METHOD FOR MANUFACTURING A TURBOMACHINE COMPRESSOR BLADE BY COMPACTING

Abstract

The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps:installing primary pins (26) comprising a material other than a titanium-based alloy in primary bores (20) of a core, the primary bores forming at least one polygon, and installing a secondary pin made of titanium-based alloy in a secondary bore of the core;producing a stack (2) of a suction-face sheet (4), a core (14) and a pressure-face sheet (6);compacting the stack;removing the primary pins (26) from the primary bores (20);removing the secondary pin from the secondary bore; andtaking the core (14) away from the stack.

Claims

1-11. (canceled)

12. A method for manufacturing a turbomachine blade, the method comprising: installing primary pins comprising a material other than a titanium-based alloy in primary bores of a core, the primary bores forming at least one polygon, and installing a secondary pin made of a titanium-based alloy in a secondary bore of the core; making a stack of an upper wing skin, the core and a lower wing skin; pressing the stack; removing the primary pins from the primary bores; removing the secondary pin from the secondary bore; and taking the core out of the stack.

13. The method as claimed in claim 12, wherein at least one of the primary and secondary pins comprises a shank having a longitudinal shaft and a head protruding from the shank along a direction radial to the shaft.

14. The method as claimed in claim 1, comprising, after pressing the stack, performing in order: immobilizing the stack with respect to a support; removing the primary pins while the stack is immobilized on the support; immobilizing the stack on a tooling by attaching members traversing the primary bores; and while the stack is immobilized, removing the secondary pin and taking out the core.

15. The method as claimed in claim 12, wherein the secondary bore extends inside the polygon.

16. The method as claimed in claim 12, wherein the stack comprises a straight longitudinal edge, the secondary bore and a first of the primary bores extending in one and the same plane perpendicular to the longitudinal edge, the secondary bore extending between the first of the primary bores and the edge.

17. The method as claimed in claim 16, wherein the secondary bore and the first of the primary bores are separated by a distance of at least 10 mm.

18. The method as claimed in claim 12, wherein the primary pins are odd in number.

19. The method as claimed in claim 12, wherein the primary pins are at least two in number.

20. The method as claimed in claim 12, wherein the step of pressing the stack implements Hot Isostatic Pressing.

21. A stack comprising: an upper wing skin; a core; a lower wing skin; primary pins comprising a material other than a titanium-based alloy, the primary pins being housed in primary bores of the core and forming at least one polygon; and a secondary pin made of a titanium-based alloy, wherein the primary pins are housed in a secondary bore of the core.

22. The stack as claimed in claim 21, wherein at least one of the primary and secondary pins comprises a shank having a longitudinal shaft and a head protruding along a direction radial to the shaft.

Description

DESCRIPTION OF THE FIGURES

[0051] We will now describe an embodiment of the invention by way of non-limiting example with reference to the drawings wherein:

[0052] FIG. 1 is an exploded perspective view showing the three layers of the stack in a method of implementation of the method of the invention;

[0053] FIGS. 2 to 4 are three views of the core of the stack of FIG. 1;

[0054] FIG. 5 is a perspective view showing several stacks after pressing in the context of this method of implementation;

[0055] FIGS. 6 and 7 are views showing several steps of this method of implementation of the method;

[0056] FIG. 8 is a view of a tooling used in the context of this implementation,

[0057] FIGS. 9 and 10 show the stack attached to this tooling, and

[0058] FIG. 11 shows axial views of one of the pins before and after crimping.

[0059] We will therefore describe a method of implementation of the method of the invention which concerns the manufacturing of a turbomachine compressor blade, for example of an airplane turbojet engine. The blade 2, shown in the form of the stack in FIG. 1, comprises an upper wing skin or wall 4, a lower wing skin or wall 6, a leading edge 10 and a trailing edge 8.

[0060] In a first step, the core only is considered.

[0061] The core 14 is for example made of the material marketed under the brand name Waspaloy by United Technologies Corp.

[0062] As illustrated in FIG. 2 which shows only the core, the core comprises primary bores which are here odd in number, five in number in this example. Four of them are aligned roughly parallel to a straight longitudinal lower edge 22 of the core, at a short distance from this edge.

[0063] The fifth primary bore 20 extends in the center of gravity of the core, or in the vicinity of it, in the median area of one of the main faces of the core. If one considers the geometrical projection of each of the primary bores 20 on the longitudinal edge 22, these bores are evenly spaced along this edge. The two bores located at the ends of the row are located in proximity to the respective ends of this edge.

[0064] Bearing in mind that this fifth primary bore extends at a distance from the line defined by the four other primary bores, these five bores 20 together define several polygons formed by triangles. FIG. 3 thus visualizes the triangle 15 formed by the three primary bores 20 located in the median area of the core.

[0065] The core 14 also comprises a secondary bore 24 separate from the preceding ones. It is located inside this triangle 15, between on the one hand the line defined by the four aligned primary bores and on the other hand the fifth primary bore.

[0066] The secondary bore 24 and this fifth primary bore 20 extend in one and the same plane P perpendicular to the longitudinal edge 22, the secondary bore 24 extending between the fifth primary bore 20 and the edge 22. This plane P is visible in the section in FIG. 4. It is perpendicular to the plane of the figure. The secondary bore 24 and this primary bore are separated by a distance d of at least 10 mm indicated in FIG. 2.

[0067] The primary 20 and secondary 24 bores each traverse the core 14.

[0068] Five primary shouldered pins 26 are installed in the respective primary bores 20. These pins are made of a material other than a titanium-based alloy. They are for example made of a nickel-based material or made of the aforementioned material marketed under the brand name Waspaloy or made of one of those marketed under the brand name Inco by Special Metals Corporation. These pins 26 are used to close off the corresponding bores 20 of the core which are then used for the clamping of the stack during the machining that follows the pressing. The pins 26 are overlong, for example by 0.5 mm, with respect to the length of the bore 20 of the core to leave a visual imprint after pressing of the titanium coating around the core.

[0069] In addition, as illustrated in FIG. 11, the primary pins 26 are shouldered in order to cover a peripheral bearing surface on the core, located in the centerline of the bores on the upper wing skin side 4, as illustrated in the right-hand part of FIG. 11. More accurately, each primary shouldered pin 26 comprises a shank 40, here cylindrical, having a longitudinal shaft and a head 42 protruding from the shank along a direction radial to the shaft. The head 42 thus forms a flange.

[0070] A secondary pin 28 made of a titanium-based alloy, for example the alloy TA6V, is also installed in the secondary bore 24 of the stack. This pin is also shouldered. It makes it possible to create a point of affinity between the core 14 and the pin and allows for homogeneous withdrawal. It is welded to the core by diffusion welding. It is also dimensioned to be overlong, for example by 0.5 mm, with respect to the length of the bore of the core to leave a visual imprint after pressing.

[0071] Next, the upper wing skin 4, a core 14 and the lower wing skin 6 are stacked. The core 14 is interposed between the two skins 4 and 6 and will serve to define an inner volume of the blade at the level of its leading edge 8.

[0072] The bores are formed in the core 14 only, so that the pins are encapsulated in the lower and upper wing skins. The first step of the method is therefore the installation of the pins, the second step the stacking of the skins and the core, the third the pressing.

[0073] Next, the stack is pressed, here by carrying out Hot Isostatic Pressing (HIP). During this operation, the two skins closely fit the shape of the core 14 so that the core gives them their final shape. During the HIP, under the effect of pressure, the secondary pin 28 deforms and becomes crimp-fitted into the core. The same applies for the primary pins 26.

[0074] Stacks resulting from the pressing are illustrated in FIG. 5. It can be seen that, before and after the pressing, a stack 2 is present comprising: [0075] an upper wing skin 4, [0076] a core 14, [0077] a lower wing skin 6, [0078] primary pins 26 comprising a material other than a titanium-based alloy housed in the primary bores 20 of the core forming a polygon 15, and [0079] a secondary pin 28 made of a titanium-based alloy housed in a secondary bore 24 of the core.

[0080] After the pressing and prior to the withdrawal of the core, the pins must be removed, particularly those of the core, during the unpinning step.

[0081] To do this, the stack 2 is immobilized with respect to a non-illustrated support, after an operation of setting it on the support.

[0082] Then the primary pins 26 are removed from the primary bores 20. For this purpose, as illustrated in FIGS. 6 and 11, a first operation is carried out of machining the side of the stack bearing the heads of the pins. During this step, the titanium of the skin is cleared facing the pins 26 to free up their way out, over a volume contained between the face 19 of the core 14 against which the head 42 is bearing and the apex of the head. On this occasion, the head is removed.

[0083] Next, the pins 26 are tapped out to extract them from the core and from the stack, as illustrated in FIGS. 6 and 7.

[0084] Next, the stack 2 of the support is freed up and this time it is immobilized on a tooling 32 illustrated particularly in FIG. 8 by means of attaching members 34 traversing the respective primary bores 20 and the corresponding bores of a jig 36 of the tooling in order to rigidly attach the stack 2 to the jig 36. The primary bores 20 thus make it possible to create a frame of reference and areas of clamping of the stack. The areas of the face 19 initially located under the heads 42 thus also serve as a frame of reference.

[0085] While the stack is thus immobilized, the secondary pin 28 of the secondary bore 24 is removed by machining. For this purpose, the jig comprises an additional bore 38 visible in FIGS. 8 to 10 and coinciding with the secondary bore 28 of the stack. This additional bore makes it possible to introduce a tool for machining the secondary pin through the jig.

[0086] This removal can be carried out without difficulty and without compromising the integrity of the core since the pin can be located with accuracy. It is also possible to drill the titanium pin without the risk of impacting the core since the stable attachment of the stack 2 to the jig 36, procured by the arrangement of the primary bores 20 and the direct bearing on the face of the core, ensures perpendicularity between the main face 17 of the stack, visible in FIG. 6, and the centerline of this bore. This same attachment allows a robust and accurate straightening of the stack with respect to the main face 17 which serves as a reference face during the removal of the pin.

[0087] Once the secondary bore has been freed up, the core 14 can be removed from the stack and the coring in the strict sense can be performed, which makes it possible to separate the coating and the core.

[0088] The question arises of whether the choice of the position of the point of affinity between the titanium coating and the core has an effect on the geometry of the leading edge during the pressing. It has been found that this is not the case.

[0089] Although the invention is implemented here with an additional secondary pin by comparison with the prior art, the cost of this pin is negligeable in relation to the cost of production of the part.

[0090] Of course, many modifications may be made to the invention without departing from the scope thereof. The number of primary bores and pins may be modified as well as the number of secondary bores and pins as well as the arrangement of all these components.