阅读说明：本技术 用于飞行器涡轮发动机的叶片 (Blade for an aircraft turbine engine ) 是由 布鲁诺·马克-艾蒂安·卢瓦泽尔 斯蒂芬妮·艾琳·玛丽·德弗朗德尔 埃里克·杰克奎斯·德尔夸涅 于 2019-02-01 设计创作，主要内容包括：本发明涉及用于飞行器涡轮发动机的转子叶片(10),所述叶片具有堆叠轴线(X)并且一旦所述叶片已经牢固地连接到转子上就具有旋转轴线(A)。该叶片包括在内平台(19)与外平台(20)之间延伸的桨叶(16),该外平台支承至少一个突出的唇部(31,32),所述桨叶具有下表面(16a)和上表面(16b)。外平台包括下侧边缘(22)和上侧边缘(21),该下侧边缘和上侧边缘分别位于下表面(16a)一侧和上表面(16b)一侧并且被构造成以形状配合的方式与相邻叶片的互补的侧边缘(21,22)配合,所述侧边缘中的每一个侧边缘具有耐磨覆盖物(36)。本发明的旋转叶片的特征在于,下侧边缘的耐磨覆盖物在平台的基本直线的第一脊部(40)的一个壁(40a)上延伸以及在平台的第二脊部(42)的一个壁(42a)上延伸,所述第二脊部至少部分地在唇部(31)内延伸并且相对于第一脊部沿基本上平行于唇部的横向轴线(Z)的方向倾斜。(The invention relates to a rotor blade (10) for an aircraft turbine engine, said blade having a stacking axis (X) and an axis of rotation (A) once said blade has been firmly connected to the rotor. The blade comprises a blade (16) extending between an inner platform (19) and an outer platform (20) supporting at least one protruding lip (31, 32), the blade having a lower surface (16a) and an upper surface (16 b). The outer platform comprises a lower side edge (22) and an upper side edge (21) located on the side of the lower surface (16a) and on the side of the upper surface (16b), respectively, and configured to cooperate in a form-fitting manner with complementary side edges (21, 22) of adjacent blades, each of said side edges having a wear-resistant covering (36). The inventive rotary blade is characterized in that the wear-resistant covering of the lower side edge extends on one wall (40a) of a first substantially rectilinear ridge (40) of the platform and on one wall (42a) of a second ridge (42) of the platform, which extends at least partially in the lip (31) and is inclined with respect to the first ridge in a direction substantially parallel to the transverse axis (Z) of the lip.)

1. A rotor blade (10) for an aircraft turbine, the blade having a stacking axis (X) and having an axis of rotation (A) once the blade has been securely connected to a rotor, and the blade comprising a blade (16) extending between an inner platform (19) and an outer platform (20), the outer platform supporting at least one protruding lip (31, 32), the blade comprising a pressure side (16a) and a suction side (16b), and the outer platform comprising a pressure side lateral edge (22) and a suction side lateral edge (21), the pressure side lateral edge and the suction side lateral edge being located on the pressure side (16a) side and the suction side (16b) side, respectively, and being configured to mate in a form-fitting manner with complementary lateral edges (21, 22) of an adjacent blade, each of the lateral edges comprising a wear-resistant covering (36), characterized in that the wear-resistant covering of the pressure-side lateral edge extends on one wall (40a) of a first substantially rectilinear ridge (40) of the platform and on one wall (42a) of a second ridge (42) of the platform, which extends at least partially in the lip (31) and is inclined with respect to the first ridge in a direction substantially parallel to the transverse elongation axis (Z) of the lip.

2. Blade (10) according to the preceding claim, wherein the first ridge (40) has a substantially constant thickness E1.

3. Blade (10) according to the preceding claim, wherein the thickness E2 of the second ridge (42) is less than E1.

4. Blade (10) according to claim 2 or 3, wherein the wear resistant covering (36) of the lateral edge on the side of the suction side extends over a wall (52) of a third ridge (52) having a thickness E3 similar to E1.

5. Blade (10) according to one of the preceding claims, wherein the wall (42a) of the second ridge (42) extends in the lip and over 20% to 50% of the height of the lip (31), the height being measured along the stacking axis (X).

6. Blade (10) according to one of the preceding claims, wherein the lip (31) comprises two opposite longitudinal ends, one of which comprises at least partially the wall (42a) of the second ridge (42) and the other of which comprises an excess thickness in a direction perpendicular to the elongation axis (X).

7. Blade (10) according to one of the preceding claims, wherein the lip (31) is inclined with respect to a plane perpendicular to the rotation axis (a).

8. Blade (10) according to one of the preceding claims, wherein the second ridge (42) has a first end connected to one end of the first ridge (40) and a second free end at the pressure side lateral edge.

9. Rotor wheel for an aircraft turbomachine, comprising a disc carrying at its periphery an annular row of blades (10) according to one of the preceding claims.

10. Aircraft turbine comprising at least one blade (10) according to one of claims 1 to 8, or comprising a wheel according to claim 9.

Technical Field

The present invention relates to the general field of manufacturing rotor blades for aircraft turbines.

Background

Disclosure of Invention

The invention provides a rotor blade for an aircraft turbine, the blade having a stacking axis and having an axis of rotation once it has been firmly connected to a rotor, and the blade comprising a blade extending between an inner platform and an outer platform, the outer platform supporting at least one protruding lip, the blade comprising a pressure side and a suction side, and the outer platform comprising a pressure side lateral edge and a suction side lateral edge, located respectively on the pressure side and the suction side and configured to cooperate in a form-fitting manner, in particular by interlocking, with complementary lateral edges of adjacent blades, each of the lateral edges comprising a wear-resistant covering, characterized in that the wear-resistant covering of the lateral edge on the pressure side extends over one wall of a substantially rectilinear first ridge of the platform and over one wall of a second ridge of the platform A second ridge extends at least partially in the lip and is inclined relative to the first ridge in a direction substantially parallel to the transverse axis of elongation of the lip.

Thus, the wear resistant covering is deposited on the ridges, which stiffen the blade and limit the risk of cracks occurring during this deposition. These ridges make it possible to thicken the area of the wear-resistant covering applied as required, thus ensuring better heat dissipation during deposition, thus reducing the risk of cracks forming.

Furthermore, the shape of the ridge is adapted on the one hand to limit the dimensions of the ridge and of the cover and on the other hand to prevent the cover from coming into contact with the aforementioned wear-resistant cover extending around the wheel, and wherein the lip of the heel is intended to form an annular groove during operation. If the lip is inclined with respect to a plane perpendicular to the axis of rotation of the wheel and the ridges of each vane are aligned (and therefore not inclined to each other), the second ridge may spill over the lip and make unnecessary contact with the wear-resistant covering, resulting in a widening of the corresponding groove and an increased risk of gas leakage in this area.

The blade according to the invention may comprise one or more of the following features, independently of each other or in combination with each other:

-the first ridge has a substantially constant thickness E1,

-the thickness E2 of the second ridge is less than E1,

the wear-resistant covering of the lateral edge on the suction side extends over the wall of a third ridge, the thickness E3 of which is similar to E1,

the thickness of each ridge is measured in a direction substantially perpendicular to the surface on which the ridge is formed, or in a direction substantially perpendicular to the longitudinal mid-plane of the respective ridge, or in the direction of the axis of elongation of the respective ridge,

-the wall of the second ridge extends in the lip and extends over 20% to 50% of the height of the lip, the height being measured along the stacking axis,

-the lip comprises two opposite longitudinal ends, one of which at least partially comprises the wall of the second ridge and the other of which comprises an additional thickness in a direction perpendicular to the elongation axis,

-the lip is inclined with respect to a plane perpendicular to the axis of rotation,

the blade comprises two protruding lips, and the first ridge is located between these lips, an

-the second ridge having a first end connected to one end of the first ridge and a second free end at the pressure side lateral edge.

The invention also relates to a rotor wheel for an aircraft turbomachine, comprising a disk carrying on its periphery an annular row of blades as described above.

The invention also relates to an aircraft turbine comprising at least one blade or wheel as described above.

Drawings

The invention will be better understood and other details, features and advantages thereof will appear more clearly on reading the following description, given by way of non-limiting example and with reference to the accompanying drawings, in which:

FIG. 1 is a schematic perspective view of a turbine blade for an aircraft turbine,

FIG. 2 is an enlarged schematic view of a portion of another turbine blade for an aircraft turbine,

FIG. 3 is a schematic side view of a rotor blade according to the invention,

figure 4 is a schematic top view of the blade of figure 3,

figures 5 and 6 are detail views of figure 4, in which figure 6 shows one of the features of the invention, while figure 5, on the contrary, does not show the invention, and

fig. 7 is a schematic top view of the blade of fig. 3, shown in cross-section.

Detailed Description

The present invention is applicable to the movable wheel blade 10 described above with reference to fig. 1 and 2.

The blade 10 comprises at least one blade 16 extending between two platforms, an inner platform 19 and an outer platform 20 respectively. The inner platform 19 is connected to the radially inner end of the blade and the outer platform 20 is connected to the radially outer end of the blade and comprises a covering 36 of wear resistant material.

Fig. 3, 4, 6 and 7 show embodiments of the invention.

According to the invention, the wear-resistant covering 36 of the lateral edge 22, on the side of the pressure side 16a of the blade 16, extends on a wall 40a of the first ridge 40 between the lips 31, 32 and on a wall 42a of the second ridge 42 extending at least partially into the lip 31. The ridges 40, 42 are integral parts of the platform 20. As shown in fig. 3, the wall 42a extends over approximately 20% to 50% of the height of the lip 31, as measured along the stacking axis X.

The first ridge 40 is substantially straight and has a downstream end connected to a boss 44 which projects on the outer face of the platform 20. The boss has a general shape of the blade profile and forms an extension of the blade 16 radially outward of the platform 20.

The second ridge 42 is substantially straight and has a downstream end connected to the upstream end of the first ridge 40. The second ridge 42 is inclined with respect to the first ridge 40 in a direction substantially parallel to the transverse axis of elongation Z of the lip 31. In other words, the second ridge 42 is substantially parallel to the lip 31, and the first ridge 40 is inclined with respect to the lip 31 and the second ridge 42.

FIG. 7 is a cross-sectional view of the blade wherein the cutting plane passes substantially through the ridges 40, 42 and boss 44 and is substantially parallel to the plane of the platform 20. Fig. 7 shows the thickness E1, E2 of the ridges 40, 42 and the inclination angle a of the ridges 40, 42, which is for example between 120 ° and 150 °. In other words, the second ridge 42 forms a substantially zero angle with the lip 31 or axis Z, and the first ridge 40 is inclined at an angle with respect to the lip 31 or axis Z, which is comprised between 30 ° and 60 °.

This angle α is also visible in fig. 6, fig. 6 showing ridges 40, 42 inclined relative to each other, and fig. 5 conversely showing aligned ridges. In the latter case, and as explained above, the ridge 42 may extend beyond the lip and the wear-resistant covering supported by the ridge 42 may widen the groove 46 formed in the wear-resistant covering around the blade due to rotation of the disc supporting the blade.

The groove 46 is here partly indicated by a hatched area, the size of which depends on the maximum size of the lip 31. In the example shown, the lip 31 comprises a longitudinal end on the side of the pressure side 16a of the blade in which the ridge 42 extends and an opposite longitudinal end on the side of the suction side of the blade. The opposite longitudinal end portion is thickened in a direction perpendicular to the elongation axis of the lip portion, and has an overall shape called an elephant foot. The thickened end defines the maximum thickness of the lip and thus the thickness of the groove 46. The groove is annular and is therefore intended to extend entirely around the wheel supporting the blade.

In the example shown, the ridges 40, 42 define a first recess 50 between the ridges 40, 42 for receiving the wear-resistant covering 36, wherein a ledge 48 is present on the wall 40a of the ridge 40.

On the suction side of the blade 16, a wear-resistant covering is located on the wall 52a of the third ridge 52, the wall 52 having an overall orientation substantially parallel to the ridge 40. The ridge 52 has a thickness E3. The ridge 52 defines a second recess 58 for receiving the wear-resistant covering 36, wherein two lugs 54, 56 are present at opposite ends of the wall 52 a.

The thickness of the ridge is measured in a direction substantially perpendicular to the surface on which the ridge is formed, or in a direction substantially perpendicular to the longitudinal mid-plane of the ridge, or in the direction of the elongation axis of the ridge. The thickness of the ridge 42 may be measured in a direction substantially perpendicular to the axis Z. In fig. 7, the elongation axes of the ridges 40, 42, and 52 are referred to as 40b, 42b, and 52b, respectively.

The thicknesses E1, E2 and E3 are for example between 1mm and 3 mm. The thickness E2 of ridge 42 is preferably less than the thickness E1 of ridge 40. For example, thickness E1 is about 2mm and thickness E2 is about 1.5 mm. Thickness E3 is preferably similar to thickness E1 and is, for example, about 2 mm. These thicknesses ensure good mechanical strength and prevent the formation of cracks when depositing stellite.

The blade may be manufactured in the following manner. First, the blade is rough cast from metalAnd (4) obtaining. Then, e.g. by deposition of molten

The material fills the recesses 50, 58 with the wear-resistant covering 36 which is located on the wall of the ridge. The blade may then be subjected to machining operations to set the blade to the desired dimensions. During this last operation, the covers 36 and the ridges and lugs that define the recesses for receiving the covers may be machined.