Blade provided with platforms possessing attachment portions

Abstract

A preform for a turbine engine blade, comprising a main fiber preform obtained by three-dimensional weaving and comprising: a first longitudinal segment, suitable for forming a blade root; a second longitudinal segment, extending upwards from the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment, extending transversely from the junction between the first and second longitudinal segments to a substantially linear distal edge and suitable for forming a first platform; the preform further including at least one attachment tab provided under the first transverse segment at its distal edge, suitable for forming an attachment portion of the platform.

Claims

1. A blade for a turbine engine, the blade comprising: a blade root; an airfoil portion extending upwards from the blade root; a platform made of composite material and extending transversely to the airfoil portion at a junction between the blade root and the airfoil portion, wherein the platform extends from the blade root along a first axis; and an attachment portion provided on a lower surface of the platform at a distal end of the platform, configured to cooperate with a first hook of the turbine engine, wherein the attachment portion is at a furthest position of the platform on the first axis away from the blade root.

2. The blade according to claim 1, made as a single piece of composite material by means of a preform, said preform being shaped in a mold and embedded in a matrix.

3. The blade according to claim 1, wherein the attachment portion is fitted to the platform.

4. A rotor wheel for a turbine engine, the wheel comprising a plurality of blades according to claim 1, and a disk or a downstream drum.

5. The wheel according to claim 4, wherein radial clearance of at least 0.5 mm, and/or tangential clearance of at least 1 mm is provided between the attachment portion of the platform of at least one of the plurality of blades and a corresponding first hook while the wheel is stationary.

6. A turbine engine including the wheel according to claim 4.

7. A turbine engine including at least one blade according to claim 1.

8. The blade according to claim 1, wherein a first portion of the platform is at a proximal location relative to the airfoil portion and a second portion of the platform is at a distal location relative to the airfoil portion.

9. The blade according to claim 8, wherein the second portion of the platform includes the attachment portion.

10. The blade according to claim 9, wherein the attachment portion forms an axial cavity on the lower surface of the platform.

11. The blade according to claim 1, wherein the attachment portion forms an axial cavity on the lower surface of the platform.

12. The blade according to claim 1, wherein: the airfoil extends from the blade root in a first direction; the platform extends from the blade root in a second direction that is perpendicular to the first direction; and the attachment portion forms an axial cavity that extends in a third direction that is perpendicular to both the first direction and the second direction.

13. A disk for a rotor wheel, the disk having its circumference presenting a succession of slots and of teeth, each slot being configured to receive one of a plurality of blades, wherein at least one of the plurality of blades includes: a blade root; an airfoil portion extending upwards from the blade root; a platform made of composite material and extending transversely to the airfoil portion at a junction between the blade root and the airfoil portion; and an attachment portion provided on a lower surface of the platform at a distal end of the platform, configured to cooperate with a first hook of the turbine engine; wherein at least one tooth among said teeth is provided with the first hook extending radially from a top surface of the tooth and configured to cooperate with the attachment portion of the at least one of the plurality of blades.

14. The disk according to claim 13, wherein at least one tooth among said teeth is provided with a second hook possessing at least two distinct attachment fingers, wherein the attachment fingers taper away from a body of the second hook.

15. A rotor wheel for a turbine engine, the wheel comprising a plurality of blades, and the disk according to claim 13.

16. The disk according to claim 13, wherein the attachment portion is provided in a middle zone of the platform of the one of the plurality of blades.

17. The disk according to claim 16, wherein the middle zone is formed by a portion of the platform of the one of the plurality of blades and a further portion of a platform of an adjacent blade of the plurality of blades.

18. The disk according to claim 13, wherein the hook is machined in a thickness of the disk; or wherein the hook is fitted on a top surface of the disk.

19. A downstream drum for a rotor wheel configured to rotate synchronously with a disk carrying a plurality of blades, wherein at least one of the plurality of blades includes: a blade root; an airfoil portion extending upwards from the blade root; a platform made of composite material and extending transversely to the airfoil portion at a junction between the blade root and the airfoil portion; and an attachment portion provided on a lower surface of the platform at a distal end of the platform, configured to cooperate with a first hook of the turbine engine; the downstream drum including at least one third hook extending from an upstream face of the downstream drum and configured to cooperate with the attachment portion of the at least one of the plurality of blades.

20. A rotor wheel for a turbine engine, the wheel comprising a plurality of blades, and the downstream drum according to claim 19.

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 element) that are identical are identified by the same reference signs. In addition, elements (or portions of an element) that belong to different embodiments, but 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 a turbine engine of the invention.

(4) FIG. 2 is a fragmentary radial section diagram of a rotor wheel of the invention.

(5) FIG. 3 is an axial section diagram of a rotor wheel of the invention.

(6) FIG. 4 is a fragmentary radial section view of a rotor wheel in a first embodiment.

(7) FIG. 5 is a diagram showing the preform corresponding to the blade of this first embodiment, prior to shaping.

(8) FIG. 6 is a diagram showing the preform corresponding to the blade of this first embodiment, after shaping.

(9) FIG. 7 is a fragmentary radial section view of a rotor wheel in a second embodiment.

(10) FIG. 8 is a fragmentary radial section view of a rotor wheel in a third embodiment.

(11) FIG. 9 is a fragmentary radial section view of a rotor wheel in a fourth embodiment.

(12) FIG. 10 is a perspective view of a hook in the fourth embodiment.

DETAILED DESCRIPTION OF EMBODIMENTS

(13) In order to make the invention more concrete, embodiments are described below in detail with reference to the accompanying drawings. It should be recalled that the invention is not limited to these embodiments.

(14) FIG. 1 is a view of a bypass turbojet 1 of the invention, shown in section on a vertical plane containing its main axis A. From upstream to downstream in the flow direction of the air stream, 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.

(15) The fan wheel 2 is shown in greater detail in FIGS. 2 and 3. It comprises an upstream shroud 14, a fan disk 11, and a downstream drum 15, also referred to as a “booster drum”.

(16) A plurality of slots 12 are formed in the outside surface of the fan disk 11: these slots 12 are rectilinear and they extend axially from upstream to downstream all along the disk 11. They are also regularly distributed around the axis A of the disk 11. In this manner, each slot 12 co-operates with its neighbour to define a tooth 13 that thus likewise extends axially from upstream to downstream all along the disk 11.

(17) The fan wheel 2 also comprises a plurality of blades 10 mounted in the slots 12 of the fan disk 11. Each blade 10 has a dovetail blade root 21 configured to engage in a slot 12 of the disk 11 so as to fasten it to the disk 11. This blade root 21 is extended upwards by an airfoil 22 presenting a suction side face 22e and a pressure side face 22i, each extending from upstream to downstream between a leading-edge 22a and a trailing edge 22f.

(18) The blade 10 also has a suction side platform 23 extending transversely from the suction side of the blade from the junction between the blade root 21 and the airfoil 22, and a pressure side platform 24 extending transversely from the pressure side of the blade from the junction between the blade root 21 and the airfoil 22.

(19) The upstream shroud 14 and the downstream drum 15 are connected to the disk 11, which disk is coupled to the low-pressure shaft of the turbojet 1. Thus, while the turbojet is in operation, the upstream shroud 14, the fan disk 11, the blades 10, and the downstream drum 15 are driven together in rotation by the low-pressure turbine 7.

(20) At the distal end of each of the platforms 23 and 24, and on its insides, there are provided a plurality of attachment portions 40. Each of these attachment portions 40 is in the form of a box section or of a pipe segment arranged against the bottom surface of the corresponding platform 23, 24, along its distal edge 23a, 24a. These attachment portions 40 thus form substantially cylindrical cavities 41 on rectangular bases that are open both upstream and downstream.

(21) In this embodiment, each platform 23, 24 has three attachment portions 40: a first at the downstream end of the platform 23, a second in the middle zone of the platform 23, and a third at the upstream end of the platform 23. Nevertheless, it is clear that an arbitrary number of attachment portions 40 could be used, in particular as a function of the lengths of the platforms 20, 24, on the magnitudes of their overhangs, and on the configuration of the wheel 2.

(22) Each attachment portion 40 is configured to cooperate with a hook of the fan wheel 2. Three types of hook are described in this first embodiment.

(23) Each tooth 13 thus possesses two hooks 50 for co-operating with respective attachment portions 40 situated in the middle zones of the coinciding platforms 23, 24. Each hook 50 thus extends radially from the top of the tooth 13 and possesses an attachment finger 50a that engages from downstream inside the cavity 41 of the attachment portion 40 of the platform 23, 24 in question. The attachment finger 50a may be triangular in shape, tapering from the body of the hook: the cavity 41 of the attachment portion 40 of the platform 23, 24 then possesses a complementary prismatic shape as a wedge shape. In a variant, the attachment finger 50a may also be of constant profile.

(24) The downstream drum 15 also possesses a plurality of hooks 51, with their attachment fingers 51a configured to cooperate with the attachment portions 40 situated at the downstream ends of the platforms 23, 24. Likewise, the upstream shroud 14 possesses a plurality of hooks 52 with their attachment fingers 52a configured to cooperate with the attachment portions 40 situated at the upstream ends of the platforms 23, 24.

(25) As can be seen more clearly in FIG. 4, when stationary, radial clearance R is left between the bottom face of the attachment finger 50a and the bottom face of the cavity 41; and, when stationary, radial clearance T is also left between the proximal face of the attachment finger 50a and the proximal face of the cavity 41. Such clearances may also exist with the other types of hook 51 and 52.

(26) In the first embodiment, better shown in FIG. 4, the blade 10 is obtained as a single piece by 3D weaving a preform 30 and by injecting an organic resin using the resin transfer molding (RTM) method, known to the person skilled in the art.

(27) FIG. 5 shows this three-dimensionally woven preform 30 suitable for making this embodiment of the blade 10. FIG. 6 shows the final preform 30′ after it has been shaped. The preform 30 is described from bottom to top, i.e. from upstream to downstream in the weaving direction T. Nevertheless, it is clear that the weaving could be performed starting from the other end and in the opposite direction.

(28) In this embodiment, the preform 30 is three-dimensionally woven out of carbon fibers using a 3D interlock weave. Only the surfaces of the preform 30 are woven two-dimensionally using a satin type weave.

(29) At the bottom end, weaving begins by making a first longitudinal segment 31 that is to form the root 21 of the blade 10.

(30) Above this first longitudinal segment 31, there begins a zone of non-interlinking D in which a first free panel 35, a second longitudinal segment 32, and a second free panel 36 are woven jointly in non-interlinked manner with respective non-interlinking planes 38 and 39. Methods that enable such non-interlinking are now well known in the field of 3D weaving.

(31) As from a certain level, which may vary depending on the weaving plane, the free panels 35, 36 have reached the lengths desired for the platforms 23, 24 in question in the weaving plane under consideration. As from the distal edge 33a, 34a as defined in this way, weaving continues in certain planes only in order to form tabs 37 that extend from the distal edge 33a, 34a.

(32) In a variant, the weaving may continue from the distal edge 33a, 34a in uniform manner all along the free panel 35, 36: under such circumstances, the tabs 37 are obtained by cutting out or machining.

(33) Once weaving has finished, the free panels 35, 36 are cut out: on the suction side this provides a first transverse segment 33 that extends to the distal edge 33a, and that is to form the suction side platform 23 of the blade 10 together with a plurality of attachment tabs 37 extending from some of the segments of the distal edge 33a so as to form attachment portions; on the pressure side, this provides a second transverse segment 34 that extends to the distal edge 34a, and that is to form the pressure side platform 24 of the blade 10 together with a plurality of attachment tabs 37 extending from some of the segments of the distal edge 34a so as to form attachment portions. It should be observed at this point that the terms “transverse” and “longitudinal” are used as a function of the final position of the segment in question, the transverse segments necessarily being woven longitudinally prior to being folded transversely.

(34) The preform 30 can then be moistened in order to soften it and make it easier to move fibers out of register. The preform 30 is then put into a shaping mold having its inside space matching the shape desired for the preform 30. During this step, the attachment tabs 37 are folded in U-shapes under the transverse segments 33 and 34, with the ends of the tabs 37 being pressed against the bottom surfaces of the corresponding transverse segments 33, 34.

(35) Thereafter, the preform 30 is dried so as to stiffen it, thus blocking the shape imparted during shaping. The preform 30 as shaped in this way is finally placed in an injection mold having the dimensions of the desired final blade 10, and a matrix is injected therein, specifically an epoxy resin. By way of example, such injection may be performed using the RTM method. This consolidation thus serves to block the shape of the blade and to secure the ends of the tabs 37 against the bottom surfaces of the platforms 23 and 24. Thus, at the end of this step, a single piece blade 10 is obtained that is made out of composite material and that is provided with attachment portions 40.

(36) Naturally, the above-described weaving example is merely one out of numerous other possible examples that the person skilled in the art will easily recognise. In particular, it is possible to imagine other forms of non-interlinking or to use other weaving techniques such as layer crossings, extracting layers, or thickness transitions in order to obtain a preform of analogous shape. The person skilled in the art can find numerous examples of weaving in Document WO2014/076408.

(37) In a second embodiment, shown in FIG. 7, the attachment portions are in the form of box sections 140 that are rectangular in section, extending against the bottom surfaces of the platforms 123, 124, along certain segments of their distal edges 123a, 124a. This metal or composite box section is hollow and thus forms a cavity 141 that opens out axially both upstream and downstream.

(38) Such a blade 110 can be obtained using a fabrication process analogous to the first embodiment. A main fiber preform analogous to the fiber preform 30 of the above embodiment is thus woven, and then the box sections 140, acting as attachment tabs, are fitted against the bottom surfaces of the transverse segments of the main preform, e.g. using rivets or spots of adhesive, the completed preform then being subjected to co-injection.

(39) Alternatively, the box sections 140 may be fitted, by adhesive, riveting, bolting, or any other method, to a composite blade that has already been consolidated, e.g. obtained from a main fiber preform analogous to that described in the context of the first embodiment, but without any extra length of weaving beyond the distal edges of the transverse segments.

(40) In a third embodiment, shown in FIG. 8, the attachment portions 240 are in the form of box sections 243 analogous to the box section 140 of the above embodiment having woven tabs 242 analogous to the extra lengths of the first embodiment wrapped around them. Each attachment portion 240 is thus likewise hollow and forms a cavity 241 that opens out axially both upstream and downstream.

(41) In order to make such a blade 210, a main fiber preform analogous to that of the first embodiment is woven initially. Thereafter, box sections 243 analogous to those of the second embodiment are fitted against the bottom surfaces of the transverse segments of the main preform, against its distal edges. The attachment tabs of the main fiber preform are then folded around the box sections 243, which therefore act as inserts. The preform as finished off in this way and as shaped is then subjected to a step of matrix injection and consolidation analogous to that of the first embodiment.

(42) FIG. 9 shows a fourth embodiment in which the blades 310 are analogous to those of the first embodiment, but in which the disk 311 is provided with different hooks 350. As can be seen in FIG. 10, each hook 350 in this embodiment is provided with two distinct attachment fingers 350a, 350b extending side-by-side and configured to cooperate with two coinciding attachment portions 340 of two neighbouring platforms 323, 324.

(43) It will naturally be understood that such a double hook can be used with a blade in accordance with any of the embodiments described.

(44) The embodiments or implementations described in the present description are given by way of nonlimiting illustration, and a person skilled in the art can easily, in the light of this description, modify these embodiments or implementations, or can envisage others, while remaining within the ambit of the invention.

(45) Furthermore, the various characteristics of these embodiments can be used singly or in combination with one another. When they are 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, a characteristic described with reference to any one embodiment may be applied in analogous manner to any other embodiment.