TURBOMACHINE EXHAUST CASING AND METHOD FOR MANUFACTURING SAME

Abstract

A casing is provided, for example, an exhaust casing for a turbomachine. The casing generally includes an inner hub having an axis of rotation and an outer annular ferrule extending around the hub, the ferrule configured to define, with the hub, an annular flow path for a gas stream. In some examples, the ferrule is rigidly connected to the hub by arms. The hub generally includes, at one longitudinal end, a scalloped annular flange comprising solid portions distributed at regular intervals about said axis and spaced apart from each other by hollow portions. The hub is produced by assembling several angular hub sectors arranged circumferentially end to end around the axis, each hub sector connected to an adjacent hub sector by a longitudinal weld bead that extends over substantially the entire axial extent of the hub and that is substantially aligned axially with a hollow portion of said flange.

Claims

1. A casing for a turbomachine, comprising: an inner hub with an axis of revolution; and an outer annular ferrule extending around the inner hub, the ferrule configured to define, with the inner hub, an annular flow path for a gas stream, and rigidly connected to the hub by arms, the hub comprising, at a longitudinal end, a scalloped annular flange comprising solid portions regularly distributed about the axis and spaced apart from each other by hollow portions, wherein the hub is produced by assembling, by welding, several angular hub sectors arranged circumferentially end to end around the axis, each sector connected to an adjacent hub sector by a longitudinal weld bead extending over substantially the entire axial extent of the hub and substantially aligned axially with a hollow portion of the flange.

2. The casing of claim 1, wherein the number of hub sectors is equal to the number of arms of the casing.

3. The casing of claim 1, wherein each hub sector is initially formed from one single part with a radially inner portion of one of the arms.

4. The casing of claim 1, wherein the radially inner portion of each arm is substantially situated between two adjacent solid portions.

5. The casing of claim 1, wherein each arm comprises an upper surface and a lower surface, each weld bead extending between the upper surface of a first arm and the lower surface of a second adjacent arm, and being situated closer to the lower surface of the second arm than the upper surface of the first arm.

6. The casing of claim 1, wherein the hollow portions each comprise a median edge, substantially straight-lined and tangent to a circumference centered on the axis A.

7. The casing of claim 1, wherein the arms extend into the planes, substantially tangent to a circumference centered on the axis.

8. A turbomachine comprising at least one casing according to claim 1.

9. A method for manufacturing a casing for a turbomachine, the casing comprising an inner hub and an outer annular ferrule extending around the hub and an axis of revolution, the ferrule configured to define, with the inner hub, an annular flow path for a gas stream and rigidly connected to the hub by arms, the hub comprising, at a longitudinal end, a scalloped annular flange comprising solid portions regularly distributed about the axis and spaced apart from each other by hollow portions, the method comprising: assembling, by welding, several angular hub sectors arranged circumferentially end to end around the axis, each hub sector being connected to an adjacent hub sector by a longitudinal weld bead extending over substantially the entire axial extent of the hub, and substantially aligned axially with a hollow portion of the flange.

10. The method of claim 9, wherein the welding is performed by an electron beam.

11. The method of claim 9, wherein, to produce each weld bead, the electron beam is inclined with respect to the axis, and is moved into a substantially longitudinal plane passing via the axis and the bead to be produced, without passing through the material of the flange.

12. The method of claim 11, wherein the electron beam is inclined with respect to the axis radially towards the outside from a downstream longitudinal end towards an upstream longitudinal end of the casing.

Description

DESCRIPTION OF THE FIGURES

[0033] The invention will be best understood, and other details, characteristics and advantages of the invention will appear more clearly, upon reading the following description, made as a non-limiting example and in reference to the appended drawings, wherein:

[0034] FIG. 1 is a schematic, axial cross-sectional half-view of a downstream turbomachine portion, and shows an exhaust casing,

[0035] FIG. 2 is a schematic, perspective view of an exhaust casing, front view from downstream,

[0036] FIG. 3 is a schematic, perspective view of an exhaust casing according to the invention, and FIG. 3a shows, in perspective, the hub sectors which compose this casing,

[0037] FIG. 4 is an axial cross-sectional partial schematic view of an exhaust casing,

[0038] FIGS. 5 and 6 are schematic, perspective views of the casing of FIG. 3, and shows a flange, downstream from this casing, and

[0039] FIG. 7 is a perspective partial schematic view of the exhaust casing of FIG. 3.

DETAILED DESCRIPTION

[0040] FIGS. 1 and 2 represent a casing 10, here an exhaust casing, of an aircraft turbomachine.

[0041] Conventionally, a turbomachine comprises a gas generator comprising, from upstream to downstream, in the flow direction of the gas streams, at least one compressor, a combustion chamber, and at least one turbine. Downstream of the turbine 12, is situated the exhaust casing 10 which mainly comprises an inner hub 14 and an outer annular ferrule 16 which extends around the hub and an axis of revolution A which is the longitudinal axis of the turbomachine. In the present application, the expressions radial and radially make reference to the axis of revolution of the hub or of the casing.

[0042] The ferrule 16 and the hub 14 together define an annular flow path 18 for the combustion gases exiting the turbine 12.

[0043] The ferrule 16 and the hub 14 are rigidly connected to each other by arms 20, substantially radial with respect to the axis A. The arms 20 can be inclined with respect to the planes passing via the axis A. Advantageously, the arms 20 extend into the planes, substantially tangent to a circumference centred on the axis A, as can be seen in FIG. 2.

[0044] The casing 10 comprises flanges 22 for fixing to other elements of the turbomachine. These mounting flanges 22 are situated at the upstream and downstream longitudinal ends of the casing. In the example represented, the ferrule 16 comprises an annular flange 22a, 22b at each of its upstream and downstream longitudinal ends. The upstream flange 22a is fixed to a downstream end of a casing of the turbine 12 and the downstream flange 22b is fixed to an upstream end of an exhaust nozzle 24.

[0045] The hub 14 comprises, at the downstream longitudinal end, an annular flange 22c for fixing to an upstream end of an exhaust cone 26 surrounded by the nozzle 24.

[0046] The flange 22c is scalloped, i.e. it comprises solid portions regularly distributed about the axis A and spaced apart from each other by hollow portions.

[0047] In the prior art, the casing 10 is manufactured by returning and by fixing the ferrule 16 and the arms 18 on a hub 14 which is one-piece and produced from one single part, generally by casting.

[0048] FIG. 3 illustrated a principle of the invention, consisting of manufacturing such a casing from a hub 14, sectored and therefore formed by assembling several hub sectors 14 arranged circumferentially end to end and fixed to each other by welding, preferably by electron beam or EB welding.

[0049] FIG. 3a shows the hub sectors 14 which each comprise a radially inner portion 20a of an arm. The number of sectors 14 here is equal to the number of arms 20 and each hub sector 14 is associated with a radially inner portions 20a of an arm. The hub sector 14 and the portion of arm 20a are formed from one single part by casting. The radially outer portions 20b of the arms are thus returned and fixed on the portions 20a, and the ferrule, sectored or not, is also returned and fixed on the portions 20b. The fixing of the different portions of the casing can be done by welding, preferably EB welding.

[0050] In the case of an EB welding, and such as represented in FIGS. 3 and 4, each hub sector 14 is connected to an adjacent hub sector by a longitudinal weld bead 30 which extends over substantially the entire axial extent of the hub.

[0051] To produce each weld bead, the electron beam is inclined with respect to the axis A, for example radially towards the outside from a downstream longitudinal end towards an upstream longitudinal end of the casing, and is moved in a substantially longitudinal plane passing via the axis and the bead to be produced, and which corresponds to the plane of the drawing sheet of FIG. 4

[0052] The reference 34 to FIG. 4 means the electron beam. It is oriented towards the zone to be welded, i.e. at the level of the junction zone between two longitudinal edges opposite two adjacent hub sectors. The beam 34 here passes through successively three skins or walls, namely the edges to be welded, an inner annular stiffener 32 of the hub, and the flange 22c. Indeed, the solid portions 22c1 of the flange 22c are situated on the trajectory of the beam and are therefore passed through by the latter. This is not the case for the hollow portions 22c2. This specific case is naturally connected to the inclination angle of the electron beam vis--vis the axis A, but this angle can be imposed by the general shape of the casing.

[0053] As mentioned in the above, EB welding is capable of passing through several skins, but this requires more power and leads to less stability in the quality of the welding obtained.

[0054] The invention makes it possible to overcome this problem, thanks to the axial alignment of the weld bead 30 between two hub sectors 14 with a hollow portions 22c2 of the scalloped flange 22c.

[0055] FIGS. 5 to 7 make it possible to illustrate the invention.

[0056] It is observed, in these figures, that the radially inner portion 20a of each arm 20 is substantially situated between a first longitudinal plane P1 passing via the axis A and one of the solid portions 22c1 of the flange, and a second longitudinal plane P2 passing via the axis A and another adjacent portion of these solid portions. The solid portions 22c1 are situated halfway from the portion 20a of the arm. In other words, the solid portions are placed symmetrically on either side of this portion of the arm.

[0057] Each arm 20 comprises an upper surface 36 and a lower surface 37. Each weld bead 30 extends between the upper surface of a first arm and the lower surface of a second adjacent arm, and is situated closer to the lower surface of the second arm than the upper surface of the first arm in the example represented.

[0058] The hollow portions 22c2 of the flange 22c each comprise a median edge 38, substantially straight-lined and tangent to a circumference C1 centred on the axis A. The solid portions 22c1 also each comprise a median edge, substantially straight-lined and tangent to a circumference C2 centred on the axis A. These solid portions 22c1 are furthermore pierced with orifices 40 for passing of screw-nut type means.

[0059] FIG. 7 illustrates the passing of the electron beam 34 at the level of the zone of the flange 22c. It is observed that, because of the axial alignment of the zone to be welded with a hollow portion 22c2 of the flange 22c, or even also because of the resizing of the flange, especially in the thickness and/or radial size, the beam does not pass through the flange 22c. The welding can thus be of the double-skin type, if the beam must pass through the stiffener 32, which is the case in the example represented.