COMPOSITE BLADE FOR A TURBINE ENGINE ROTOR

Abstract

The invention relates to a composite blade (5) for a turbine engine rotor, for example, an unducted propeller, comprising a skin (6) made of woven fibres forming the outer profile of the blade and an attachment (11) with cylindrical geometry in the direction of the span emerging from the blade root (9), which attachment is intended to retain the blade (5) on a hub of the rotor, characterised in that it further comprises a spar (16) having a hollow tube structure made of braided carbon fibres, fixed to the attachment (11) and extending inside the skin (6) over at least part of the span of the blade (5). The invention also relates to a propeller comprising said blade and to a method for manufacturing said blade.

Claims

1. A composite blade for a turbine engine rotor, for example an un-ducted propeller, comprising a skin (made of woven fibres forming the external profile of the blade and an attachment with cylindrical geometry in the direction of the span emerging from a blade root, which attachment is intended to hold the blade on a hub of said rotor, wherein said blade further comprises a spar having a hollow tube structure made of braided carbon fibres, fixed to the attachment and extending inside the skin over at least one portion of the span of the blade, preferably over a distance of between 30% and 70% of the span from the blade root.

2. The blade according to claim 1, wherein the attachment comprises a bell-shaped portion inserted at one end of the spar, a coiling of glass fibre preferably surrounding said end of the spar so as to immobilize the latter around the bell-shaped portion.

3. The blade according to claim 1, wherein the attachment is made of metallic material.

4. The blade according to claim 3, characterised in wherein the attachment is made of martensitic steel.

5. The blade according to claim 1, wherein a foam shape ensures the interface between the spar and the skin.

6. The blade according to claim 1, wherein the interior of the spar is filled with a foam shape.

7. The blade according to claim 1, wherein it comprises at its head only a monolithic portion of woven skin, without spar or foam inserted.

8. The blade according to claim 1, wherein the attachment comprises at least one reinforcement intended to form a ring for a ball rolling.

9. A turbine engine propeller comprising blades according to claim 1.

10. A method for manufacturing a blade according to claim 1, comprising the weaving of a preform for the skin, wherein it comprises a step of manufacturing an assembly comprising a braided preform of hollow spar and a cylindrical attachment fixed together, a step of inserting said assembly into the skin preform and a step of forming the blade with its final shape by a resin transfer moulding method, referred to as RTM.

11. The method according to claim 10, wherein the weaving of the preform of the skin is done with a method of interweaving warp strands with weft strands with the creation of an unbinding on a portion of the skin, arranged to insert the assembly comprising the braided spar preform and the attachment.

12. The method according to claim 11, wherein said unbinding takes place at a trailing edge of the skin preform.

13. The method according to claim 10, wherein a foam shape is inserted into the braided preform of the spar, when assembled with the attachment, in order to make it conform to the final shape of the profile of the blade.

Description

BRIEF DESCRIPTION OF THE FIGURES

[0036] Further characteristics and advantages of the invention will become apparent from the following detailed description, for the understanding of which reference is made to the annexed drawings in which:

[0037] FIG. 1 is a schematic perspective view of a turbine engine of the Open Rotor type concerned by the invention;

[0038] FIG. 2 is a schematic side view of a blade according to the prior art for the propeller of the turbine engine of FIG. 1;

[0039] FIG. 3 is a schematic side view of a blade according to the invention for the propeller of the turbine engine of FIG. 1;

[0040] FIG. 4 is a schematic side view of the spar inserted into the blade in FIG. 3 with its attachment to the root of the blade;

[0041] FIG. 5a is a schematic cross-sectional view of the blade of FIG. 3 near the root (section along line A in FIG. 6);

[0042] FIG. 5b is a schematic cross-sectional view of the blade of FIG. 3 in the body of the blade away from the root (section along line B in FIG. 6);

[0043] FIG. 6 is a schematic side view of the blade in FIG. 3 showing its internal structure; and

[0044] FIG. 7 is a schematic view in the longitudinal direction of the constitution of a preform of the skin of the blade of FIG. 3 during the step of weaving this preform.

DETAILED DESCRIPTION OF THE INVENTION

[0045] With reference to FIG. 3, a composite propeller blade 5 according to the invention comprises a woven skin 6, here made of carbon fibres, which forms the aerodynamic surface of the blade 5, in contact with the air moved by the propeller. The skin 6 forms an intrados face and an extrados face of the blade 5 connecting to the leading edge 7 and to the trailing edge 8. The weaving of the skin 8 comprises warp strands, oriented longitudinally from the root 9 towards the head 10, and weft strands, oriented transversely along the chord of the blade 5. A good path of the weft strands is ensured by means of an interlocking method, in particular at the level of the leading edge 7, to ensure a good link between the extrados and intrados portions of the skin 8 at this level. Further characteristics of the weaving of the skin 6 are described later in the description of the method of manufacturing the blade 5.

[0046] The profile of the blade 5 is relatively thick at the level of the root 9 and becomes thinner along the span towards the head 10 of the blade. The blade 5 in the example has almost no deflection, but other examples may have positive or negative deflections. Furthermore, the blade 5 is shown here in radial projection, but it may have a tilt and a twist about the radial axis, which are not shown in the figure.

[0047] According to the invention, an attachment 11, also referred to as root, of cylindrical shape around a radial axis R is inserted partly between the extrados and intrados faces of the woven skin 6, at the root 9 of the blade 5. The portion 12 of the attachment 11 inserted between the two faces of the skin 6 is bell-shaped, flaring out in the direction of the head 10 of the blade 5. A second portion 13, outside the blade profile defined by the woven skin 6, is shaped to mount the blade 5 in a propeller hub and allow the blade to be rotated about the radial axis R, to vary the pitch. Here, the second portion 13 of the attachment 11 is designed to be mounted on a device with two rolling lines and to act as an inner ring. Schematically, a recess 14 at the bottom of the attachment 11 is intended for the inner ring of a first row of balls (large rolling which absorbs the centrifugal forces) and a recess 15 near the bell-shaped portion 12 is intended for the inner ring of a second row of balls (small rolling which absorbs aerodynamic forces).

[0048] It is possible to reverse this device by positioning the rolling taken up the radial forces above and a rolling taken up the secondary forces below. This choice can be proposed for integration constraints.

[0049] The attachment 11 is made of a metallic material, preferably martensitic steel, to take up the forces between the blade 5 and the hub of the propeller.

[0050] Also, according to the invention, a spar 16 attached to the bell portion 12 of the attachment 11 extends over a large portion of the span of the blade 5 between the intrados and extrados faces of the skin 6. In the example shown, it extends to about two-thirds of the span. Depending on the design choices, the length of the spar 16 will preferably be between 30% and 70% of the span of the blade 5, with 0% corresponding to the radius of the blade root at the level of the leading edge 9 of the blade and 100% corresponding to the radius of the head 10 at the level of the leading edge. This spar 16 is a hollow tube made of braided carbon fibre. As shown in FIGS. 5A and 5B, it has an almost circular cross-section at the level of the root 9 of the blade 5, where the thickness of the profile allows, and its cross-section gradually flattens out to arrive in the areas where the profile of the blade 5 is thin, in the body of the blade 5.

[0051] With reference to FIG. 4, the spar 16 is inserted around the bell portion 12 of the attachment 11 and is here strapped around the latter by a fibreglass coiling 17. This strapping allows to retain the blading against centrifugal force. The glass fibre is an example here, the coiling must be made with a fibre that the person skilled in the art will choose according to the mechanical constraints present.

[0052] Furthermore, with reference to FIG. 5A, a foam shape 18 here fills the interior of the spar 16. Similarly, a foam 19 fills the space between the spar and the skin of the blade. In FIG. 6, this free volume filled with foam 19 is represented within its limits in the longitudinal and transverse directions by the dotted line 20.

[0053] The assembly is injected with resin and polymerised to obtain its mechanical strength by a known method of resin transfer moulding (RTM). Further characteristics of the blade 5 are described in the following description of the manufacturing method for the blade, which uses the RTM method.

[0054] In a step prior to the method itself, the metallic material attachment 11, with its bell portion 12, can be machined by conventional methods.

[0055] The method then comprises two steps that can be performed in parallel.

[0056] The first of these two steps concerns the assembly of the preform of the spar 16 with the attachment 11.

[0057] It comprises the braiding of the preform for the spar 16, which is made with carbon fibres on an industrial braiding machine. The preform is a hollow tube open at both ends. The cross-section of the tube may be circular with a variable diameter, in particular to subsequently adapt the cross-section of the spar 16 to the variations in the thickness of the profile of the blade 5 along the span.

[0058] The preform of the spar 16 is then assembled with the bell portion 12 of the attachment. The assembly of the braided preform with the bell portion 12 is done by inserting the bell portion 12 into the preform of the spar 16 and then making a coiling 17 of glass fibre which has been described previously. These operations are preferably performed around a very cold bell portion 12 by forcing the bell portion 12 into the preform of the spar 16.

[0059] A previously machined foam part 18 can then be inserted into the preform of the spar 16. The function of this foam part 18 is to fill the cavity left empty inside the braided preform of the spar and to guarantee the final shape of the spar 16 during the shaping of the blade 5. Note that the foam shape 18 may be non-cylindrical. In this case, the preform of the spar 16 can be crushed in the portions of the vane where the profile is thin, as described above. The foam part 18 may stop before the free end of the preform of the spar 16.

[0060] At the end of this step, a secured assembly is obtained comprising the attachment 11 and the preform of the spar 16, integrating the foam shape 18 that the spar will surround in the blade.

[0061] The second of the first steps comprises the weaving of the woven preform for the skin 6.

[0062] With reference to FIG. 7, as previously indicated, this is essentially a conventional weaving with warp strands 21 running in the direction of the span and weft strands 22 running around the profile in a substantially perpendicular direction. The weaving of the preform is realized with carbon fibres on an industrial loom. The linking in the thickness or “interlocking” is performed by making a particular weft strand path 22 between the warp strands 21.

[0063] With reference to FIG. 7, the preform of the skin 6 consists of a lower portion 23, starting from the root 9, at the level of which there is an unbinding 24 and an upper portion 25, comprising the head 10, which is monolithic. The unbinding 4 is here a longitudinally extending line, along which the weft strands are stopped, so that the preform can be opened along this line to let the preform of the spar 16 pass.

[0064] FIG. 6 shows a possible form of unbinding 24 with a constant skin thickness 6 in the unbound portion and an unbinding at the trailing edge 8. This unbinding 8, which is also shown in the cross-sections of FIGS. 5A and 5B, serves only to open the preform of the skin 6 for insertion of the spar. The shape of the unbinding 24 is chosen so as to guarantee a good insertion of the spar. Furthermore, depending on the strategy in terms of skin thickness in the unbound portion, the shape of the unbinding 24 is more or less extensive.

[0065] For these reasons, the unbinding is done at the level of the trailing edge and not, for example, at the leading edge, the woven preform being interwoven or interlocked all along the leading edge 7.

[0066] To allow the spar to be inserted, the unbinding 24 covers the area where the latter is integrated.

[0067] The lower portion 23, being intended to surround the spar, therefore has a span at least equal to that of the spar 16. The upper portion 25 is monolithic. On the one hand, there is no unbinding of the skin 6, and on the other hand, the thickness of the skin 6 does not allow to leave a gap between the two lateral faces, as this portion is entirely made of a carbon fibre weaving. The dashed line 26 in FIG. 6 shows the boundary, seen from the side, of this portion 25.

[0068] With reference to FIG. 7, the weaving strategy consists in starting to weave the raw preform of the skin 6 through the root 9 by integrating all the warp strands 21 necessary to weave the part in a kind of dummy root 27.

[0069] Once the preform is woven, trimming of the floats is realized and then a water jet cut to drop the dummy root 27. The result is an unbinding 24 opening at the root 9, ready to receive the assembly of the attachment 11 and the preform of spar 16.

[0070] As is the case with a conventional preform, the raw preform, once the dummy root 27 has been dropped, still has excess lengths. There are excess lengths at the level of the head, the leading edge and the trailing edge. On the lower portion of the skin 6, the ability to rework post-injection is limited due to the assembling on the spar and the bell. However, there may be a small over-length which will be taken up except in the immediate vicinity of the root 9.

[0071] After the first two steps, a third step consists of performing a shaping of the blade 5 and the injection.

[0072] The attachment 11, preform of the spar 16 and foam shape 18 assembly is inserted into the woven preform of the skin 6 at the level of the unbinding 24. A pre-machined foam structure 19 may be used at the interface between the preform of the skin 6 and the preform of the spar 16. The geometry of this interface part 19 can be designed to ensure the centrifugal holding of the skin 6.

[0073] The assembly is then injected and polymerised using the RTM method to obtain the blank of the blade 5.

[0074] The last step in the manufacturing method is clipping and finishing.

[0075] It should be noted that during the polymerisation, flashes of resin may occur on the over-lengths. They are eliminated during the rework, which comprise the clipping of the leading edge 7 and the trailing edge 8, as well as the trimming of the blade head 10.

[0076] The step also normally comprises rework at the level of the lower portion of the blade (on the hub line), which must be done precisely because of the assembling with the attachment 11.

[0077] Optionally, the method is completed by gluing a leading edge and/or a trailing edge fitted and a protective film to the skin.