• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
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    • 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 comprises an eccentric spreader (101) engaged on one side with said at least one annular tab (26) and, on the other hand, with the segmented annular element, and acting to allow to adjust radially the distance between said at least one annular tab and the segmented annular element.
    公开号:FR3068071A1
    申请号:FR1755847
    申请日:2017-06-26
    公开日:2018-12-28
    发明作者:Gerard Claude Lepretre Gilles；Guy Xavier Tesson Thierry；Jean-Yves Illand Hubert；Henri Jacques Quennehen Lucien；Arnaud Gimat Matthieu
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Assembly for the linkage by spreader 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 outer platform sectors of vanes of a distributor of said turbine, the two therefore being 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 mounting 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 gas turbine engine for an aircraft,
    - an annular element segmented from a first material, comprising one of:
    - ring sectors which are arranged circumferentially end to end and are suspended from the outer casing,
    - sectors of the external platform of blades of a distributor of said turbine,
    - radial positioning means comprising at least one annular tab in a second material having a coefficient of thermal expansion different from that of the first material, for:
    - fix the ring sectors with the outer casing, via an annular support, or
    position radially with respect to said annular lug the sectors of the external platform of distributor vanes, characterized in that the radial positioning means further comprise an eccentric lifter engaged on one side with said at least one annular lug and, on the other hand, with the sectorized annular element, and acting to allow the distance between said at least one annular tab and the sectorized annular element to be radially adjusted.
    Thus, we will 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 stream, therefore increasing the performance of the turbomachine. In addition, we will be able to better manage the shape of this upper vein, especially since the proposed solution therefore also applies to the radially external fixing part of a turbine distributor.
    On this subject, in the present request:
    - radial has the direction perpendicular to the axis X around which the turbine blades rotate, for example,
    - circumferential has the meaning extending around the X axis,
    - external and internal (or external and internal) have radially external and radially internal directions respectively,
    - axial has the direction parallel to the axis of rotation X already mentioned,
    - spreader has the meaning of a device allowing an effort to be distributed evenly, generally between two points, the English term spreader is sometimes used, and
    - Upstream and downstream are axial positions, with reference to the overall direction of movement of the gases in the turbomachine.
    Preferably, the eccentric lifter will include studs mounted with clearance in passages of the segmented annular element and will be arranged to urge support between an outer circumference portion of at least one said pin and an outer circumference portion of the passage in which said pawn is mounted.
    Thus, by establishing cold (approximately 20 ° C) an initial clearance between a said pin carried by said at least one 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 some 100 th of mm. We reduce the cold play, by acting on an adaptive system, put under stress so as to press the annular elements on the top of the pins, almost canceling the relative play.
    The / each eccentric lifter will be used to ensure the assembly (thus "cold", at room temperature, turbomachine stopped) the contact mentioned. Once the radial positioning has been ensured, the / each eccentric lifter is blocked. Contact is therefore ensured permanently whatever the operating temperatures (which can be framed between - 30 ° C and 600 ° C).
    The proposed assembly makes it possible to significantly reduce (ideally to cancel) the cold radial clearance between the segmented annular elements and said at least one annular tab. As for the hot setting, it is obtained by the linear mounting of the contact surfaces between the pins of the spreader, the oblongs of the passages of the ring sector, the planes or external faces of these and the internal planar faces of support ( 261 a, 261 b below) of the lugs located on said annular legs of the casing. The attached eccentric spreader also ensures contact without constraining the manufacture of segmented annular elements.
    Providing that the eccentric lifter:
    - includes a lifting beam and an eccentric, and
    - Either linked to said at least one annular tab via the eccentric including an operating rod, which extends parallel to an axis along which extend coaxially said at least one annular tab and the segmented annular element , either engaged without play in a first passage of said at least one annular tab and is maneuverable for adjusting said radial distance, two groups of two so-called rudder pins, each parallel to said axis, being mounted with at least one radial play in said passages of the annular element sectorized circumferentially distant from one another, it will also be possible to distribute the supports in an adapted manner and this precisely, in the preferred locations, thereby favoring a control of the constraints.
    Among the advantages of the proposed assembly, one can note the interest of the device of the vice system used. The pin is mounted with a clearance 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 manner, due to the pawn / drilling mounting clearance), the (so-called flat internal faces of the) lugs of said annular legs of (linked to) are used casing which are offset from the pins to be on a common tangent line with bearing surfaces (260a, 260b below), in order to create the vice system with the top of the pin.
    To promote flexible and permanent adaptation of the assembly as a function of the operational conditions encountered, it is further proposed that elastic return means are provided in the radial direction which will radially stress the segmented annular element towards said at least one annular tab.
    Using such flexible elements (the elastic return means may be washers), in addition to offering an additional degree of rotation on the lifter, makes it possible to compensate for parasitic thermal gradients linked to the different metallic components of the lifter and of the casing and the non-control of the expansion coefficients of the latter.
    Preferably the eccentric lifter will include a radial tie rod on which the eccentric can act radially, thus ensuring a radial adjustment of said two groups of two other pins.
    Still to promote the balancing of the forces as often as possible under very varied operating conditions in terms of temperature and mechanical stresses, it is also proposed that said two groups of other pins are, in groups respectively engaged in the passages of the segmented annular element, themselves engaged with respectively a first and a second traction fingers pivotally mounted with respect to the lifter about an axis perpendicular to said radial direction of adjustment and to said axis along which coaxially extend said at least one annular tab and the sectorized annular element.
    In this regard, it may even be preferred that said other pins of each of the two groups are pivotally engaged in the first and second respective traction fingers, in order to be able to rotate around respective axes parallel to said axis along which coaxially extend said at least one annular tab r and the segmented annular element.
    For the same considerations, it is also proposed that the radial tie rod and the lifting beam can rotate relative to one another about an axis parallel to said radial direction of adjustment.
    The aforementioned degrees of freedom, individually and in combination, favor the expected contacts between said at least one annular tab and the segmented annular element.
    It is moreover provided that the two so-called pawns of each group can each be mounted in the passage which receives it with also a circumferential clearance.
    We can thus refine the guidance of moving parts and therefore even more the balance of forces.
    Two other considerations were also taken into account:
    firstly, that there is provision, next to the eccentric lifter, and for an angular setting, another pin extending parallel to said axis which coaxially extend said at least one annular tab and the sectored annular element, and engaged:
    - without play in another passage of said at least one annular tab,
    - And, with a radial clearance, through an orifice of the sectorized annular element;
    - Or that said other pawn is located radially below the eccentric and circumferentially between the two said pawns of one of said groups of pawns, halfway between each of them.
    With this additional pin, we will be able to ensure an angular blocking of positioning of the annular element sectorized in the vein. Positioning it in the center allows the deltas of length to be distributed symmetrically between the sectors and the casing (its annular legs), and to obtain a more homogeneous vein shape.
    Given the preferred applications targeted, it is also planned in particular:
    the first material, said at least one annular leg of the turbine, is a metal or a metal alloy, and
    - that the second material of the segmented 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:
    FIG. 1 shows diagrammatically, in axial partial section (axis X), a part of an aeronautical turbomachine to be mounted on an aircraft,
    FIG. 2 shows diagrammatically, in perspective and same section plane II as that of FIG. 4, the embodiment shown in FIG. 4,
    - Figure 3 is a perspective of an annular element sector, with an eccentric spreader, but without annular leg of the turbine,
    - Figure 4 shows in local section along the same section plane as Figure 1, an embodiment according to the invention in zone III of Figure 1 with, as in all Figures 2-7, an annular tab (26 ci -after) of which only the radially inner part is shown,
    FIG. 5 corresponds to section V-V of FIG. 4,
    FIG. 6 is an exploded view of the eccentric lifter,
    - Figure 7 shows, according to the same view as that of Figure 4, another embodiment according to the invention in zone X or XI of Figure 1 with another annular tab (26 'below) of which only the part radially inner is shown, and
    - Figures 8 and 9 show the mode of operation of the general solution of the invention.
    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.
    However, with these mounting solutions in particular, there is still a need to minimize the radial clearances between the annular tab (hereinafter marked 26 or 26 ′) of the turbine in question and the sectorized annular element concerned (here the ring sectors 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, and this all the more if the material of the annular tab is a metal or a metal alloy and the second material of the segmented annular element contains a ceramic matrix composite (CMC).
    Figures 2 to 6 thus show ways, different from the above, of mounting the ring sectors 20 with the annular support 24, via the annular tab 26 or 26 ’and means 125,125’ for radial positioning.
    These figures thus show a different way from the above to mount, with the annular support 24, via at least one annular tab 26 or 26 ’:
    - either the ring sectors 20 (solution illustrated in FIGS. 2 to 5),
    - Or sectors of external platforms 48 and / or 66 of blades of a turbine distributor (solution illustrated in Figure 7).
    Thus it is proposed in a solution according to the invention to link together, in particular suspend, the ring sectors 20 or 20 'to the annular tab 26 or 26' by means of positioning means 125 or 125 ' radial, which include eccentric spreaders 101 or 101 '(typically one per ring or platform sector) engaged:
    - on one side with the annular tab 26 or 26 ’,
    - and on the other hand with the segmented annular element concerned.
    These eccentric spreaders will act to allow the distance between the annular tab 26 or 26 ’and the segmented annular element in question to be radially adjusted.
    A practical and effective assembly consists, in the first solution illustrated in FIGS. 2 to 5, so that each eccentric lifter 101 comprises pins 103 mounted with clearance (J) in axial passages 105 (axis X, preferably two coaxial; see Figure 2) of the ring sector 20 considered and is arranged to urge a support between a portion 103a of outer circumference of at least one said pin and a portion 105a of outer circumference of the passage 105 in which said pin is mounted. Coaxially with each passage 105, the pin 103 considered is, at least at one axial end engaged without play in an orifice 106 in the annular tab 26.
    Thus, the eccentric spreaders will serve to provide the desired support for mounting (therefore cold), as explained below, with reference to FIGS. 8 and 9. Once the radial positioning has been ensured, the eccentric spreaders are blocked. The contact is therefore permanently ensured whatever the operating temperatures (which can be framed between - 30 ° C and 600 ° C).
    For the connection between each ring sector 20 and the annular tab 26, the two comprise in the example two radial tabs, respectively 200a, 200b; 206a, 206b (Figures 2,4), sectorized for the ring sectors 20 and non-sectorized for the annular tab 26. Radially offset, each orifice 106 is formed in the radial tab 206b, while the lifter 107 with its rod of operation 119 crosses the radial tab 206a.
    In this regard, it is advised that the eccentric spreader 101 therefore comprises a spreader 107 and an eccentric 109, and is linked to the annular lug 26 via the eccentric 109 including an operating rod 119, which s extends parallel to the axis X, is engaged without play in at least a first axial passage 111 of the annular tab 26 and is maneuverable for adjusting the radial distance J, two groups (103b, 103c) of two said pins 103 of the lifting beam, each parallel to the axis X, being mounted with at least the radial clearance J in the passages 105 circumferentially distant from each other of the annular tab 26.
    In more detail, the solution presented here is such that, for the reasons already mentioned, the eccentric lifter 101 comprises means 115, such as two superimposed washers, of elastic return in the radial direction which urge radially towards the annular tab 26 the sector ring 20 considered. The means 115 are in radial abutment against a flange 116, in said direction R of adjustment. In addition, a radial tie rod 113, here threaded, is provided, on which the eccentric 109 acts radially, for a radial adjustment of said two groups of two other pieces 103b, 103c.
    Arranged radially inside with respect to the eccentric 103, the elastic return means 115 will absorb the radial jolts and will stress outwards this eccentric.
    To promote balance in particular, as already indicated, said two groups of other pins 103b, 103c are, in groups, respectively engaged in the axial passages 105 of the ring sector 20 considered. And these passages 105 are themselves engaged with (receive) respectively a first and a second traction fingers 117a, 117b (FIG. 6) pivotally mounted with respect to two arms 107a, 107b of the spreader 107, around an axis Y perpendicular to said radial direction of adjustment R and to said axis X (FIG. 4) along which coaxially extend the annular tab 26, the outer casing 22 and the sectorized annular element considered, here the ring sector 20 in question. Two washers 118a, 118b welded respectively at the ends of the rods 107a, 107b retain along the axis Y the traction fingers 117a, 117b (FIG. 6).
    Furthermore, in the preferred solution presented, said other pins 103b, 103c of each of the two groups are pivotally engaged in the first and second fingers 117a, 117b of respective traction, in order to be able to rotate around respective axes X1, X2 (FIG. 6) each parallel to said axis
    X along which the annular tab 26, the outer casing 22 and the segmented annular element considered extend coaxially.
    Again for the balance of forces, it is provided that the radial tie rod 113 and the lifter 107 can rotate relative to each other about an axis parallel to said radial direction R of adjustment.
    For further possible angular or circumferential catching up of the forces, the two so-called (other) pins 103b, 103c of each group are here each mounted in the passage 105 which receives it also with a circumferential clearance J2; see figure 5.
    And for this same purpose, as well as for an angular setting, it may be preferred that, for at least some of the ring sectors 20, and next to the eccentric lifter 101, another pin 103e extending parallel to said axis X either hired:
    - without play in another passage 106 of the annular tab 26,
    - And, with a radial clearance J3 (FIG. 4), through another orifice 105 of the sectorized annular element, here the ring sector 20 in question.
    In practice, it is recommended that, if this said other piece 103e is provided, as shown in FIGS. 3 and 5, located radially under the eccentric 109 and circumferentially between the two said pieces 103b, 103c of one of said groups of pawns, circumferentially midway between each of them.
    Application of the above solution in the case of a radially positioned connection, adaptable with temperature, between sectors of the outer platform, 48 ′, 66 ′ of blades of a turbine distributor and an annular tab 26 ', is shown in Figure 7.
    As can be seen, the same means or the means ensuring the same functions as those of the embodiment of FIGS. 2 to 5 and applied to the example of FIG. 1 have been identified identically, except for the mark ‘(prime); see items marked 103 ’, 103a’, 103c ’, 105’, 105a ’, 107’, 109 ’, 111’, 119 ’, 47716’.
    The transverse branch which is present in the radially inner part of the radial branches 200a ’, 200b’ can serve as an (part of) outer platform for the distributor vanes 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 200a ', 200b', and the hooks 370, 380 of the annular support 24 of this figure. be by the radial branches 206a ', 206b' of the annular tab 26 ', which annular tab could itself then be a part of the annular support 24.
    Figures 8.9 illustrate the operating principle here, respectively before and after tightening via the eccentric: The segmented annular element considered, such as the ring sectors 20 in the example, is (are) plated (s) ), according to planar supports, on the internal faces 261 a, 261 b of the lugs 260a, 260b situated on said annular legs, here 26 (for fixing to the external casing 22 or for radial positioning of the sectors of the external platform 48,66 d distributor vanes). This is obtained by the clamping force exerted, radially outward, by the eccentric spreader, 101 in the example, in connection with the rotation of the eccentric (109 in the example): Via the rotation of its maneuvering drum, the rotation of the eccentric about its Y axis resulted in the application of the radial force F1 on the lifter. The radial clearance J which existed between the flat bearing surfaces, such as 210a, 210b of the sectored annular element considered, 20, before tightening (FIG. 8) has disappeared; The complementary bearing surfaces 210a, 210b and 260a, 260b are pressed one against the other, two by two, along a contact line marked 262 in figures 8,9. This contact line 262 is situated at the level of the external faces 105a, oblong passages, such as 105, of each sector of the sectorized annular element.
    The definition of the vein 12 is therefore controlled at the level of the contact zones between the ring sectors 20 and the pins.
    The guarantee of maintaining the tightening whatever the thermal conditions is obtained by the alignment along line 262, of the contact zones located:
    on the one hand, at the level of the pins, such as 103, of the spreader with the external faces, such as 105a, oblong passages, such as 105, of each sector of the segmented annular element, and
    - On the other hand, pins 260a, 260b of the legs 26 of the casing with the flat outer zones 5 of the legs or bearing surfaces, such as 200a, 200b, of the sectors.
    Concerning the length differential linked to the different thermal gradients and coefficients of expansion between the two materials in question (metal / CMC in the selected case), it is not significant with respect to the initial tightening above detailed, which is furthermore kept in all phases of flight.
    In addition, the addition of elastic washers 115, in addition to providing an additional degree of rotation on the lifter, makes it possible to compensate for parasitic thermal gradients linked to the various metallic components of the eccentric lifter (101, 101 ') and (legs 26) of the casing. and the non-mastery of the expansion coefficients of the latter.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Set including:
    - an annular outer casing (22) of a gas turbine engine for an aircraft,
    - an annular element segmented 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 ’) for radial positioning comprising at least one annular tab (26,26’) made of a second material having a coefficient of thermal expansion different from that of the first material, for:
    - fix the ring sectors with the outer casing (22), by means of an annular support (24), or
    - radially positioning with respect to said annular lug the sectors of the outer platform (48, 66) of distributor vanes, characterized in that the means (125, 125 ') for radial positioning also comprise an eccentric lifter (101, 101') engaged on one side with said at least one annular tab (26,26 ') and, on the other side, with the segmented annular element, and acting to allow the distance between said at least one annular tab to be radially adjusted ( 26.26 ') and the segmented annular element.
    [2" id="c-fr-0002]
    2. Assembly according to claim 1, in which the eccentric lifter comprises pins (103,103 ', 103b, 103c, 103b', 103c ') mounted with clearance in passages (105,105') of the sectored annular element and is arranged to request support between a portion of outer circumference (103a, 103a ') of at least one said pin and a portion of outer circumference (105a, 105a') of the passage in which said pin is mounted.
    [3" id="c-fr-0003]
    3. The assembly of claim 2, wherein the eccentric spreader (101,101 ') comprises a spreader (107,107') and an eccentric (109,109 '), and is connected to said at least one annular lug via the eccentric including an operating rod (119,119 '), which extends
    5 parallel to an axis along which coaxially extend said at least one annular tab (26,26 ') and the segmented annular element, is engaged without play in a first passage (111) of said at least one annular tab and is maneuverable for adjusting said radial distance, two groups of two so-called pins (103b, 103c, 103b ', 103c') of the spreader, each parallel
    10 to said axis, being mounted with at least one radial clearance in said passages (105,105 ’) of the annular element sectorized circumferentially distant from one another.
    [4" id="c-fr-0004]
    4. The assembly of claim 3, wherein the eccentric lifter comprises
    15 a radial tie rod (113) on which the eccentric acts radially, for a radial adjustment of said two groups of two pins (103b, 103c, 103b ’, 103c’).
    [5" id="c-fr-0005]
    5. Assembly according to any one of the preceding claims, which further comprises elastic return means (115)
    20 in the radial direction which urge the segmented annular element radially towards the said at least one annular tab (26.26 ’).
    [6" id="c-fr-0006]
    6. An assembly according to at least one of claims 3,4, alone or in combination with claim 5, wherein said two groups of two pawns (103b, 103c, 103b ’, 103c’) are, in groups respectively
    25 engaged in the passages (105,105 ') of the sectored annular element, themselves engaged with respectively a first and a second traction fingers (117a, 117b) pivotally mounted with respect to the lifter (107,107') around an axis perpendicular to said radial adjustment direction and to said axis which extend coaxially said at least one annular tab
    30 (26.26 ’) and the segmented ring element.
    [7" id="c-fr-0007]
    7. The assembly of claim 6, wherein said pins of each of the two groups (103b, 103c, 103b ', 103c') are pivotally engaged in the first and second traction fingers (117a, 117b) respectively, to be able to rotate around respective axes parallel to said axis which extend coaxially said at least one annular tab (26,26 ') and the sectorized annular element.
    [8" id="c-fr-0008]
    8. An assembly according to claim 4, alone or in combination, with any one of claims 5 to 7, in which the radial tie rod (113) and the spreader (107,107 ') can rotate relative to each other about an axis parallel to said radial adjustment direction.
    [9" id="c-fr-0009]
    9. The assembly of claim 3, alone or in combination, with any one of claims 4 to 8, wherein the two said pawns of each group (103b, 103c, 103b ', 103c') are each mounted in the passage (105,105 ') which receives it with also a circumferential clearance.
    [10" id="c-fr-0010]
    10. Assembly according to any one of the preceding claims, which further comprises, next to the eccentric lifter (101,101 '), and for an angular setting, another pin (103e) extending parallel to said axis along which s' coaxially extend said at least one annular tab and the sectorized annular element, and engaged:
    - without play in another passage (106) of said at least one annular tab,
    - And, with a radial clearance, through an orifice (105) in the sectored annular element.
    [11" id="c-fr-0011]
    11. An assembly according to claims 3 and 10, alone or in combination with any one of claims 4 to 8, wherein said other pin (103e) is located radially under the eccentric (109,109 ') and circumferentially between said two pawns (103b, 103c, 103b ', 103c') of one of said groups of pawns, halfway between each of them.
    [12" id="c-fr-0012]
    12. Aircraft gas turbine engine comprising the assembly according to any one of the preceding claims.
    类似技术:
    公开号 | 公开日 | 专利标题
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    同族专利:
    公开号 | 公开日
    US11015484B2|2021-05-25|
    GB2565894B|2022-01-12|
    FR3068071B1|2019-11-08|
    GB201810466D0|2018-08-08|
    US20180371948A1|2018-12-27|
    GB2565894A|2019-02-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4127357A|1977-06-24|1978-11-28|General Electric Company|Variable shroud for a turbomachine|
    FR2651830A1|1989-09-08|1991-03-15|Gen Electric|MECHANICAL DEVICE FOR CONTROLLING THE PLAY OF BLADES IN A GAS TURBINE ENGINE.|
    FR2651831A1|1989-09-08|1991-03-15|Gen Electric|DEVICE FOR CONTROLLING THE EXTREMITY OF THE AUBES FOR GAS TURBINE ENGINE.|
    US7922445B1|2008-09-19|2011-04-12|Florida Turbine Technologies, Inc.|Variable inlet guide vane with actuator|
    US20140271147A1|2013-03-14|2014-09-18|Rolls-Royce Corporation|Blade track assembly with turbine tip clearance control|
    FR3036435A1|2015-05-22|2016-11-25|Herakles|TURBINE RING ASSEMBLY|
    FR2591674B1|1985-12-18|1988-02-19|Snecma|DEVICE FOR ADJUSTING THE RADIAL CLEARANCES BETWEEN ROTOR AND STATOR OF A COMPRESSOR|
    US5921749A|1996-10-22|1999-07-13|Siemens Westinghouse Power Corporation|Vane segment support and alignment device|
    DE102006012361A1|2005-03-30|2006-10-05|Alstom Technology Ltd.|Rotary turbomachine e.g. turbine or compressor for e.g. power plant has regulating device, which exhibits driven element which is mounted around first axis of rotation swiveling at external housing|
    FR3033825B1|2015-03-16|2018-09-07|Safran Aircraft Engines|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL|FR3033825B1|2015-03-16|2018-09-07|Safran Aircraft Engines|TURBINE RING ASSEMBLY OF CERAMIC MATRIX COMPOSITE MATERIAL|
    FR3045716B1|2015-12-18|2018-01-26|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITH COLD ELASTIC SUPPORT|
    FR3055146B1|2016-08-19|2020-05-29|Safran Aircraft Engines|TURBINE RING ASSEMBLY|
    FR3056632B1|2016-09-27|2020-06-05|Safran Aircraft Engines|TURBINE RING ASSEMBLY INCLUDING A COOLING AIR DISTRIBUTION ELEMENT|
    DE102017211866A1|2017-07-11|2019-01-17|MTU Aero Engines AG|Guide vane segment with curved relief gap|
    FR3080142B1|2018-04-16|2020-05-01|Safran Aircraft Engines|TURBINE RING ASSEMBLY WITH INTER-SECTOR SEAL|
    US10823002B2|2018-05-15|2020-11-03|General Electric Company|Variable stiffness static structure|
    US11215064B2|2020-03-13|2022-01-04|Raytheon Technologies Corporation|Compact pin attachment for CMC components|
    法律状态:
    2018-12-28| PLSC| Publication of the preliminary search report|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
    FR1755847A|FR3068071B1|2017-06-26|2017-06-26|ASSEMBLY FOR THE PALLET CONNECTION BETWEEN A TURBINE HOUSING AND AN ANNULAR TURBOMACHINE ELEMENT|
    FR1755847|2017-06-26|FR1755847A| FR3068071B1|2017-06-26|2017-06-26|ASSEMBLY FOR THE PALLET CONNECTION BETWEEN A TURBINE HOUSING AND AN ANNULAR TURBOMACHINE ELEMENT|
    US16/018,814| US11015484B2|2017-06-26|2018-06-26|Assembly for a spreader connection between a turbine casing and a turbine engine ring element|
    GB1810466.1A| GB2565894B|2017-06-26|2018-06-26|Assembly for a spreader connection between a turbine casing and a turbine engine ring element|
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