• 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:
    The invention relates to an assembly comprising a turbojet intermediate casing formed of a hub comprising a downstream transverse flange (48) in which is formed at least a first opening (36) communicating the interior of the hub with a duct (46). extending downstream of the flange (48) and opening at its downstream end at a second opening (40) formed in an outer annular shell (68) extending downstream of the hub and intended to internally define an annular space flow of a secondary flow. More particularly, the upstream end of said duct (46) is fixed on the downstream flange (48) of the hub by removable elastic engagement.
    公开号:FR3018548A1
    申请号:FR1452197
    申请日:2014-03-17
    公开日:2015-09-18
    发明作者:Frederic Jacques Eugene Goupil；Noel Joseph Camille Robin；Regis Eugene Henri Servant
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to an aircraft turbojet engine, in particular of the double-flow type. In a double-body turbojet engine, an intermediate casing is usually designated as a casing whose hub is arranged between a low-pressure compressor casing and a high-pressure compressor casing. The present invention more particularly relates to the assembly of an air discharge duct associated with a discharge valve, of the type sometimes designated by the acronym VBV (Variable Bleed Valve), on an intermediate casing hub in a aircraft turbojet engine. Conventionally, a turbofan engine 10, as shown in FIG. 1 in a partial diagrammatic view in axial section, consists of a gas turbine 12 having an axis 14 driving a ducted fan 16, or fan, the latter being generally placed upstream (AM) of the engine. The mass of air sucked by the engine is divided into a primary air flow (arrow A), which flows in the gas turbine or primary body, and a secondary air flow (arrow B), which comes from the blower 16 and surrounding the primary body, the primary and secondary air streams being concentric.
    [0002] In a well known manner, the primary air flow (arrow A) is generally compressed by a first compressor 18, said low pressure (BP) or booster, the BP shaft is connected to the shaft of the fan 14 and driven in rotation by the shaft of a downstream low pressure turbine (not shown), then in a second downstream compressor (AV), said high pressure (HP), whose HP shaft is rotated by the shaft of a high pressure turbine arranged at the outlet of a combustion chamber and upstream of the low pressure turbine (not shown). In such a double-body turbojet engine, an intermediate casing 22 is usually designated a casing whose hub is arranged between a casing 24 of the low-pressure compressor 18 and a casing 26 of the high-pressure compressor 20. The intermediate casing 22 comprises a hub formed of an inner annular wall 28 externally defining the annular flow vein of the primary air flow between the low-pressure compressor 18 and the high-pressure compressor 20 and an outer annular wall 30 internally defining the annular flow vein 33 of the flow of secondary air. Moreover, such a turbojet engine is generally equipped with devices called discharge valves 32 or VBV (for Variable Bleed Valve, in English), which make it possible to return part of the primary air flow, at the output of the compressor BP 18, in the annular channel 33 of the secondary air flow. This discharge has the effect, by lowering the pressure downstream of the compressor BP 18, to lower the operating point thereof and to reduce the risks of pumping the compressor 18, 20 consisting of a sudden inversion of the flow. the flow of hot gases from the combustion chamber, which can damage the compressor 18, 20. In addition, in the event of accidental water penetration, especially in the form of rain or hail, or of various debris, which are liable to impede the operation of the turbojet engine, these valves make it possible to recover this water or these debris and to eject them outside the primary vein supplying air to the combustion chamber. Thus, the discharge valves 32 are formed in the inner annular shell 30 of the hub of the intermediate casing 22 and communicate with a space between the inner annular shell 28 and the outer shell 30 of the intermediate casing 22. To allow the discharge of air the hub of the intermediate casing 22 comprises a downstream transverse flange 34 arranged upstream of the high-pressure compressor 20 of the turbojet engine and mutually connecting the downstream ends of the inner annular and outer annular ferrules 30. The downstream flange 34 comprises a plurality of first openings 36 distributed around the axis 14 of the turbojet engine 10 and communicating each upstream with the interior of the hub and downstream with a pipe 38 whose downstream end opens at a second opening 40 of an outer annular shell 42 formed in the downstream extension of the outer annular wall 30 of the intermediate casing 22. As represented in FIG. 1, the hub of the intermediate casing Fig. 22 carries stator vanes 44 for straightening the secondary air stream from the upstream fan 16. Typically, the discharge conduits 38 are bolted to the downstream flange 34 of the hub of the intermediate housing 22 and then to the outer shell 42 downstream of the intermediate casing 22 is mounted around the downstream ends of the ducts 38 which are also fixed by bolting on the internal face of the outer shell 42. In the case of a large-diameter turbojet engine, this type of duct assembly discharge 38 is simple to perform. However, in the case of engines of smaller diameter, the reduced space requirement downstream of the downstream flange 34 does not allow to carry out a prefixing by bolting the upstream ends of the discharge ducts 38 on the flange 34 of the hub of the intermediate casing 22. This limited space is mainly due to the need to circulate easements, such as cables in particular. Therefore, it is then necessary to assemble the ducts 38 and the outer shell 42 simultaneously, which is complicated and long to achieve by a limited number of operators during a maintenance operation.
    [0003] The invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid at least partly the aforementioned drawbacks. The invention proposes for this purpose, an assembly comprising an intermediate casing for a turbomachine comprising a hub provided with a downstream transverse flange 30 in which is formed at least a first opening communicating the interior of the hub with a duct extending in downstream end of the flange and opening at its downstream end at a second opening formed in an outer annular shell extending downstream of the hub, said ferrule being intended to internally define an annular flow space of a secondary flow, characterized in that the upstream end of said duct is fixed on the downstream flange of the hub by removable elastic coupling. According to the invention, the attachment of the upstream end of the discharge duct to the hub of the intermediate casing by a connection with removable elastic engagement allows for a pre-assembly of the duct before mounting the outer annular shell. In addition, the maintaining in position of the duct by its upstream fixing to the hub to the intermediate casing makes it possible, during a maintenance operation, to reduce the immobilization time of the turbojet engine and thus allows assembly / disassembly within a limited time under wing. some other turbojet equipment.
    [0004] In addition, the proposed arrangement provides a more flexible connection of the discharge conduit with the downstream flange of the hub than in the prior art, thereby reducing the static stresses in operation applied to the conduit. According to another characteristic of the invention, the downstream end of the duct is fixed by removable rigid assembly, for example by screwing, to the outer annular shell. The combination of an assembly of the discharge duct by elastic coupling upstream and a rigid assembly downstream avoids a hyperstatic assembly of the conduit between the hub and the shell, increasing its service life. The term "rigid assembly" here must be understood as defining a connection that is made without elastic deformation does not help the assembly. Preferably, the assembly comprises at least one first member integral with the downstream flange and extending downstream thereof and a second member integral with the upstream end portion of the duct, the first member and the second member being arranged at the outside of the duct and cooperating together by removable elastic casing. In a first embodiment of the invention, the first member comprises a first radial planar portion fixed on a radial annular flange of the outer periphery of the downstream flange by means of the fastening elements for securing the downstream ends of an annular row of radial stator vanes formed around the hub of the intermediate casing. It is thus possible to fix the first member to the hub without adding a new independent fastening element that may complicate the assembly of the turbojet engine. The first member may comprise a second portion extending downstream from the first portion and having an elastically deformable portion cooperating by elastic deformation with the second member for the removable elastic engagement.
    [0005] To achieve the fixation of the first member on the second member, the elastically deformable portion comprises a lamella of which a portion is bent on itself and is engaged by elastic deformation in an orifice of a radial ear of the conduit forming the second member, of in order to ensure axial and radial retention of the second member on the first member. The second member may also comprise a rod extending substantially radially from an outer surface of the duct and which is intended to be guided to move upstream in an axial notch of the elastically deformable portion, the notch having a predetermined width of in order to elastically pinch the rod during the downstream movement of the conduit. According to yet another characteristic of the invention, the notch opens at its upstream end in a tubular housing of diameter greater than that of the cylindrical rod.
    [0006] The elastically deformable portion may also be an insert and fitted downstream on the free end of the second part of the first member, the notch of said insert cooperating with a corresponding notch of the free end of the second part of the first organ. The first member may also be a one-piece elastically deformable piece. The elastically deformable portion may also be formed by a lyre collar cooperating with a rod extending substantially radially from an outer surface of the conduit. According to another characteristic of the invention, the assembly comprises means for immobilizing in rotation the first member on the downstream flange, in order to allow an angular retention of the first member on the flange during the elastic engagement with the second member of the discharge duct. Preferably, the radially outer end of the rod 15 comprises a protrusion, for example spherical, shaped and dimensioned so as to ensure a radial stop inward of the second member on the first member. In another embodiment of the invention, the first member is a rod extending substantially along the axis of the hub from the downstream face of the downstream flange and cooperating by elastic engagement with an orifice of an elastically deformable part carried by a support leg extending from outside the conduit. Finally, the invention also relates to a turbomachine, such as a turbofan engine comprising at least one assembly of the type 25 described above. The invention will be better understood and other details, advantages and characteristics of the invention will become apparent on reading the following description given by way of nonlimiting example, with reference to the appended drawings, in which: FIG. already described, is a schematic half-view in axial section of an aircraft turbojet of a known type; Figure 2 is a schematic axial sectional view of an assembly of a discharge duct assembled to an intermediate housing hub according to the invention; Figures 3 to 6 are schematic perspective views of a first embodiment of the invention; Figures 7 to 9 are schematic perspective views of a second embodiment of the invention; Figures 10 and 11 are schematic perspective views of a third embodiment of the invention; Figures 12 and 13 are schematic perspective views of a fourth embodiment of the invention; Figures 14 to 16 are schematic perspective views of a fifth embodiment of the invention. FIG. 2 more particularly illustrates a discharge duct 46 according to the invention intended to be fixed at its upstream end by removable elastic engagement with a downstream flange 48 of a hub 49 of intermediate casing. The removable elastic locking means are not shown in this figure and several assembly variants will be described with reference to FIGS. 3 to 16.
    [0007] The downstream flange 48 of the hub of the intermediate casing comprises an external radial annular flange 50 interposed between a radial annular rim 52 upstream of an annular angle 54 and radial tabs 56 of stator blades, known by the acronym of OGV. , for Outlet Guide Vane, externally surrounding the hub 49 of the intermediate casing.
    [0008] The radial lugs 56 of the stator vanes, the annular flange 50 of the downstream flange 48 and the radial annular flange 52 of the bracket 54 comprise orifices aligned with each other for fixing together by screw / nut systems of said elements, the screw 55 being visible in Figures 5, 6, 10, 11 and 12 commented later and the nuts being for example riveted nuts on the upstream face of the lugs 56 of the stator vanes so that it is the screws which are rotated and not the nuts to tighten the screw / nut system. Alternatively, the hub formed integrally with the downstream flange 48 may also be formed integrally with the annular angle 54. This assembly may for example be obtained from foundry. Each radial lug 56 of a stator vane extends radially inwardly from a platform 58 from which extends radially outward a blade 60. The stator vanes are arranged circumferentially side by side so as to the circumferential ends of the platforms 58 are in contact and together form an inner annular envelope internally defining the flow vein of the secondary air flow. The annular angle 54 comprises a cylindrical wall 62 which is connected at its upstream end to the annular rim 52 and which carries externally an annular rib 64 housed in an annular groove 66 of the annular ferrule 68. The downstream ends of the platforms 58 aligned circumferentially are arranged in contact with the upstream end of the outer annular ferrule 68 so as to ensure continuity of the internally delimiting walls of the annular flow channel of the secondary air flow. In practice, the outer annular shell 68 is formed of several circumferentially end-to-end sectors, some of which comprise an opening 40, as described with reference to FIG. 1, communicating with the downstream end of a discharge duct 46.
    [0009] Each discharge duct 46 comprises at its upstream end an annular flange 70 applied on the periphery of an orifice of the downstream flange 48 to seal. The downstream end of the conduit 46 also comprises a peripheral flange 72 having tapped orifices 74 aligned with corresponding orifices 76 of the annular ferrule 68 so as to make a screw fastening.
    [0010] In the various embodiments of the invention described below, the upstream end of the duct 46 is fixed to the downstream flange 48 by removable elastic casing which can take several varied forms covered by the invention. In particular, in the embodiments shown, the casing is made by means of two independent members one of the other one of which is integral with the downstream flange 48 or the discharge duct 46 and the other is secured to the downstream flange 48 or discharge duct 46. Of course, the invention is not limited to the embodiments described and covers any type of elastic engagement between the downstream flange 48 and the discharge duct 46. In a first embodiment of the invention described with reference to Figures 3 to 6, the first member 78 has a generally L-shaped formed of a first portion 80 and a second portion 82. The first portion 80 is formed by a wall transverse to the axis 14 (Figure 1), substantially planar square comprising an orifice 84 located approximately in the center of the wall for the passage of a fixing screw on the annular flange 52 of the annular angle 54 (Figures 3 and 4). The screw used is advantageously one of the screws used for fixing a downstream tab 56 of a stator vane (OGV). The second portion 82 has a generally rectangular general shape defining a tongue extending downstream. A bulge 86 is formed at the junction of the first portion 80 and the second portion 82 so as to have a convexly curved shape inwardly of the L-shape and concave outwardly of the L shape. 86 is intended to increase the mechanical resistance to deformation of the first member 78. The first portion 80 also comprises two radial grooves 88 substantially parallel to each other and opening at the radially inner end of the first portion 80. These grooves delimit two lateral tabs 90 whose radially internal ends 92 are bent in a direction opposite to the second part 82, that is to say upstream when the first member 78 is mounted on the hub 49 of the intermediate casing . As shown in FIGS. 5 and 6, the curved ends 92 come into contact with the inner periphery of the annular flange 52 of the annular angle 54 in order to lock the first member 78 in rotation on the annular angle 54.
    [0011] The downstream end portion of the second portion 82 of the first member 78 comprises on its outer face (oriented radially outwardly relative to the axis 14) a recess 94 with a flat bottom whose contour is generally of substantially rectangular shape . A lamella 96, made for example of metallic material, is mounted in the recess of the second part.
    [0012] This plate 96 comprises at its end opposite the first portion 80 a bent portion 98 upstream so as to form an elastically deformable portion. The strip 96 comprises an orifice 100 aligned with an orifice 102 formed in the recess of the second part 82 and in which orifices a screw 104 is inserted and receives at its free end a nut 106. Thus, the strip 96 is locked on the second portion 82 of the first member 78. A workpiece 108 is force-fitted around the second portion 82 and the portion of the lamella not comprising the curved portion 98 and is dimensioned so that it abuts against the upstream on two lateral faces 110 substantially parallel to the first portion 80. This piece 108 is previously mounted around the second portion 82 before the positioning of the strip 96. The first member 78 is intended to cooperate with a second member 112 which is in this first embodiment of the invention a radial lug formed on the outer face of the duct 46. This lug 112 comprises an orifice 114 whose shape and dimension are determined so as to allow a resiliently fitting assembly of the bent portion 98 of the strip 96 in the ear when the conduit is moved downstream in its mounting position. After assembly, it is understood that the bent portion 98 resumes its original shape and its upstream end is thus arranged in axial relation with an edge of the lug 112 so as to axially retain the duct 46 on the downstream flange 48 The first member 78 is made of a weakly deformable material, such as titanium. The part 108 is advantageously made of a non-metallic material, preferably an elastomer, in order to limit the effects of friction between the first member 78 made of metallic material and the radial lug 112 also made of metallic material (for example titanium). FIGS. 7 to 9 show a second embodiment of an interlocking assembly in which the first member 116 comprises a first portion 80 which is identical to the first portion 80 described with reference to the first member 78 described with reference to FIGS. The second part 120 is however different and comprises an axial and radial notch opening at its downstream end. A block of elastically deformable material 122, for example made of elastomeric material, is fitted on the downstream end of the second portion 120 and comprises a median portion 124 delimiting a notch 126 and connecting a so-called upper portion 128 to come s' apply on the outer surface of the second portion 120 and a so-called lower portion 130 intended to be applied on the inner surface of the second portion 120. The shape and dimensions of the middle portion 124 of the elastic block 122 are determined from in order to ensure a tight fitting thereof in the notch of the second part 120. Similarly, the spacing between the said upper part 128 and the so-called lower part 130 is provided to allow tight fitting of these parts on the second portion 120 of the first member 116. Alternatively, the block of material can be secured to the second portion 120 by gluing or riveting. An assembly can also be made by a spacing between the lower 130 and upper 128 parts so as to clamp the second portion 120.
    [0013] The upstream end of the notch 126 of the material block 122 opens into a tubular housing 132 of axis substantially perpendicular to the second portion of planar shape. In this second embodiment, the second member 134 is a rod secured to the conduit by screwing into an outgrowth 136 of the outer surface of the conduit. The radially outer end of the rod 134 carries a spherical portion 138 whose diameter is greater than the diameter of the tubular housing 132 so that the spherical portion 138 comes into contact with the block of material 122 and thus radially maintains the conduit 46 relative to the flange 48. When the discharge duct 46 is fitted elastically at its upstream end to the downstream flange 48 and then fixed at its downstream end by screwing on the annular shell 68, the rod 134 is then only slightly constrained by the elastic block 122 since the rod is not tight in the housing.
    [0014] The width of the notch 126 is smaller than the diameter of the rod 134 so that the median portion 124 of the material block 122 pinches the rod 134 as the discharge conduit 46 moves towards the downstream flange 48 In a third embodiment of the invention shown in Figures 10 and 11, the second member 134 is identical to that described with reference to Figures 7 to 9 and the first member 140 is an elastically deformable monobloc piece, for example elastomer. The first member 140 of general L shape also comprises a first portion 142 having a passage hole of a fixing screw on the annular flange 52 of the angle 54 and a second portion 144 substantially perpendicular to the first portion 142 and s' extending downstream from the radially inner end of the first portion 142. The pinch notch 146 of the rod 134 and the tubular housing 132 are directly formed in the thickness of the second portion 144. The mounting principle is identical to that described with reference to FIGS. 7 to 9.
    [0015] In this embodiment a metal washer 148 is integrated with the first portion 142 and around the orifice so as to serve as a bearing surface to the head of the fixing screw on the annular angle 54. In a fourth embodiment of the invention shown in Figures 12 and 13, the second member 134 is also identical to that described with reference to Figures 7 to 9, only the first member 150 is different. In this embodiment, the first member 150 comprises a support piece 151 of a lyre collar 152 intended to receive by elastic engagement the rod 134 of the duct 46. The support 151 comprises a first radial wall 154 having an orifice 155 for passing a fixing screw on the annular angle 54, connected to a downstream end to a second wall 156 extending downstream and substantially perpendicular to the first wall 154, itself connected to a third wall 158 extending in one direction circumferentially opposed to the first wall 154. This third wall 158 bears on its face facing downstream the lyre collar 152 formed of two arms 160 extending vis-à-vis one of the other from the third wall 158 and connected to one another by a transverse wall 162 fixed, for example by screwing, on the third wall 162 of the support 150. The arms 160 each comprise two cylindrical portions 164 arranged with respect to the other so that their concave faces are oriented towards each other and together define a tubular receiving zone of the rod 134. The cylinder portions 164 each have a generatrix of the same axis and are connected to their end opposite the transverse wall 162 to a guide wall 166. The two guide walls 166 diverge relative to each other away from the third wall 162 so as to form a guide zone of the rod 134 when moving between the two arms 164 of the lyre collar 152. The lyre collar 152 may be made of high alloyed steel, that is to say comprising at least one additive element exceeds 5% by mass. Other forms of lyre collar can be used, without departing from the scope of the invention, provided that they are adapted to the elastic insertion of a second member. In this embodiment, the locking in rotation of the first member 150 on the angle 54 is made by pressing the upper edge 151 of the support 150 on the radially inner face 153 of the cylindrical wall 62 of the angle 54 as well as by a pin 157 s' extending axially upstream intended to come into contact with the inner periphery of the annular flange 52 of the annular bracket 54 (Figures 2, 12 and 13). The lug is offset away from the second wall 156 relative to a plane passing through the axis 159 of the orifice 155 and substantially parallel to the second wall 156. In this way, when an observer looks towards the upstream, the lug 157 ensures a locking in rotation of the first member 150 in the counterclockwise direction, and the upper edge 151 ensures a rotational locking of the first member 150 in the clockwise direction. The anti-clockwise direction may correspond to the tightening direction of the screw 55 and counter-clockwise to its loosening. In another possible embodiment of the invention, the first member 150 may not include a lug and be shaped so that the upper edge provides an anti-rotation screwing the screw 55. Although not shown, the radially outer end of the rod 134 may carry a spherical portion 138 as described with reference to Figures 7, 10 and 11. In a final embodiment of the invention shown in Figures 14 to 16, the elastically deformable portion is here borne by the second member 170 secured to the duct 46.
    [0016] To this end, the upstream end of the duct 46 comprises at least one lug extending substantially radially from an outer surface of the duct. In the example shown, the duct comprises two lugs 170, 172 one extending, with respect to the axis of the turbomachine, circumferentially 170 and the other extending, with respect to the axis of the turbomachine , radially inward. The upstream end of the duct here in section, in a plane perpendicular to the axis of the turbomachine4, a substantially rectangular shape. In the following, only the first 174 and second 170 fixing members of the tab 170 will be described although in all respects identical to the tab 172. The first member 174 is here a rod whose upstream end is screwed into a boss 176 of the downstream flange 48. This first member 174 comprises a substantially cylindrical median portion 178 and a convexly bulging portion 180 arranged immediately downstream of the middle portion 178 and ending downstream at the free end of the rod 174 by a conical portion 180 with decreasing section downstream. The second member 170 carries an elastically deformable member 182, for example elastomer, having a passage opening of the rod 174. This elastic piece 182 is formed by an elastic ring having an annular groove 184 external peripheral cooperating with the inner edge of the The orifice of the lug 170. The elasticity of the piece 182 allows it to be forced into the opening of the lug 170. The duct 46 is thus mounted by aligning the orifice of each elastic piece 182 with a rod 174. of the downstream flange 48. An elastic casing is then made by means of the convex portion 180 whose outer maximum diameter is greater than the internal diameter of the orifice of the elastic part 182. The duct 46 is engaged until the portion median 178 of the rod 174 is housed in the orifice of the elastic piece 182.
    [0017] Thus, in the various embodiments of the invention, the assembly of a discharge duct 46 with the flange is made by elastic engagement on the downstream flange 48, which allows a simple and fast assembly thereof on the hub intermediate casing without constraining it too strongly. During disassembly, the sectors of the ring ferrule 68 are disassembled and the ducts are thus held radially by the upstream elastic coupling of the duct on the flange 48, which simplifies the maintenance operations and reduces the immobilization time of the turbomachine . Note that the embodiments according to Figures 3 to 13 have the advantage of not requiring any modification of the hub of the intermediate housing which is a piece obtained from foundry and whose shape changes are very expensive. In the embodiments shown in Figures 3 to 13, only a first member 78, 140, 150 and a second member 112, 134 have been shown and described. It will be understood, however, that the conduit may be secured by means of more than one first organ and a second organ.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. Assembly comprising an intermediate casing for a turbomachine comprising a hub provided with a downstream transverse flange (48) in which is formed at least a first opening (36) communicating the interior of the hub with a duct (46) extending downstream flange (48) and opening at its downstream end at a second opening (40) formed in an outer annular shell (68) extending downstream of the hub, said ferrule (68) being intended to internally delimit a space annular flow of a secondary flow, characterized in that the upstream end of said duct (46) is fixed on the downstream flange (48) of the hub by removable elastic sleeve.
    [0002]
    2. The assembly of claim 1, characterized in that the downstream end of the conduit (46) is fixed by removable rigid connection, for example by screwing, to the outer annular shell (68).
    [0003]
    3. An assembly according to claim 1 or 2, characterized in that it comprises at least a first integral member (78, 116, 140, 150, 178) of the downstream flange and extending downstream thereof and a second member (112, 134, 170) integral with the upstream end portion of the conduit (46), the first member (78, 116, 140, 150, 178) and the second member (112, 134, 170) being disposed at the outside of the duct (46) and cooperating together by removable elastic casing.
    [0004]
    4. The assembly of claim 3, characterized in that the first member (78, 116, 140, 150) comprises a first radial planar portion (80, 142, 154) fixed on a radial annular flange (50) of the outer periphery. the downstream flange (48) by means of fasteners for securing the downstream ends of an annular row of radial stator vanes (44) formed around the hub of the intermediate casing.
    [0005]
    An assembly according to claim 4, characterized in that the first member (78, 116, 140, 150) comprises a second portion (82, 120, 144, 156) extending downstream from the first portion (80, 150, 144, 156) extending , 142, 154) andcomprising an elastically deformable portion (98, 122, 152) cooperating by elastic deformation with the second member (112, 134) for the removable elastic engagement.
    [0006]
    6. The assembly of claim 5, characterized in that the elastically deformable portion comprises a strip (96), a portion of which is bent (98) on itself and is engaged by elastic deformation in an orifice (114) of an ear radially of the conduit (46) forming the second member (112) to provide axial and radial retention of the second member (112) on the first member (78).
    [0007]
    7. The assembly of claim 5, characterized in that the second member (134) comprises a rod extending substantially radially from an outer surface of the duct and intended to be guided upstream in a notch (126, 146 ) of the elastically deformable portion, the notch (126, 146) having a width determined so as to elastically pinch the rod (134) during the downstream displacement of the conduit (46).
    [0008]
    8. An assembly according to claim 7, characterized in that the notch (126, 146) opens at its upstream end in a housing (132) tubular diameter greater than that of the rod (134) cylindrical.
    [0009]
    9. An assembly according to claim 7 or 8, characterized in that the elastically deformable portion (122) is an insert and fitted from downstream on the free end of the second portion (120) of the first member (116), the notch of said insert (126) cooperating with a corresponding notch of the free end of the second portion (120) of the first member (116).
    [0010]
    10. The assembly of claim 7 or 8, characterized in that the first member (140) is an elastically deformable monobloc piece.
    [0011]
    11. The assembly of claim 5, characterized in that the elastically deformable portion is a lyre collar (152) cooperating with a rod (134) extending substantially radially from an outer surface of the duct (46).
    [0012]
    12. An assembly according to one of claims 7 to 11, characterized in that the radially outer end of the rod (134) carries a protrusion, for example spherical (138), shaped and dimensioned so as to provide a radial abutment towards the interior of the second member (134) on the first member (140).
    [0013]
    13. Assembly according to one of claims 4 to 11, characterized in that it comprises locking means for locking in rotation the first member (78, 116, 140, 150) on the downstream flange (48).
    [0014]
    14. An assembly according to one of claims 1 to 3, characterized in that the first member (174) is a rod extending substantially along the axis of the hub from a downstream face of the downstream flange (48) and cooperating by interlocking resilient member with an elastically deformable piece port carried by a bracket (170, 172) extending from the outside of the conduit (46).
    [0015]
    15. Turbomachine, such as a turbojet engine, characterized in that it comprises at least one assembly according to one of the preceding claims.
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    US10330020B2|2019-06-25|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB2406609A|2003-10-01|2005-04-06|Rolls Royce Plc|Retaining device comprising resilient members with arcuate portions|
    EP1584794A1|2004-04-09|2005-10-12|Snecma|Axial retention device for the blades in a disk of a turbomachine rotor|
    US20060242964A1|2005-04-28|2006-11-02|Siemens Westinghouse Power Corp.|Gas turbine combustor barrier structures for spring clips|
    WO2011117560A2|2010-03-26|2011-09-29|Snecma|Turbojet venting pipe, method for mounting one such pipe and turbojet provided with one such pipe|
    FR2961251A1|2010-06-15|2011-12-16|Snecma|Hub for use in intermediate casing of e.g. ducted-fan turbine engine of aircraft, has flange including air outlet orifices formed downstream from bleed valves, and deflectors permitting guiding of air between inlet and outlet orifices|
    WO2013163554A1|2012-04-27|2013-10-31|General Electric Company|Retaining clip, turbine frame, and method of limiting radial movement|FR3094755A1|2019-04-03|2020-10-09|Safran Aircraft Engines|Intermediate casing carrying removable panels fitted with retaining members|US5048286A|1990-06-29|1991-09-17|General Electric Company|Bypass valve door|
    US7475532B2|2005-08-29|2009-01-13|General Electric Company|Valve assembly for a gas turbine engine|
    FR3012846B1|2013-11-07|2015-12-25|Snecma|INTERMEDIATE CASTER HUB FOR AIRCRAFT TURBOJET AIRBORNE COMPRISING A DEFORMABLE CONDUIT OF AIR AND DEBRIS CANALIZATION|US20140338360A1|2012-09-21|2014-11-20|United Technologies Corporation|Bleed port ribs for turbomachine case|
    EP3208431B1|2016-02-16|2022-01-05|MTU Aero Engines AG|Connection assembly for housing element of a turbine center frame|
    US10865819B2|2016-05-20|2020-12-15|Yazaki North America, Inc.|Tuneless cantilever system|
    US10774788B2|2016-06-28|2020-09-15|Raytheon Technologies Corporation|Particle extraction system for a gas turbine engine|
    FR3101616B1|2019-10-03|2021-09-17|Airbus Operations Sas|Method and device for installing a fitting for positioning a fan cowl.|
    法律状态:
    2015-03-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-24| PLFP| Fee payment|Year of fee payment: 3 |
    2017-03-15| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 8 |
    2022-02-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1452197A|FR3018548B1|2014-03-17|2014-03-17|TURBOREACTOR CONDUIT OF DISCHARGE|FR1452197A| FR3018548B1|2014-03-17|2014-03-17|TURBOREACTOR CONDUIT OF DISCHARGE|
    GB1504406.8A| GB2525492B|2014-03-17|2015-03-16|A turbojet with a discharge duct|
    US14/660,170| US10330020B2|2014-03-17|2015-03-17|Turbojet with a discharge duct|
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