Bypass turbomachine

Abstract

The invention relates to an assembly for a turbomachine with a longitudinal axis comprising a first annular wall (24), panels (38) being arranged around the longitudinal axis (A) and extending radially opposite said first annular wall (24) so as to form a flow surface for a flow of air, each panel (38) being secured to the first annular wall (24) by at least one fixing member (72) passing through an orifice in the panel (38) and secured to the first annular wall (24) by means of a sleeve and a stud forming a spacer.

Claims

1. An assembly for a turbomachine (10) of longitudinal axis (A) comprising a first annular wall (24), panels (38) being arranged around the longitudinal axis (A) and extending radially opposite said first annular wall (24) so as to form a flow surface for a flow of air, each panel (38) being fixed to the first annular wall (24) by at least one fixing member (72) passing through an orifice (64) in the panel (38) and fixed to the first annular wall (24), characterized in that a bushing (60) is inserted in each orifice (64) and comprises a first annular end portion (74) applied to a face (66a) of the periphery of the orifice (64) opposite the first annular wall (24), the fixing member (72) clamping said first annular end portion (74) of the bushing (60) to the periphery of the orifice (64), a stud (62) forming a spacer surrounding the bushing (60) and being clamped radially between the periphery of the orifice (64) and the first annular wall (24), in which each first annular portion of the bushing (60) forms a frustoconical skirt (78) applied to a frustoconical part (66) of the periphery of the orifice (64) of the panel (38).

2. The assembly according to claim 1, wherein each bushing (60) comprises a second annular end portion (76) opposite the first annular end portion (74) and arranged radially opposite a corresponding surface (84) of the stud (62) for retaining the stud (62) on the panel (38).

3. The assembly according to claim 2, wherein the bushing (60) comprises a cylindrical portion (82) for joining the first annular end portion (74) and the second annular end portion (76).

4. The assembly according to claim 2, in which each first annular portion (74) of the bushing (60) forms a frustoconical skirt (78) applied to a frustoconical part (66) of the periphery of the orifice (64) of the panel (38).

5. The assembly according to claim 3, in which each first annular portion (74) of the bushing (60) forms a frustoconical skirt (78) applied to a frustoconical part (66) of the periphery of the orifice (64) of the panel (38).

6. The assembly according to claim 1, in which the frustoconical part (66) of the periphery of the orifice (64) of the panel (38) is extended by a cylindrical annular rim (68) whose free end is arranged at a distance from the stud (62), the frustoconical part (66) of the periphery of the panel (38) being clamped between the first annular end part (74) of the bushing (60) and the stud (62).

7. The assembly according to claim 1, in which the first annular end portion (74) and the second annular end portion (76) of the bushing (60) form frustoconical skirts (78, 80).

8. The assembly according to claim 2, in which the first annular end portion (74) and the second annular end portion (76) of the bushing (60) form frustoconical skirts (78, 80).

9. The assembly according to claim 3, in which the first annular end portion (74) and the second annular end portion (76) of the bushing (60) form frustoconical skirts (78, 80).

10. The assembly according to claim 1, in which the first annular end portion (74) and the second annular end portion (76) of the bushing (60) form frustoconical skirts (78, 80).

11. The assembly according to claim 6, in which the first annular end portion (74) and the second annular end portion (76) of the bushing (60) form frustoconical skirts (78, 80).

12. The assembly according to claim 1, in which the bushing (60) and the stud (62) are mounted with a play in radial translation relative to the panel, this play being of the order of a tenth of a millimeter.

13. The assembly according to claim 2, in which the bushing (60) and the stud (62) are mounted with a play in radial translation relative to the panel, this play being of the order of a tenth of a millimeter.

14. The assembly according to claim 3, in which the bushing (60) and the stud (62) are mounted with a play in radial translation relative to the panel, this play being of the order of a tenth of a millimeter.

15. The assembly according to claim 1, in which the bushing (60) and the stud (62) are mounted with a play in radial translation relative to the panel, this play being of the order of a tenth of a millimeter.

16. The assembly according to claim 1, wherein the panels (38) are made of a composite material comprising carbon fibers embedded in a thermosetting matrix.

17. The assembly according to claim 1, in which it comprises an annular shroud (22) formed by the first annular wall (24) arranged downstream of a second annular wall (26) and connected to the latter by a radial annular step (30), each panel (38) being arranged around the longitudinal axis (A) and extending in the downstream extension of the second upstream annular wall (26) of the annular shroud (22) so as to delimit a flow surface for an annular air flow.

18. A bypass turbomachine (10) comprising an assembly according to claim 17, in which the second annular wall (26) carries radially outwardly extending stator vanes (28), the first annular wall (24) being fixed to an intermediate casing (16) to which the downstream end of each panel (38) is also fixed, the second annular wall (26) and the panels (38) delimiting radially inwardly an annular flow path (20) for a secondary air flow.

19. A turbomachine (10) according to claim 18, wherein each panel (38) is arranged circumferentially between radial arms (40) of the intermediate casing (16).

Description

BRIEF DESCRIPTION OF THE FIGURES

(1) FIG. 1, already described previously, is a schematic axial section view of the upstream part of a turbomachine;

(2) FIG. 2, already described earlier, is a larger scale view of the area delineated by the dotted line in FIG. 1;

(3) FIG. 3 is a schematic perspective view of a set according to the invention;

(4) FIG. 4 is a schematic cross-sectional view of the attachment of a panel to a first annular wall as shown in FIG. 3, with the fastener not visible;

(5) FIG. 5 is a schematic cross-sectional view of the attachment of a panel to a first annular wall as shown in FIG. 3, with the fastener visible;

(6) FIG. 6 is a schematic cross-sectional perspective view similar to FIG. 4;

(7) FIG. 7 is a schematic sectional view of a bushing mounted on a panel in an assembly according to the invention, the bushing being crimped on the stud;

(8) FIG. 8 is a schematic sectional view of a bushing mounted on a panel in an assembly according to the invention, the bushing not being crimped on the stud.

DETAILED DESCRIPTION

(9) First of all, we refer to FIG. 3 which represents an assembly according to the invention intended to be mounted in a turbomachine 10. More specifically, FIG. 3 represents an intermediate casing 16 which is a structural part of the turbomachine 10 and is used to transmit the thrust forces from the turbomachine 10 to the aircraft via a pylon.

(10) This intermediate casing 16 comprises an inner annular shroud (not shown) from which extend radial arms 40 connected at their radially outer ends to an outer annular shroud 52. In practice, the inner annular shroud is covered externally by panels 38 each circumferentially interposed between two radial arms 40 of intermediate casing 16. Each panel 38 has openings or slots 54 formed in its downstream part for the passage of air from the annular primary air stream, which is well known to the skilled person in the art.

(11) An upstream annular shroud 22 allows the support of stator blades 28 used to straighten the air exiting an upstream fan 12 as described in reference to FIG. 1. This annular shroud 22 comprises a first downstream annular wall 24 connected to a second upstream annular wall 26 by a radial annular step 30. The second upstream annular wall 26 comprises openings 56 oblong in longitudinal direction A and each crossed by a baseplate 58 for fixing a stator vane 28 for straightening the air flow. The downstream end of the first annular downstream wall 24 is bolted 34 to the inner annular shroud of the intermediate casing 16.

(12) As can be seen in FIGS. 4 and 5, the upstream end of each panel 38 is attached to the first annular wall 24 of the upstream annular shroud 22 and extends in the downstream extension of the second annular wall 26 to reconstitute a radially inner annular flow surface of a secondary air stream.

(13) For this purpose, it is necessary that each panel 38 is arranged at a predetermined distance from the first annular wall 24. This can be difficult to achieve when the panels are made of carbon fiber composite material embedded in a thermosetting resin matrix, such as epoxy.

(14) The invention proposes to fix each panel 38 to the first radial annular wall 24 by means of a bushing 60 and a stud 62 arranged according to a specific configuration so as to have a good transmission of forces.

(15) Thus, each panel 38 comprises a plurality of holes 64 whose periphery has a part of substantially frustoconical shape 66 flared radially outward and extending at its radially inner end by a cylindrical annular rim of substantially radial axis 68. The frustoconical part 66 of the periphery of the hole 64 makes it possible to accommodate the head 70 of a fastening device 72 such as a screw 48 so that the latter does not protrude into the annular secondary air stream 20.

(16) An intermediate bushing 60 is mounted in each hole 64 and comprises a first annular end portion 74 arranged at a radially outer end of the bushing 60 and a second annular end portion 76 arranged opposite the first annular end portion 74 and thus arranged in position in the turbomachine radially at the inner end of the bushing 60. The first annular end portion 74 and the second annular end portion 76 present in the embodiment represented in FIGS. 4 to 8 the shape of a frustoconical skirt 78, 80 widening, respectively, radially towards the outside and radially towards the inside. The first portion 74 annular of end and the second portion 76 annular of end are connected one to the other by a cylindrical annular portion 82. It can be seen that the second annular end portion 76 of bushing 60 has a wall thickness e1 less than the wall thickness e2 of cylindrical portion 82 so as to allow crimp deformation of the second annular end portion 76 used to retain stud 62. This difference in thickness is best seen in FIG. 8 showing the bushing 60 before crimping and also in FIG. 7 showing the bushing 60 after crimping.

(17) The first annular end portion 74 of bushing 60 is applied to the radially outer face 66a of the circumference of hole 64, and more precisely to the radially outer face 66a of the frustoconical portion 66 of the circumference of hole 64.

(18) At each hole 64, a stud 62 is mounted around a bushing 60 and radially between a panel 38 and the first radial annular wall 24. This stud 62 is traversed by the bushing 60 and held by this one integral with a panel 38. This stud 62 comprises a radially outer annular face 84 of a shape substantially complementary to the radially inner face 66b of the frustoconical part 66 of the periphery of hole 64 of panel 38. In the present case, this radially outer annular face 84 of stud 62 is of frustoconical shape with a cross-section increasing radially outwards. It can be seen that stud 62 has an annular recess or counterbore 86 surrounding the bushing 60 and receiving the cylindrical rim 88 of the periphery of the hole 64. The free end of the cylindrical rim 68 of the circumference of the hole 64 is arranged at a distance, i.e., without contact with the bottom 90 of the recess, so that the support of the stud 62 on the circumference of the hole 64 is made at the radially outer annular face 84 of the stud 62 and not at the free end of the cylindrical rim 88 of the circumference of the hole 64. Stud 62 comprises a substantially flat annular surface 92 applied to a radially outer face of the first annular wall 24 of the upstream annular shroud 22.

(19) As it is clearly visible in FIGS. 4, 5 and 7, the second frustoconical skirt 80 of the bushing 60 is arranged radially opposite a corresponding annular surface 81 of the stud 62, here also frustoconical in shape, so as to ensure radial retention of the stud 62 on the panel 38. In this way, it is possible to pre-install the bushing 60 and the stud 62 on panel 38 by making these three parts integral with each other to allow simple handling of panel 38.

(20) As shown in FIG. 8, the bushing 60 is installed so that its first frustoconical skirt 78 comes to rest on the radially external face of the frustoconical part 66 of the periphery of the hole 64, the second annular portion 76 of the bushing 60 then having a substantially cylindrical shape necessary for the introduction of the bushing 60 into the hole 64 of panel 38. The stud 62 is then mounted around the bushing 60 and the second annular portion 76 is crimped to form a frustoconical skirt 80 as described above.

(21) The second skirt 80 frustoconical can present an angular opening of approximately 60°. The first frustoconical 78 skirt can present an angular opening higher than the angular opening of the second frustoconical 80 skirt, which can be of the order of 100° to 130° (FIGS. 4, 5 and 7).

(22) More specifically, the mounting and crimping of the bushing 60 on stud 62 is carried out in such a way that the bushing has a clearance in the radial direction relative to panel 38 of about one tenth of a millimeter when the stud is in contact with the radially inner face of the frustoconical wall 66 of panel 38. This limits the mechanical stresses applied to the panel 38, particularly around the periphery of the hole 64 of the panel 38 and also to the stud 62 after crimping of the bushing 60. In practice, the crimping is carried out in such a way as to have an annular space between the second annular portion 76 or frustoconical skirt 80 and the annular surface 81 of the stud (FIG. 7).

(23) When panel 38 is provided with the bushings 60 and the studs 62, it is mounted radially opposite the first annular wall 24 and screws 48 are inserted into the bushings 60, the head 70 of a screw coming to rest on the first frustoconical skirt 78 and its opposite end is screwed into a nut 50 crimped on the first annular wall 24 (FIG. 5).

(24) FIG. 7 includes a plurality of arrows F1, F2, F3 which represent the clamping force applied to panel 38 which is observed to pass through and be distributed over the entire frustoconical part 66 of the periphery of hole 64, then passes through the frustoconical surface 84 of pad 62 and is then transmitted to the first annular wall 24.

(25) Bushing 60 can be made of metallic material and stud 62 can be made of thermosetting resin.