upstream and downstream ends of the ring sectors 20. An annular locking member 46 with a C section is axially engaged from downstream on the downstream cylindrical rim 36 and on the downstream hooks 360 of the ring sectors to ensure the locking the assembly.
    Further upstream, the wall 28 of the annular support 24 defines with the frustoconical wall 58 of the chamber an annular enclosure 80 which is supplied with air (arrow F) for ventilation and cooling by orifices 82 formed in the frustoconical wall 58.
    The external platform 66 sectorized of the distributor 16 comprises at each of its upstream and downstream ends an annular groove 74 opening radially outwards. Annular seals 76 are housed in these grooves 74 and cooperate with cylindrical ribs 78 formed on the frustoconical wall 58 and on a radial wall upstream of the attachment means 26, respectively, to prevent the passage of gas from the vein 12 / 12a of the turbine, radially, towards the outside of the outer platform sectors 66, and conversely, the passage of air from the enclosure 80 radially towards the inside, in the vein of the turbine.
    Furthermore, in order to increase the efficiency of the turbine, it is necessary to reduce as much as possible the radial clearance between the top of the movable blades 18 and the ring 20. An additional clearance control device 39 is therefore provided, which comprises a circular control box 40 surrounding the fixed ring 20, and more precisely the annular support 24.
    According to the operating regimes of the turbomachine, the control unit 40 is intended to cool or heat the upstream 240 and downstream 242 fins of the annular support 24 by discharging (or impact) of air thereon. Under the effect of this air discharge, the annular support 24 retracts or expands, which decreases or increases the diameter of the fixed ring segments 20 of the turbine in order to adjust the clearance at the top of the blades 18 The control box 40 supports annular air circulation ramps 41, 42 and 43 which surround the aforementioned wall portion 28 of the annular support 24. The control box 40 also comprises an air collecting tube which surrounds the ramps 41, 42 and 43 and supplies them with air via lines 44.
    The DBP1 distributor 47 is, by its sectored external platform 48, mounted on the annular support 24, downstream of said wall portion 28. For this, the external platform 48 is extended radially at the external periphery by lugs provided with annular walls ( with components) radial 49,51, respectively upstream and downstream, which have flanges 49,51 (here oriented upstream), which cooperate with (are suspended from) circumferential hooks 370,380 of the annular support 24.
    With these mounting solutions in particular, however, there is still a need to minimize the radial clearances between the annular tab (hereinafter identified as 26.26 ', 260 or 260') of the turbine in question and the sectorized annular element concerned (here the ring sectors 20 or 20 'below, or at least one of the external platforms 48, 66), this for safety and in order to improve the efficiency of the turbomachine, all the more so if the material of the annular lug is a metal or a metal alloy and the second material of the sectorized annular element contains a ceramic matrix composite (CMC).
    Figures 2 to 7 thus show ways, different from the above, of mounting the ring sectors 20 or 20 ’with the annular support 24, via the annular tab 26 or 26’ and means 125, 125 ’for radial positioning.
    In connection with FIGS. 2 to 4, a first solution provides for fixing, in particular suspending, the ring sectors 20 to the annular lug 26 by means of pins 100 fixed with said annular lug. Passages 110 which cross axially the ring sectors 20 make it possible to mount the pins 100 (one pin per passage 110). The pins 100 are mounted there with at least one radial clearance J1, J2. Opposite, coaxial passages 120 adjusted to the diameter (s) of the pins receive them in the annular tab 26; see figures 2,3.
    For this, the annular tab 26 has radial branches 113,115, respectively upstream and downstream, connected in part radially outer by a substantially axial branch 114 and each ring sector 20 has radial branches 117,119, respectively upstream and downstream, connected in part radially inner by a transverse branch which can be substantially axial, 114. The transverse branch 114 can serve as a support for abradable blocks (not shown) intended to cooperate with wipers (not shown) which can be provided at the outer end of the blades mobile 18.
    Elastic return means 130 disposed radially between the annular tab 26 and (individually) the ring sectors 20 make it possible to stress radially, in the direction of the arrows F1 and in a flexible manner, a support between an outer circumference portion 100 of at least one pin 100 (per ring sector) and a portion of outer circumference 110a of the passage 110 in which the considered pin is mounted.
    On this subject, it is here provided that the elastic return means 13 are adapted and mounted, as illustrated, to permanently stress radially, at different temperatures between -30 ° C and 600 ° C, the support between the portion 100a of outer circumference of at least one said pin and the portion of outer circumference 110a of the corresponding passage 110 in which this pin is therefore mounted with a radial clearance.
    For the reasons already explained, the elastic return means 130 will favorably include curved blades 131.
    Figure 10 shows one of the elastic return means, here one of the curved blades, in two states: full compressed line (references 13O'a, 131'a, normal state, valid hot or cold) and free state, not constrained , before mounting (references 130'b, 131 'b).
    Note, moreover, that in the two embodiments of Figures 2 to 4 and 5 to 7 respectively, it will preferably be a question of associating adapted stiffness and good distribution of the supports, each of blades having triple curvature: two lateral oriented radially in the same direction, (respectively 133a, 133b and 133a ', 133b') and a radially opposite (respectively 135 and 135 ') located between the two preceding ones, this along the circumference C of the sectors of ring 20 and the ring tab 26.
    Circumferentially, in the embodiment of FIGS. 2 to 4, the elastic return means 130 are individually mounted between two circumferentially successive pins 100. Each ring sector is then constrained by a single means 130, individually, which guarantees the correct distribution of the loads on each ring. The creation of parasitic games resulting from an adaptation of said return means is prevented in the event that it presses on several sectors.
    Thus, it will be possible that, still circumferentially (direction C), a said elastic return means 130 is in contact with the ring sector 20 considered and then requests the aforementioned circumferential support between said two successive pins 100 (see zone 17 in FIG. 4, for the left elastic return means 130), while with the annular tab 26, this same means 130 will be in contact substantially at the right of said two pins
    100 circumferentially successive; see lateral zones 19a, 19b, figure 4.
    Circumferentially, each blade 131 can be wedged at its opposite ends via axial studs 15a, 15b fixed in the tab 26, at the location of the lateral zones 19a, 19b.
    It may also be advantageous that, as in the embodiment of FIGS. 2 to 4, each elastic return means 130 requests this support (circumferentially intermediate between the two successive 100 pins) by radial support against an external surface 20a of the sector ring 20 considered.
    Favorably, the studs 15a, 15b will initially ensure the circumferential setting of each means 130, their contribution to facilitate assembly and maintenance being obtained by their positioning so that they retain each means 130 over the entire circumference.
    Note also the preferably circumferentially centered nature of each radial support 17 vis-à-vis both the ring sector 20 and the blade 131, this further promoting a good balance of stresses, and easy to implement . A groove 21 formed in the outer surface 20a may even make it possible to lighten the segmented annular element and to angularly wedge the elastic return means 130 concerned.
    In this first embodiment, for the balancing already mentioned of the applied forces, it can be provided that, as illustrated, at least some of the pins 100 are mounted in the passages 110 which receive them with also a circumferential clearance, J3, J4 ; see figure 4.
    The second embodiment with elastic return means is illustrated in FIGS. 5 to 7.
    As can be seen, the same means or the means ensuring the same functions as those of the first embodiment of FIGS. 2 to 4 have been identified identically with the mark ‘(prime) close.
    Thus, in this second embodiment, circumferentially, a said means 130 ’of elastic return is in contact with the ring sector 20’. In addition, circumferentially, the means 130 'then requests support between the portion 100a' of external circumference of at least one pin 100 'and a portion 110a' opposite the external circumference of the passage 110 'in which this pin is mounted ; and this takes place substantially in line with two said pins 100 'circumferentially distant from each other, while this means 130' of elastic return is also in contact with the annular tab 26 'between these two said pins circumferentially 100 'distant from each other.
    In this case, it is moreover advised that then a third said pin 140 'is circumferentially interposed between said two pins 100' circumferentially distant from each other, the longitudinally central zone 135 ', curved against the direction of two lateral bends 133a ′, 133b ′ in contact with the elastic return means 130 ′ with the annular tab 26 ′ then being situated substantially at the level of this third pin 140 ′ (therefore on the same radial).
    In this version, circumferentially (direction C ′), a said elastic return means 130 ′ is in contact with the annular tab 26 ′ and requests the aforementioned circumferential support between the said two successive pins 100 ′ (see zone 170 in FIG. 7). , for the means 130 'of elastic return on the left), while with the ring sector 20' considered, this same means 130 'will be in contact substantially at the right of said two pins 100' circumferentially successive, therefore on the same radial ; see side zones 190a, 19b in Figure 7.
    And again as before, each blade 131 ’can, circumferentially, be wedged at its opposite ends via axial studs 15a’, 15b ’fixed in the spacer, here that 26’, at the location of the lateral zones 190a, 190b.
    To also facilitate assembly and maintenance, it may also be advantageous, as in the embodiment of FIGS. 2 to 4, that each means 130 'of elastic return urges said circumferentially intermediate support between the two 100' successive pins by support radial against the internal surface 261 ′ of the annular tab 26 ′, the lateral supports operating against the external surface 20 a ′ of the ring sector 20 ′ considered.
    In the versions of Figures 8 and 9, we find the alternatives of Figures 2 and 5, respectively, with in the case of these Figures 8 and 9, the ring sectors 20,20 'of Figures 2 and 5 which are replaced by the external platforms 48,48 'or 66,66' sectorized with turbine distributor vanes, which external platforms are therefore made of a material having a coefficient of thermal expansion different from that of the material of the annular tab, respectively 260,260 ', which surrounds it and to which these external platforms 48 or 66 are fixed by the pins, 100 ”, 100” ', respectively, with a capacity of relative radial movement, as previously.
    Again, the same means or the means ensuring the same functions as those of the first embodiment of Figures 2 to 4 have been identified identically, with the mark ', or close.
    Each annular tab 260, 260 'of the radial positioning means 125 ”, 125” will thus make it possible to position radially with respect to it, the external part of the sectors of the external platform 66, 48 or 66', 48 'of distributor vanes: the elastic return means 130 ”, 130” ', arranged radially between the annular tab and said external platform, as a segmented annular element, will urge the radial support between a portion of external circumference of at least one of said pins 100 ”, 100” 'and the outer circumference portion of the passage in which the considered piece is mounted. On this subject, the views of Figures 3,4 on the one hand and
    6.7 on the other hand are applicable as additions to Figures 8 and 9, respectively.
    In the version applied to an external platform 66 sectorized with HP 10 turbine distributor vanes, the annular tab 260 or 260 ’can be inserted between the upstream and downstream cylindrical ribs 78 which can be seen in FIG. 1.
    The passages 110 ”, 110 '” which cross axially the radial branches 117 ”, 119” or 117' ”, 119 '”, respectively upstream and downstream, of the sectors of external platforms 66,48 or 66', 48 'of the blades of distributor allow mounting the 100 ”or 100” studs (one stud per passage) with at least the radial clearance already mentioned. Opposite, the passages
    120 ", 120" coaxial, provided in the upstream and downstream radial branches
    113 ”, 115” or 113 ’”, 115 ’”, respectively, of the annular lug 260 or 260 ’, receive the pins in an adjusted manner; see figures 8.9.
    The transverse branch which is present in the radially inner part of the radial branches 117 ”, 119” or 117 ’”, 119 ”’ can serve as an (part of) external platform for the distributor blades concerned. The outer platform sectors 48 of FIG. 1 with their annular (component) radial walls 49, 51 could thus be replaced by said radial branches 117 ”, 119” or 117 '”, 119” ”, and the hooks 370, 380 of the support annular 24 of this figure 1 being by the radial branches 113 ”, 115” or 113 '”, 115'” of the annular legs 260, 260 ', respectively, which annular legs could themselves then be a part of the annular support 24.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Set including:
    an annular outer casing (22) of a gas turbine engine for an aircraft, an annular element sectorized from a first material, comprising one of:
    - ring sectors (20,20 ’) which are arranged end to end circumferentially and are suspended from the outer casing,
    - outer platform sectors (48,66,48 ', 66') of blades of a distributor of said turbine, means (125,125 ', 125 ”, 125”') of radial positioning comprising at least one annular tab (26,26 ', 260,260') in a second material having a coefficient of thermal expansion different from that of the first material, for:
    - fix the ring sectors (20) with the outer casing (22), by means of an annular support (24), or
    - radially positioning, relative to said annular tab, the sectors of the outer platform (48,66) of distributor vanes, characterized in that the means (125,125 ’) for radial positioning further comprise:
    pins (100,100 ', 100 ”, 100”') fixed with said at least one annular lug (26,26 (260,260 '), passages (120,120', 120 ”, 120” ') in the sectored annular element, in which the pins are mounted with at least one radial clearance, and elastic return means (130,130 ', 130 ”, 130”') arranged radially between said at least one annular tab (26,26 ', 260,260') and l 'sectorized annular element, to request support between an outer circumference portion of at least one said pin and an outer circumference portion of the passage in which said pin is mounted.
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein the elastic return means (130,130 ', 130 ”, 130”') are designed and mounted to stress radially continuously, at different temperatures between 30 ° C and 600 ° C, l support between the outer circumference portion of at least one said pin and the outer circumference portion of the passage in which said pin is mounted.
    [3" id="c-fr-0003]
    3. Assembly according to any one of the preceding claims, in which the elastic return means (130,130 ’, 130”, 130 ’”) comprise curved blades.
    [4" id="c-fr-0004]
    4. Assembly according to any one of the preceding claims, in which, circumferentially, the elastic return means (130,130 ', 130 ”, 130” ”are individually mounted between two circumferentially successive pins (100,100', 100”, 100 ' ").
    [5" id="c-fr-0005]
    5. The assembly as claimed in claim 4, in which, circumferentially, said elastic return means (130,130 ', 130 ”, 130” ”) is in contact with the sectorized annular element and urges said support circumferentially between said two successive pins, while it is in contact with the annular tab (26,26 ', 260,260') substantially in line with said two circumferentially successive pins.
    [6" id="c-fr-0006]
    6. The assembly of claim 5, wherein said elastic return means (130,130 ', 130 ”, 130'”) request the support circumferentially between said two successive pins (100,100 ', 100 ”, 100'”) by pressing against an outer surface of the segmented annular element, radially.
    [7" id="c-fr-0007]
    7. Assembly according to any one of the preceding claims, in which at least some of the pins (100,100 ’, 100”, 100 ’”) are mounted in the passages which receive them with also a circumferential clearance.
    [8" id="c-fr-0008]
    8. Assembly according to one of claims 1 to 3, wherein, circumferentially, a said elastic return means (130,130 ', 130 ”, 130” ”) is in contact with the sectored annular element and biases, circumferentially, said support substantially at the right of two said pins circumferentially distant from each other, while the elastic return means is in contact with the annular tab (26,26 ', 260,260') between said two pins circumferentially distant one the other.
    5
    [9" id="c-fr-0009]
    9. The assembly of claim 8, wherein a third said pin is circumferentially interposed between said two pins circumferentially distant from each other, the contact of the elastic return means with the annular tab (26,26 ', 260,260' ) being located substantially to the right of the third said pawn.
    [10" id="c-fr-0010]
    10. Assembly according to any one of the preceding claims, in which the first material of the annular leg (26,26 ', 260,260') of a turbine is a metal or a metal alloy and the second material of the sectorized annular element contains a ceramic matrix composite.
    [11" id="c-fr-0011]
    11. An aircraft gas turbine engine comprising the assembly according to any one of the preceding claims.
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    FR2972759A1|2012-09-21|Wheel for rotor of low pressure turbine in e.g. turbojet of airplane, has annular part defining radial plane to axially support blades and align blades with disk, and tightly maintained against downstream faces of teeth by downstream plate
    FR3006366A1|2014-12-05|TURBINE WHEEL IN A TURBOMACHINE
    FR2969209B1|2019-06-21|TURBINE STOVE FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED SEAL BETWEEN THE FLASK AND THE TURBINE BLADES
    FR2961848A1|2011-12-30|TURBINE FLOOR
    WO2016146920A1|2016-09-22|Assembly with sealing plates for gas turbine
    WO2015044579A1|2015-04-02|Rotary assembly for a turbomachine
    FR2961850A1|2011-12-30|Turbine i.e. low pressure turbine, for e.g. turbojet engine of airplane, has distributor whose upstream and downstream edges are supported against casing via runners that are made of thermically insulator material
    FR2923526A1|2009-05-15|TURBINE OR TURBOMACHINE COMPRESSOR STAGE
    EP3721058A1|2020-10-14|Connection between a ceramic matrix composite stator sector and a metallic support of a turbomachine turbine
    FR3021692A1|2015-12-04|SEAL PLATE WITH FUSE FUNCTION
    FR3053384A1|2018-01-05|FIXING ASSEMBLY OF A DISTRIBUTOR TO A STRUCTURAL ELEMENT OF A TURBOMACHINE
    FR3075271A1|2019-06-21|ASSEMBLY FOR FIXING BETWEEN ELEMENTS WITH DIFFERENT THERMAL EXPANSION COEFFICIENTS
    FR3049307A1|2017-09-29|ROTARY ASSEMBLY FOR TURBOMACHINE
    FR3087825A1|2020-05-01|TURBINE RING SECTOR WITH COOLED SEALING TONGS
    同族专利:
    公开号 | 公开日
    FR3068072B1|2020-09-04|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2651830A1|1989-09-08|1991-03-15|Gen Electric|MECHANICAL DEVICE FOR CONTROLLING THE PLAY OF BLADES IN A GAS TURBINE ENGINE.|
    WO2016189224A1|2015-05-22|2016-12-01|Herakles|Turbine ring assembly supported by flanges|
    WO2017103411A2|2015-12-18|2017-06-22|Safran Ceramics|Turbine ring assembly, elastically retained in a cold-state|FR3093344A1|2019-03-01|2020-09-04|Safran Ceramics|SET FOR A TURBOMACHINE TURBINE|
    FR3096726A1|2019-06-03|2020-12-04|Safran Ceramics|Turbomachine turbine assembly|
    WO2021191538A1|2020-03-24|2021-09-30|Safran Aircraft Engines|Turbine shroud assembly|
    法律状态:
    2018-12-28| PLSC| Search report ready|Effective date: 20181228 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 3 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1755848A|FR3068072B1|2017-06-26|2017-06-26|KIT FOR THE FLEXIBLE CONNECTION BETWEEN A TURBINE CASING AND A TURBOMACHINE ANNULAR ELEMENT|
    FR1755848|2017-06-26|FR1755848A| FR3068072B1|2017-06-26|2017-06-26|KIT FOR THE FLEXIBLE CONNECTION BETWEEN A TURBINE CASING AND A TURBOMACHINE ANNULAR ELEMENT|
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