Turbine or compressor stage including an interface part made of ceramic material

Abstract

A turbine or compressor stage for a turbine engine is provided. The stage includes a disk including a metal material configured to be coupled to a shaft of the turbine engine, an airfoil including a ceramic matrix composite material, and an interface part that is distinct from the airfoil and that is configured to be fastened to the disk and to fasten the airfoil. The interface part includes a ceramic or a ceramic matrix composite material.

Claims

1. A turbine or compressor stage for a turbine engine, the turbine or compressor stage comprising: a disk configured to be coupled to a shaft of the turbine engine; and at least one airfoil having a fastener portion at a radially inner end, wherein the disk comprises metal material, wherein the at least one airfoil comprises ceramic matrix 3D-woven composite material, wherein the turbine or compressor stage further includes an interface part distinct from the at least one airfoil and configured to be fastened to the disk and to fasten said at least one airfoil so as to form an interface between the disk and the at least one airfoil, the interface part including a slot in which the fastener portion of the at least one airfoil is inserted in order to fasten the fastener portion of the airfoil to the interface part, and walls located on upstream and downstream ends of the interface part, the walls extending radially outward, and a piece of ceramic or ceramic matrix 3D-woven composite material distinct from the at least one airfoil and distinct from the interface part, the piece of ceramic or ceramic matrix 3D-woven composite material being attached to the walls located on the upstream and downstream ends of the interface part, the piece of ceramic or ceramic matrix 3D-woven composite material including an inner platform, an upstream lip, and a downstream lip, the downstream lip being radially outward of the upstream lip, and wherein the interface part comprises a ceramic material, at least in a zone of the interface part in contact with the disk.

2. A turbine or compressor stage according to claim 1, wherein the interface part is a single piece comprising ceramic material.

3. A turbine or compressor stage according to claim 1, wherein the interface part comprises a first portion of ceramic matrix 3D-woven composite material and a second portion of ceramic material, the interface part being configured so that the first portion is not in contact with the disk.

4. A turbine or compressor stage according to claim 1, wherein the interface part includes a fastener portion projecting towards the disk, and wherein the disk comprises two half-disks with outer segments configured so as to co-operate with the fastener portion of the interface part so as to fasten the fastener portion of the interface part to the disk, the two half-disks being held pressed one against the other.

5. A turbine or compressor stage according to claim 1, wherein an inner end of the at least one airfoil is extended by the fastener portion, and wherein the interface part includes a socket into which the fastener portion of the at least one airfoil is engaged, the fastener portion of the at least one airfoil being fastened in the socket by a retaining element inserted through said fastener portion of the at least one airfoil and through at least a portion of the interface part.

6. A turbine or compressor stage according to claim 1, wherein parts of the turbine or compressor stage comprise ceramic material which is molded and sintered.

7. A turbine engine, including at least one turbine or compressor stage according to claim 1.

8. A turbine or compressor stage according to claim 1, wherein an outer platform of the at least one airfoil includes an upstream wiper and a downstream wiper, a free end of the downstream wiper being radially outward of a free end of the upstream wiper.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The accompanying drawings are diagrammatic and seek above all to illustrate the principles of the invention.

(2) In the drawings, from one figure to another, elements (or portions of an element) that are identical, are identified by the same reference sign. In addition, elements (or portions of elements) belonging to different embodiments and that are analogous in function, are identified in the figures by numerical references incremented by 100, 200, etc.

(3) FIG. 1 is an axial section view of an example of a turbojet.

(4) FIG. 2 is an axial section view of a first example of a stage of the invention.

(5) FIG. 3 is an axial section view of a second example of a stage of the invention.

(6) FIGS. 4A, 4B and 4C show variant embodiments of the fastening of the airfoil on the interface part.

(7) FIGS. 5A and 5B show variant embodiments of the platform and of the lips.

(8) FIGS. 6A, 6B, and 6C show variant embodiments of the structure of the interface part.

(9) FIGS. 7A, 7B, and 7C show variant embodiments of the fastener portion of the interface part.

DETAILED DESCRIPTION OF EMBODIMENTS

(10) In order to make the invention more concrete, examples of turbine stages of a turbine engine are described in detail below with reference to the accompanying drawings. It should be recalled that the invention is not limited to these examples.

(11) FIG. 1 is a section view on a vertical axial plane containing the main axis A of a bypass turbojet 1 of the invention. From upstream to downstream it comprises a fan 2, a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, and a low pressure turbine 7.

(12) FIG. 2 is a section view on the same axial plane showing a portion of the low pressure turbine 7. This turbine 7 comprises a plurality of stages 10 in a first embodiment, each comprising a rotor 10a and a stator 10b following one after the other from upstream to downstream. Each rotor 10a comprises a plurality of rotor blades 11, each comprising an airfoil 20 and an interface part 40 that are mounted on a disk 30, which is coupled to a shaft of the bypass turbojet 1.

(13) Each airfoil 20 is made of 3D-woven ceramic matrix composite (CMC) material. At its bottom end, the airfoil 20 has a dovetail-shaped fastener portion 21.

(14) Each interface part 40 is made of ceramic material. Each interface part 40 includes at its top end a slot 41 of shape complementary to the shape of the dovetail-shaped fastener portion 21 of the airfoil 20, and at its bottom end it includes a rod 42 terminating in a fastener portion 43 that is likewise dovetail-shaped.

(15) The disk 30 is made of metal. It comprises two half-disks 30a and 30b arranged one against the other. The outer end segment 31a, 31b of each half-disk 30a, 30b is spaced apart from the adjacent half-disk 30a, 30b so as to be C-shaped in order to co-operate with the adjacent half-disk 30b, 30a to form a cavity 32.

(16) Thus, the airfoil 20 is mounted on the interface part 40 by means of its fastener portion 21 that is engaged and brazed in the slot 41 in the interface part 40. The interface part 40 is itself mounted on the disk 30 by its fastener portion 43 being clamped within the cavity 32 by the outer segments 31a and 31b of the half-disks 30a and 30b, which disks are held pressed against each other by means of a bolted connection 33.

(17) The disks 30 of each stage 10 are also connected to one another in pairs by metal shrouds 34 that are bolted to the disks 30. Advantageously, such shrouds 34 are fastened to the bolted connection 33 between the two half-disks 30a and 30b.

(18) The blade 11 also has an outer platform 50 made of woven CMC material that is attached to the airfoil 20 by brazing. It could equally well be made of ceramic material. The outer platform 50 has wipers 51 configured to rub against an abradable track of the stator of the turbine 7 so as to provide the rotor 10a with sealing relative to the stator.

(19) The blade 11 also has an inner platform 61 with upstream and downstream lips 62 and 63 made as a single piece 60 of woven CMC material fitted on the interface part 40 by brazing. It could equally well be made of ceramic material. In this embodiment, the part 60 constituting the platform 61 and the lips 62 and 63 is attached via low walls 44 of the interface part 40 that extend radially outwards so as to be located on either side of the non-airfoil bottom portion of the airfoil 20 leading to the fastener portion 21.

(20) FIG. 3 is a section in the same axial plane showing a portion of a second example of the low pressure turbine 7. This turbine 7 has a plurality of stages 110 in a second embodiment. In manner identical to the first example, each rotor 110a has a plurality of rotor blades 111, each comprising an airfoil 120 and an interface part 140 mounted on a disk 130 that is coupled to a shaft of the bypass turbojet 1. Only the differences with the first example are described in detail.

(21) Unlike the first example, which presents a hammer type attachment, this second example presents a shank type attachment.

(22) In this second example, the dovetail 143 of the interface part 140 extends axially and no longer tangentially.

(23) The disk 130 is then made as a single piece, and in the vicinity of its outline it includes axial slots that are configured to receive the dovetail-shaped ends 143 of the interface part 140.

(24) The two above-described configurations are only two embodiments, and they may be subjected to numerous variations.

(25) In particular, in the first-described example, the airfoil 20 is mounted on the interface part 40 with the help of a fastener portion 21 having its dovetail oriented tangentially so as to engage in the tangential slot 41 in the interface part 40: this is a hammer-type attachment. Nevertheless, as shown in FIG. 4A, the dovetail of the fastener portion 321 of the airfoil 320 could equally well be oriented radially; under such circumstances, the slot 341 in the interface part 340 is also oriented radially: this thus constitutes a shank-type attachment.

(26) In another variant shown in FIGS. 4B and 4C, the airfoil 320 does not have a dovetail-shaped fastener portion. Instead of that, it has a fastener tab 322 extending the bottom portion of the airfoil 320 with unchanging profile; this fastener tab 322 is also provided with a through orifice 323. The interface part 340 does not have a slot, but rather a radial socket 344 of shape complementary to the fastener tab 322 of the airfoil 320; a through orifice 345 passes through the interface part 340 and the socket 344. Under such circumstances, the airfoil 320 engages in the socket 344 of the interface part 340: a peg 346 is then inserted through the orifices 345 in the interface part 340 and 323 in the fastener tab 322 of the airfoil 320 in order to fasten the airfoil to the interface part 340. The peg 346 is then brazed in position. An outer platform 350 may be fitted to radially outer end of the airfoil 320. A part 360 may be fitted on the interface part 340.

(27) Certain variants relate to the inner platform and the lips. In the two examples described, a single part 60 serves to provide the inner platform 61 and the lips 62 and 63 of the blade 11, this part 60 being fastened to the low wall 44 of the interface part 40. Nevertheless, as shown in FIG. 5A, in addition to the inner platform 461 and the lips 462 and 463, such a part 460 could also include upstream and downstream vertical portions 464 acting as low walls and fastened to the body proper of the interface part 440.

(28) In another variant, shown in FIG. 5B, the interface part 440 may be made integrally with portions 461, 462, 463, and 464 that correspond respectively to the inner platform, to the upstream lip, to the downstream lip, and to the low walls.

(29) Other variants relate to the structure of the interface part itself. In the two examples described, as in the example of FIG. 6A, the interface part 540 is made entirely out of ceramic material. Nevertheless, and as shown in FIG. 6B, the interface part 540 could equally well have reinforcement 547 made of woven CMC material: this reinforcement 547 is substantially in the form of a plate extending tangentially over the entire length of the interface part 540 and radially at least along the rod 542 and in part within the body of the interface part 540. The other portions of the interface part 540, and in particular the flanks of the rod 542 and the fastener portion 543 are made of ceramic material.

(30) In another variant shown in FIG. 6C, the interface part 540 has a first portion 548 forming the body and the rod 542 of the interface part 540 and made of 3D-woven CMC material. The interface part 540 then includes a second portion made up of two bearing surfaces 549 fitted to opposite sides of the rod 542 on its fastener portion 543, these bearing surfaces 549 being made of ceramic material.

(31) Finally, other variants relate to fastening the interface part on the disk. In the first embodiment described as shown in FIG. 2, the interface part 40 is mounted on the disk 30 with the help of a fastener portion 43 having its dovetail oriented tangentially so as to engage in the tangential slot 32 formed by the half-disks 30a and 30b: this constitutes a hammer-type attachment. Nevertheless, as in the second described example from FIG. 3 and as shown in FIG. 7A, the dovetail of the fastener portion 643 of the interface part 640 could equally well be radially oriented, and then the disk may be a single piece provided with radially oriented slots: this constitutes a shank-type attachment.

(32) In the variant shown in FIG. 7B, the interface part 640 does not have a fastener portion but includes a fastener tab 643 suitable for being inserted in a U-shaped cavity in the disk; the fastener tab 643 then has a through orifice 680 for passing the bolt.

(33) Nevertheless, in the variant shown in FIG. 7C, the interface part 640 could have two fastener tabs 643a and 643b, each having a through orifice 680a, 680b suitable for being fastened to the disk by bolting.

(34) The embodiments described in the present description are given by way of non-limiting illustration, in the light of this description, and the person skilled in the art can easily modify these embodiments or can envisage others, while remaining within the scope of the invention.

(35) Furthermore, the various characteristics of the embodiments may be used singly or in combination with one another. When combined, these characteristics may be combined as described above or in other ways, the invention not being limited to the specific combinations described in the present description. In particular, unless specified to the contrary, any characteristic described in relation with one particular embodiment may be applied in analogous manner to another embodiment.