Part to modify the profile of an aerodynamic jet

Abstract

A part to modify the profile of an aerodynamic jet, including: a first face configured to be secured on the aerodynamic jet, and a second face defining a modified aerodynamic jet profile, configured to modify an initial profile of the aerodynamic jet.

Claims

1. An aerodynamic jet for a turbomachine, having an initial axial profile defined along a longitudinal axis of the turbomachine, comprising: a part to modify the initial profile of the aerodynamic jet, including: a first face configured to be secured on the aerodynamic jet, and a second face defining a modified aerodynamic jet profile, configured to modify at least the initial axial profile of the aerodynamic jet, wherein the part to modify the initial profile of the aerodynamic jet includes a first structural portion that contours a curved surface of a guide blade of the aerodynamic jet, and a second structural portion that extends upstream from an upstream end of the guide blade and that is aligned along the longitudinal axis of the turbomachine.

2. The aerodynamic jet for the turbomachine according to claim 1, wherein the part to modify the initial profile of the aerodynamic jet extends along its largest dimension, on the aerodynamic jet, along the longitudinal axis of the turbomachine.

3. The aerodynamic jet for the turbomachine according to claim 1, wherein the first face of the part to modify the initial profile of the aerodynamic jet fits closely the initial axial profile of at least one portion of the aerodynamic jet.

4. The aerodynamic jet for the turbomachine according to claim 1, wherein the part to modify the initial profile of the aerodynamic jet further includes a groove to accommodate a binding band configured to maintain the part to modify the initial profile of the aerodynamic jet in position on the aerodynamic jet.

5. The aerodynamic jet for the turbomachine according to claim 1, wherein the part to modify the initial profile of the aerodynamic jet is made by stereolithography.

6. The aerodynamic jet for the turbomachine according to claim 1, comprising a plurality of parts to modify the initial profile of the aerodynamic jet, arranged in a juxtaposition relative to each other, transversely relative to the longitudinal axis of the turbomachine to ensure a continuity of the modified aerodynamic jet profile on at least one transverse section of the aerodynamic jet.

7. The aerodynamic jet for the turbomachine according to claim 1, wherein the aerodynamic jet is an outlet (OGV) or inlet (IGV) guide vane.

8. A turbomachine comprising the aerodynamic jet for the turbomachine according to claim 1.

9. A method for modifying a profile of an aerodynamic jet, comprising securing the part to modify the initial profile of the aerodynamic jet for the turbomachine according to claim 1 on the aerodynamic jet.

10. The method according to claim 9, further comprising smoothing at least at one intersection between the part to modify the initial profile of the aerodynamic jet and the aerodynamic jet.

11. The aerodynamic jet for the turbomachine according to claim 1, wherein a portion of the second face that is on the second structural portion includes a groove to accommodate a binding band configured to maintain the part to modify the initial profile of the aerodynamic jet in position on the aerodynamic jet.

12. The aerodynamic jet for the turbomachine according to claim 1, wherein a portion of the second face that is on the second structural portion includes a convex profile.

13. The aerodynamic jet for the turbomachine according to claim 1, wherein a portion of the second face that is on the first structural portion includes a concave profile.

14. The aerodynamic jet for the turbomachine according to claim 1, wherein a downstream end of the first structural portion does not extend past a downstream end of the guide blade of the aerodynamic j et.

15. The aerodynamic jet for the turbomachine according to claim 1, wherein the first structural portion includes a thickness in a radial direction that tapers toward a downstream end of the part to modify the initial profile of the aerodynamic jet.

16. The aerodynamic jet for the turbomachine according to claim 1, wherein the second structural portion includes a thickness in a radial direction that tapers toward an upstream end of the part to modify the initial profile of the aerodynamic jet.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The invention will be better understood upon reading the detailed description that follows, the non-limiting exemplary implementations thereof, as well as upon examining the schematic and partial figures of the appended drawings, wherein:

(2) FIG. 1 shows a perspective view of an exemplary part to modify according to the invention,

(3) FIG. 2 shows a perspective view of an exemplary aerodynamic jet including the parts to modify according to the invention,

(4) FIG. 3 is another perspective view of the aerodynamic jet of FIG. 2,

(5) FIG. 4 is a view along IV of FIG. 2, and

(6) FIG. 5 is an enlarged view of a portion of FIG. 4.

(7) In all these figures, identical references can represent identical or similar elements.

(8) Besides, the different portions represented in the figures are not necessarily drawn to a uniform scale, to make the figures more legible.

DETAILED EXPOSURE OF PARTICULAR EMBODIMENTS

(9) Exemplary embodiments of the part to modify and of an aerodynamic jet according to the invention will now be described in reference to FIGS. 1 to 5.

(10) FIG. 1 shows a perspective view of an exemplary part 1 to modify the profile of an aerodynamic jet 2 according to the invention.

(11) The part 1, also hereinafter called patch, comprises a first face 1a intended to be secured on the aerodynamic jet 2, and a second face 1b, opposite the first face 1a, which defines an aerodynamic jet profile modified relative to the initial profile of the portion of the aerodynamic jet 2 on which the first face 1a is intended to be secured.

(12) The first face 1a of the patch 1 can especially be coated with a glue to allow its securing to the aerodynamic jet 2.

(13) On the other hand, the patch 1 comprises a further groove 5 (or notch), which leads to both sides of the patch 1, to allow the positioning of an attachment strip or binding band 6 intended to create a mechanical support of the patch 1 on the aerodynamic jet 2. Such a mechanical support by the binding band 6 can especially be useful in case the patch 1 is unglued.

(14) The patch 1 can be made of any kind of material. Preferably, the patch 1 is made by a method of stereolithography. The method of stereolithography can especially allow any desired shape for the patch 1 to be made, and optionally a patch 1 made of several portions secured to each other to be provided, especially through gluing so as to adapt to any kind of desired profile for the aerodynamic jet 2.

(15) The materials made by stereolithography being particularly abrasion-sensitive and high temperature-sensitive, the turbomachine including a patch 1 can, if desired, be equipped with a filtering means for the air that will come into contact with the patch 1 to prevent abrasive dusts from coming into contact with the patch 1. Further, the patch 1 can be placed in a cold area of the turbomachine, especially in an area where the temperature is equal to or lower than 40? C.

(16) FIG. 2 shows a perspective view of an exemplary aerodynamic jet 2 comprising four patches 1 according to the invention.

(17) By way of example only, the aerodynamic jet 2 can be an inlet guide vane (IGV) disk, which comprises guide blades 3.

(18) The patches 1 can be arranged adjacent to each other, each patch 1 being sandwiched between two successive guide blades 3.

(19) The patches 1 can extend along their largest dimension L, on the aerodynamic jet 2, along the turbomachine longitudinal axis X, as can be seen in FIGS. 2, 3 and 4.

(20) The patches 1 can further be maintained in position on the aerodynamic jet 2 through gluing and also by a binding band 6, which can be seen in FIGS. 2 to 4, placed in the grooves 5 of the patches 1.

(21) In this example, the four patches 1 are identical. However, the aerodynamic jet 2 can comprise identical or different patches.

(22) As can be seen in FIGS. 3 and 4, the latter being a view along IV of FIG. 2, a smoothing can be provided in some areas of the patches 1 to allow a continuous reconstitution of the aerodynamic profile of the aerodynamic jet 2.

(23) Particularly, such a smoothing can be provided in upstream Z.sub.1 and downstream Z.sub.3 areas of the patches 1, as well as in the intersection areas Z.sub.2 between the patches 1 or between one patch 1 and the aerodynamic jet 2. The smoothing can also be provided at the areas Z.sub.4 where the binding band 6 is accommodated in the grooves 5 of the patches.

(24) The smoothing can for instance consists of adding an elastomeric material, especially an RN silicone elastomeric, so as to create a continuity between the patches 1 and/or a patch 1 and the aerodynamic jet 2 and/or between a groove 5 of a patch 1 and the binding band 6.

(25) FIG. 5 is an enlarged view of area A in FIG. 4, showing the smoothing carried out in an area Z.sub.1 upstream of a patch 1 at the intersection between the patch 1 and the aerodynamic jet 2.

(26) In this FIG. 5, adding an elastomeric material 7 is shown by the dotted lines and a surface continuity obtained between the patch 1 and the aerodynamic jet 2 can be observed, so as to reconstitute a continuous profile of the aerodynamic jet 2.

(27) Thus, thanks to such a part to modify or patch 1 according to the invention supplied with a modified aerodynamic profile on its second face 1b, the invention can allow easy and quick modification of the aerodynamic jet 2 profile, once the patch 1 is positioned thereon by its first face 1a.

(28) Particularly, the initial axial profile P.sub.a0 of the aerodynamic jet 2 (which can be seen in FIG. 4), which is defined along the longitudinal axis X of the turbomachine before the part to modify 1 is positioned, can be modified by adding the part to modify 1, said part having a second face 1b defining a modified axial profile P.sub.a1 (which can be seen in FIG. 4) for the aerodynamic jet 2.

(29) The initial profile of the aerodynamic jet 2 can be easily adapted to achieve the new desired profile by increasing the number of patches 1 as needed, which patches 1 can be placed or not next to each other and/or at least partially superimposed on each other.

(30) Of course, the invention is not limited to the exemplary embodiment that has just been described. Various modifications can be made by a person skilled in the art.

(31) The term including a must be understood as being a synonym of including at least one, unless otherwise specified.