Dawn including added spoilers

Abstract

Blade comprising attached spoilers. The invention relates to a blade (110) made of metallic material for an aircraft turbomachine, said blade (110) comprising a root (111) and an aerodynamic blade (114) extending between a root end and a tip end, at least one of the ends comprising at least one assembly portion (112m, 112v) extending in the upstream or downstream direction, the blade (110) further comprising at least one spoiler (113m, 113v) attached to one of the assembly portions (112m, 112v) of the blade (110) and extending in the upstream or downstream direction. Figure for the abstract: Fig. 2

Description

Title of the invention: Blade comprising attached spoilers technical field

[0001] The present invention relates to the general field of movable or fixed blades for an aircraft turbomachine. Previous technique

[0002] An axial turbine of a turbomachine typically consists of a series of stages arranged one behind the other. Each stage comprises a bladed runner corresponding to a rotor, and a bladed distributor corresponding to a stator. The runner conventionally consists of an annular disk on which a plurality of so-called "moving" blades are fixed. The bladed distributor conventionally comprises a plurality of so-called "fixed" blades.

[0003] A movable or fixed blade generally consists of a foot and an aerodynamic blade extending substantially perpendicularly to the turbine axis between a foot end and a tip end. The foot end generally includes a platform, and the tip end generally includes a heel.

[0004] The platform or heel is conventionally extended by an upstream spoiler in the upstream direction and by a downstream spoiler in the downstream direction, the terms "upstream" and "downstream" being defined with respect to the direction of gas flow in the turbomachine. The purpose of the spoilers is to channel the gas flow in the duct in order to limit aerodynamic losses. During operation, the spoilers of the moving blades may come into contact with certain parts of the stator, such as the distributor or the labyrinth seal. Similarly, the spoilers of the fixed blades may come into contact with certain parts of the rotor.

[0005] When several blades are fixed on the disc or rotor, their blades are generally arranged circumferentially edge to edge so as to form a circumferential ring delimiting a surface of revolution around the axis of rotation of the wheel.

[0006] These blades are generally produced by casting, by pouring the material from the tip or foot end of the blade, for example from the heel. Thus, the blades are produced entirely in one piece by casting, as described for example in documents FR 2 995 343 A1 and FR 3 074 217 A1

[0007] The blades are subjected to high temperatures, and suitable materials must be used to ensure good temperature resistance of the blades. However, materials of this type generally exhibit very poor flowability. Thus, since the spoilers are far from the point of material introduction into the mold because they are cast, they are more likely to have casting defects.

[0008] Document FR 3 052 088 A1 partially addresses these drawbacks by proposing a foundry mold with auxiliary channels for supplying molten metal to the ends of the spoilers. However, this solution does not eliminate all casting defects that may occur on the spoilers.

[0009] Furthermore, certain surfaces of the spoilers may be machined after their casting, particularly the surfaces intended to be in contact with the spoilers of adjacent blades. Consequently, the spoilers are particularly delicate portions of the blade to manufacture, and highly susceptible to causing the entire blade to be rejected due to casting and / or machining defects.

[0010] Furthermore, the blades are also components subject to a significant risk of breakage or wear during operation, due to their proximity to the stator or rotor. Moreover, the nickel-based alloy conventionally used to manufacture the blade, in order to ensure its resistance to thermomechanical stresses, has very low resistance to friction and wear. Consequently, the blades are particularly susceptible to damage or breakage, necessitating the replacement of the entire blade assembly. Description of the invention

[0011] The present invention aims to remedy the aforementioned drawbacks. To this end, the invention proposes a blade made of metallic material for an aircraft turbomachine, said blade comprising a foot and an aerodynamic blade extending between a tip end and a foot end of the blade, at least one of the ends of the blade comprising at least one assembly portion extending in the upstream or downstream direction, the blade further comprising at least one spoiler attached to one of the assembly portions and extending in the upstream or downstream direction.

[0012] Thus, by manufacturing the spoiler(s) separately from the rest of the blade, the risk of manufacturing defects on the spoilers is reduced, thereby limiting the proportion of rejects during production. Furthermore, if defects persist despite independent manufacturing, only the spoiler is discarded, not the entire blade.

[0013] Furthermore, since the blade is no longer entirely produced during the same foundry operation, it is possible to produce the spoilers in a different material from the rest of the blade, more suitable and resistant to wear.

[0014] Finally, since the spoilers are separate from the rest of the blade, they are easier to replace if damaged during manufacturing, assembly, or operation. Therefore, it is no longer necessary to replace the entire blade when only the spoiler is damaged.

[0015] According to a particular feature of the invention, the foot end comprises a platform including at least one of the assembly portions intended to to receive a spoiler.

[0016] According to another particular feature of the invention, the head end has a heel comprising at least one of the assembly portions intended to receive a spoiler.

[0017] Thus, the invention can provide a movable blade made of metallic material for a wheel of an aircraft turbomachine, said blade comprising a foot and an aerodynamic blade extending between a heel and a platform, said and / or said heel comprising at least one assembly portion extending in the upstream or downstream direction, the blade further comprising at least one spoiler attached to one of the assembly portions of the platform and / or the heel and extending in the upstream or downstream direction.

[0018] Consequently, the vane can typically include one to four vanes.

[0019] According to another particular feature of the invention, the foot, the aerodynamic blade, the foot end and the tip end of the blade are made of a nickel-based alloy and wherein the spoiler(s) are made of a cobalt-based alloy.

[0020] Thus, a nickel-based alloy is retained for the parts of the blade subjected to the greatest thermomechanical stress, while a cobalt-based alloy, which resists friction, is used for the spoilers. Any platform or heel is then made of a nickel-based alloy.

[0021] According to another particular feature of the invention, the spoiler(s) are fixed to the assembly portion(s) of the blade by at least one pin.

[0022] The use of a pin system allows the spoilers to be easily mounted or dismounted, which facilitates manufacturing and repair.

[0023] According to another particular feature of the invention, the spoiler(s) are fixed to the assembly portion(s) of the blade by a layer of brazing.

[0024] The invention further proposes a method for manufacturing a blade according to the invention, the method comprising:

[0025] - the manufacture of the foot, the aerodynamic blade, the foot end and of the end of the blade by casting,

[0026] - the manufacture of the spoiler(s),

[0027] - the assembly of the spoiler(s) with the assembly portion(s) of the blade.

[0028] Thus, the possible heel or the possible platform are made by casting in one go with the foot and the aerodynamic blade of the blade.

[0029] The invention also proposes a method for repairing a blade according to the invention, said blade comprising at least one defective spoiler, the method comprising:

[0030] - the complete removal of the defective spoiler(s) by breaking the connection between the or the assembly portions of the blade and said spoiler(s),

[0031] - the assembly of one or more non-defective spoilers with the portion(s) assembly of the blade.

[0032] The invention finally proposes a movable wheel for an aircraft turbomachine, comprising a disc carrying on its periphery an annular row of blades according to the invention. Brief description of the drawings

[0033] [Fig-1] Fig. 1 is an axial cross-sectional view of a turbine portion of a turbine aeronautical machine.

[0034] [Fig.2] The [Fig.2] is a schematic 3D view of a blade according to a first embodiment of the invention.

[0035] [Fig.3] The [Fig.3] is a schematic 3D view of the end of a blade according to a second embodiment of the invention.

[0036] [Fig.4] The [Fig.4] is a schematic 3D view of the end of a blade according to a third embodiment of the invention.

[0037] [Fig.5] The [Fig.5] is a diagram representing the manufacturing process according to the invention.

[0038] [Fig.6] The [Fig.6] is a diagram representing the repair process according to the invention. Description of the implementation methods

[0039] The present description and the associated figures are based on the example of winglets attached to a moving blade platform of a low-pressure turbine. It is of course not outside the scope of the invention if the winglet(s) are attached to a portion of a blade of another type of turbomachine, for example, to a portion of a counter-rotating turbine blade, as described, for example, in document FR2942273. Nor is it outside the scope of the invention if the winglets are attached to a fixed blade, for example, of a distributor.

[0040] Nor does it depart from the scope of the invention if the spoiler(s) are attached directly to the foot of the blade or, more generally, to a part of the foot end of the blade. Nor does it depart from the scope of the invention if the spoiler(s) are attached to a part of the tip end of the blade, for example, to a possible blade heel.

[0041] Figure 1 is a schematic representation of a turbine portion of a prior art turbomachine. The turbine portion shown is a low-pressure turbine 1, which comprises a succession of rotating blades 110 and stationary blade distributors 120 in alternating arrangement. Thus, the rotating blades 110 are arranged between the stationary blades 120 of the turbine 1.

[0042] The rotor of the low-pressure turbine consists, in this example, of four turbine discs 101 bolted together by their cylindrical shells 102 and carrying on their periphery, by means of sliding links 103, the feet 111 of the movable blades 110. The rotor further includes sealing structures 104, comprising cylindrical labyrinth flanges which surround the shells 102 of the rotating discs securely and provide a seal with the fixed blades 120.

[0043] As illustrated in Figures 1 and 2, each movable blade 110 comprises a foot 111, an aerodynamic blade 114, a foot end comprising a platform 112 and a head end comprising a heel 115.

[0044] The heel 115 of the blade 110 can take the form of a plate comprising at least one slat 116, for example two slats 116 as illustrated in figures 1 and 2. The aerodynamic blade 114 extends between the heel 115 and the platform 112 of the blade 110.

[0045] The foot 111 of the blade 110 includes an attachment portion 111a which allows the blade 110 to be assembled to the rotor disc of the turbine. This attachment portion 111a is typically bulbous or fir-tree shaped and is designed to fit into a complementary recess formed in the rotor disc of the low-pressure turbine.

[0046] The platform 112 of the blade 110 extends from the upper surface to the lower surface of the blade 110. The platform 112 of the blade 110 further comprises an upstream assembly portion 112m and a downstream assembly portion 112v. The upstream-downstream direction corresponds to the direction of gas flow in the turbomachine. Of course, the invention remains within the scope of the invention if the blade platform comprises only one assembly portion, either upstream or downstream.

[0047] The upstream assembly portion 112m extends upstream from the upstream end of the platform 112 of the blade 110 and the downstream assembly portion 112v extends downstream from the downstream end of the platform 112 of the blade 110.

[0048] The heel of the blade could also include an upstream assembly portion and / or a downstream assembly portion.

[0049] The movable blade 110 further comprises an upstream spoiler 113m and a downstream spoiler 113v. It is of course not outside the scope of the invention if the blade comprises only one spoiler, upstream or downstream. Each spoiler 113m, 113v comprises an assembly portion by which it is assembled to an assembly portion 112m, 112v of the platform 112 of the blade 110. It is also not outside the scope of the invention if the blade comprises two upstream spoilers, one attached to the foot end of the blade, for example attached to a possible platform of the blade, the other attached to the tip end of the blade, for example attached to a possible heel of the blade. Similarly, the invention remains within the scope of the invention if the blade includes two downstream spoilers, one attached to the foot end of the blade, for example attached to a possible platform of the dawn, the other related to the end of the head of the dawn, for example related to a possible heel of the dawn.

[0050] Thus, each beak 113m, 113v corresponds to a portion of assembly 112m, 112v of the blade 110. Each beak 113m, 113v belongs to only one single blade.

[0051] Within the framework of the invention, it is considered that the spoilers 113m, 113v are not parts of the platform 112 of the blade 110. More generally, it is considered that the spoilers are not parts of the foot end or the head end of the blade.

[0052] The upstream spoiler 113m extends upstream from the upstream end of the platform 112 of the blade 110 and the downstream spoiler 113v extends downstream from the downstream end of the platform 112 of the blade 110. The spoilers 113m, 113v are in the form of plates projecting from the platform 112 of the blade 110. Preferably, each spoiler 113m, 113v extends in line with the corresponding assembly portion 112m, 112v of the platform 112 of the blade 110.

[0053] The upstream 113m and downstream 113v spoilers serve, in cooperation with elements of the stator of the compressor or gas turbine, to limit by baffle effect the passage of gas from the inside of the compressor or turbine radially towards the intrados and extrados of the blades 110, and conversely from the intrados and extrados of the blades 110 to the inside of the compressor or turbine.

[0054] Each spoiler may include a projecting hook adapted to form an axial stop for the rotor sealing structures. The hook may extend under the lower face of the spoiler, i.e., the face facing the rotor.

[0055] If the hooks are not located on the spoilers, each platform may include a projecting hook adapted to form an axial stop for the rotor sealing structures. The hook may extend under the lower face of the platform on the upstream or downstream side, i.e., the face facing the rotor.

[0056] The manufacture of such a movable blade 110 according to the invention is described in relation to [Fig. 5]. It will be readily understood that the descriptions of the manufacturing and repair methods presented below are particular examples of the invention in which the spoiler is attached to a blade platform. Thus, the term "platform" can be equivalently replaced by "blade tip end" or "blade foot end." Similarly, the term "heel" can be equivalently replaced by "blade tip end."

[0057] The wingtip 115, the aerodynamic blade 114, the platform 112, and the foot 111 of the blade 110 are produced in a step E1, and the wingtip(s) 113m, 113v are produced in a step E2. Steps E1 and E2 can therefore be carried out independently of each other. Steps E1 and E2 can be carried out one after the other, or simultaneously.

[0058] The flange 115, the aerodynamic blade 114, the platform 112, and the foot 111 of the blade 110 can be produced using a well-known casting method, for example, by lost-wax casting. The material used for producing the flange 115, the aerodynamic blade 114, the platform 112, and the foot 111 of the blade 110 can be a nickel-based alloy. For example, the flange 115, the aerodynamic blade 114, the platform 112, and the foot 111 of the blade 110 can be made of materials such as DS200, IN100, or René® 77. The material(s) used must be suitable for the thermomechanical stresses experienced by the blade 110.

[0059] The casting of the assembly comprising the heel 115, the aerodynamic blade 114, the platform 112 and the foot 111 can be carried out according to the process described in document FR 3 002 870 A1 or in document FR 2 875 425 A1

[0060] The 113m and 113v spoilers can be manufactured using conventional methods, such as casting, plastic deformation, and / or machining, or using additive manufacturing methods. The material used for the 113m and 113v spoilers can be a cobalt-based alloy. For example, the 113m and 113v spoilers can be made from materials such as Haynes® 188, MAR-M-509, or HS25. The material(s) used are preferably resistant to friction and wear.

[0061] Once manufacturing steps E1 and E2 have been completed, the manufactured spoiler(s) 113m, 113v are assembled to the rest of the blade 110 in a step E3.

[0062] Each spoiler 113m, 113v is assembled by its assembly portion to at least one assembly portion 112m, 112v of the platform 112 of the blade 110. Several geometries are possible for the assembly edges. The geometry of the assembly edge of the spoiler 113m, 113v is preferably complementary to the geometry of the corresponding assembly edge 112m, 112v of the platform 112.

[0063] According to a first embodiment of the invention illustrated in [Fig. 2], at least a portion of the assembly portion of the spoiler 113m, 113v overlaps at least a portion of the corresponding assembly portion 112m, 112v of the platform 112. The overlap occurs in the direction perpendicular to the axis of the turbomachine. It is, of course, not beyond the scope of the invention if the assembly portion of the platform at least partially overlaps the assembly portion of the spoiler, or if the two assembly portions of the platform and the spoiler overlap alternately.

[0064] This configuration is particularly suited to a pin fastening system 10, the pin(s) 10 being positioned so as to pass through the assembly portion of the spoiler 113m, 113v and the assembly portion 112m, 112v of the platform 112 at the point where the assembly portions overlap. This system is particularly advantageous as it allows for easy mounting of the spoiler 113m, 113v on the assembly portion 112m, 112v, while allowing easy removal of the spoiler 113m, 113v from the assembly portion 112m, 112v in case of a defect or damage to the spoiler 113m, 113v. In this configuration, the pin can be mounted tightly in the well-known way by tightening.

[0065] According to a second embodiment of the invention illustrated in [Fig. 3], the edge of the assembly portion of the spoiler 213m, 213v has a right-angled "U" shape that fits into the corresponding assembly portion 212m, 212v of the blade platform 212, which has a geometry complementary to the right-angled "U". The "U" shape facilitates positioning between the spoiler 213m, 213v and the blade platform 212.

[0066] If the platform of the blade has a hook, the hook can be located between the arms of the "U", that is to say inside the "U".

[0067] The invention remains within the scope of the invention if the edge of the platform assembly portion has a "U" shape, and the spoiler assembly portion has the complementary shape. Nor does the invention depart from the scope of the invention if the "U" is not right-angled, that is, if the arms of the "U" do not form a right angle with the base of the "U".

[0068] According to a third embodiment of the invention illustrated in [Fig.4], the edge of the assembly portion of the spoiler 313m, 313v has a right “Z” shape which fits into the corresponding assembly portion 312m, 312v of the blade platform 312, which has a geometry complementary to the right “Z”.

[0069] The invention remains within the scope of the invention if the edge of the platform assembly portion has a "Z" shape, and the spoiler assembly portion has the complementary shape. Nor does the invention depart from the scope of the invention if the "Z" is not a right angle, that is, if the middle line of the "Z" does not form a right angle with the upper and lower lines of the "Z".

[0070] In each of the embodiments described above, the assembly of the assembly portion of the spoiler 113m, 113v, 213m, 213v, 313m, 313v and of the corresponding assembly portion 112m, 112v, 212m, 212v, 312m, 312v of the platform 112, 212, 312 can be carried out by brazing. The creation of a brazing layer makes it possible to securely bond the spoiler 113m, 113v, 213m, 213v, 313m, 313v to the platform 112, 212, 312 of the blade, without needing to alter the spoiler 113m, 113v, 213m, 213v, 313m, 313v or the platform 112, 212, 312.

[0071] In case of damage or defect on the moving blade, the moving blade can be repaired according to the repair method of the invention, described in relation to [Fig.6].

[0072] According to a first step E10, the entire damaged spoiler(s) are removed. Then, according to a second step E20, a new spoiler, or an old repaired spoiler, on the dawn.

[0073] If the assembly of the spoiler(s) 113m, 113v on the platform 112 is achieved by means of one or more pins 10, the entire spoiler 113m, 113v is disassembled by removing the pin(s) 10. The pin(s) 10 can be easily removed by applying pressure, for example, with a hammer. Then, another spoiler is mounted on the assembly portion 112m, 112v of the blade platform 112 110 by replacing the pin 10. The geometry and dimensions of the assembly portion of the new spoiler are preferably substantially identical to the initial geometry and dimensions of the removed spoiler.

[0074] If the assembly of the spoiler(s) 213m, 213v, 313m, 313v onto the platform 212, 312 is carried out by brazing, the junction between the spoiler assembly portion and the platform assembly portion can be heated to melt the brazing layer. When the spoiler is separated from the rest of the blade, the brazing residue is cleaned from the platform assembly portion. The spoiler can also be separated from the rest of the blade by machining. Another spoiler can then be brazed onto the blade platform assembly portion. The geometry and dimensions of the assembly portion of the new spoiler are preferably substantially identical to the initial geometry and dimensions of the removed spoiler.

[0075] After the assembly of a spoiler 113m, 113v, 213m, 213v, 313m, 313v on a portion of assembly 112m, 112v, 212m, 212v, 312m, 312v of the platform 112, 212, 312 of the blade, an adjustment can be made to ensure the regularity of the flow of the gas on the vein side, or on the clearances with the spoilers of the adjacent blades.

[0076] The method of mounting a spoiler on the blade platform and the method of repairing a blade in which at least one of the spoilers is damaged are therefore very easy to implement, with high repeatability.

Claims

Demands

1. Blade (110) of metallic material for an aircraft turbomachine, said blade (110) comprising a foot (111) and an aerodynamic blade (114) extending between a head end and a foot end of the blade (110), at least one of the ends of the blade (110) comprising at least one assembly portion (112m, 112v) extending in the upstream or downstream direction, the blade (110) further comprising at least one spoiler (113m, 113v) attached to one of the assembly portions (112m, 112v) and extending in the upstream or downstream direction.

2. Blade (110) according to claim 1, wherein the foot end comprises a platform (112) including at least one of the assembly portions (112m, 112v) intended to receive a spoiler (113m, 113v).

3. Blade according to claim 1 or 2, wherein the head end has a heel comprising at least one of the assembly portions intended to receive a spoiler.

4. Blade (110) according to any one of claims 1 to 3, wherein the foot (111), the aerodynamic blade (114), the foot end and the tip end of the blade (110) are made of a nickel-based alloy and wherein the spoiler(s) (113m, 113v) are made of a cobalt-based alloy.

5. Blade (110) according to any one of claims 1 to 4, wherein the spoiler(s) (113m, 113v) are fixed to the assembly portion(s) (112m, 112v) of the blade (110) by at least one pin (10).

6. Blade according to any one of claims 1 to 5, wherein the spoiler(s) (213m, 213v, 313m, 313v) are fixed to the assembly portion(s) (212m, 212v, 312m, 312v) of the blade by a layer of brazing.

7. Method of manufacturing a blade (110) according to any one of claims 1 to 6, the method comprising: - (E1) manufacturing the foot (111), the aerodynamic blade (114), the foot end and the tip end of the blade (110) by casting, - (E2) manufacturing the spoiler(s) (113m, 113v), - (E3) assembling the spoiler(s) (113m, 113v) with the assembly portion(s) (112m, 112v) of the blade (110).

8. Method for repairing a blade according to any one of the claims

9. indications 1 to 6, said awl comprising at least one defective spoiler, the process comprising: - (E10) the complete removal of the defective spoiler(s) by breaking the connection between the assembly portion(s) of the blade and said spoiler(s), - (E20) the assembly of one or more non-defective spoilers with the assembly portion(s) of the blade. Movable wheel for an aircraft turbomachine, comprising a disc carrying on its periphery an annular row of blades (110) according to any one of claims 1 to 6.