Additive manufacturing method of a wall comprising at least one cooling hole for a turbine engine

Abstract

The invention relates to an additive manufacturing method for a wall (10) of a turbine engine, the wall (10) comprising a first cooling hole (40). The manufacturing method comprises additively manufacturing the wall (10) by selective melting or selective sintering on a powder bed. The wall (10) is manufactured with at least one lower region (19a) at least partially surrounding the first cooling hole (40) having a minimum length (La) between 0.01 mm and 0.4 mm and / or a lower region (19a) having a total thickness (ea) between 0.06 mm and 0.22 mm.

Description

TECHNICAL FIELD

[0001] The present invention relates to the field of powder bed additive manufacturing techniques, also known as 3D printing. More specifically, the present invention relates to a method for manufacturing a wall of a turbine engine comprising cooling holes, the wall being manufactured by depositing a powder layer by layer, the powder being partially solidified by selective melting or selective sintering by means of a laser beam or an electron beam.

[0002] The present invention also relates to the general field of aircraft turbine engines, such as turbojet engines and turboprop engines. The present invention relates to the combustion chamber of a turbine engine. BACKGROUND

[0003] The selective melting or selective sintering method on a powder bed makes it possible to easily manufacture metal or ceramic parts, such as turbine engine parts subjected to significant mechanical and / or thermal stresses.

[0004] Such a method is particularly well known under the acronyms SLM (Selective Laser Melting), SLS (Selective Laser Sintering), DMLS (Direct Metal Laser Sintering) and EBM (Electron Beam Melting).

[0005] These methods generally comprise the following steps: depositing a first powder layer in a manufacturing tank using a roller or doctor blade spreading member, the bottom of the manufacturing tank being formed by a plate that can be moved in translation, then heating a predetermined zone in the powder layer by means of a laser beam or an electron beam. The energy provided by the above-mentioned beam causes the local melting or sintering of the powder, the locally melted or sintered powder solidifying to form a first layer of the part. The part is in particular a wall of a turbine engine.

[0006] The plate is then lowered by a distance corresponding to the thickness of a layer, then a second powder layer is formed on the preceding layer by the spreading member. Then, a second layer of the above-mentioned part is formed using the above-mentioned beam. These steps are repeated until the part is manufactured.

[0007] Manufacturing a turbine engine wall with small and substantially uniform cooling orifices by additive manufacturing, in particular in a reproducible manner, is particularly difficult, in particular when these cooling orifices extend substantially perpendicularly to the wall of the turbine engine.

[0008] A turbine engine annular combustion chamber comprises two coaxial inner and outer annular walls connected together at an upstream end by a combustion chamber bottom wall and a fairing. The combustion chamber bottom wall comprises openings for mounting an injection system in which fuel injectors are engaged.

[0009] Some known combustion chambers have their inner and outer walls coated with a thermal shield to thermally protect the inner and outer walls from the hot gases produced by the combustion.

[0010] Known combustion chambers have their inner and outer walls provided with cooling holes passing through the inner and outer walls to cool these walls by a film of cold air coming from the combustion chamber diffuser, thereby thermally protecting these walls from the hot gases in the combustion chamber.

[0011] However, it is useful to further protect the inner and outer walls of the combustion chamber from the heat produced by the combustion, in particular to enable combustion at higher temperatures and to increase the efficiency of the turbine engine. SUMMARY

[0012] The present invention aims to at least partially solve the problems encountered in the solutions of the prior art.

[0013] In this respect, one object of the present invention is an additive manufacturing method for a wall of a turbine engine, said wall comprising a first cooling hole. Said manufacturing method comprises additive manufacturing of said wall by selective melting or selective sintering on a powder bed.

[0014] According to the invention, said wall is manufactured with a lower region having a total thickness between 0.06 mm and 0.22 mm at least partially surrounding said first cooling hole. The energy input per unit length used to manufacture said lower region is lower than the energy input used to manufacture an intermediate region forming the bulk of said wall.

[0015] By means of the additive manufacturing method according to the invention, it is facilitated to manufacture a wall of a turbine engine having at least one first cooling hole of small size. The geometry of the first cooling hole is in particular improved.

[0016] The manufacturing method of said wall tends to be more reproducible. It also facilitates the creation of more uniform first cooling holes in the wall, including when these first cooling holes extend substantially perpendicularly to the outer surface of the turbine engine wall.

[0017] According to one feature, said lower region is manufactured with a minimum lower region length between 0.01 mm and 0.4 mm. Said minimum lower region length is the minimum powder solidification length enabling the formation of said lower region.

[0018] In particular, the minimum length of the lower region is reduced and / or the overall thickness of the lower region is increased, thereby manufacturing the lower region over a larger volume. The larger volume of the lower region in the first region enables to reduce manufacturing defects in the first cooling hole.

[0019] The lower region, also referred to as "downskin", is a region formed from at least one solidified powder layer and the energy input per length for manufacturing the lower region is lower than the energy input per length for manufacturing the intermediate region.

[0020] The intermediate region, also referred to as "inskin", is in particular a region formed from at least one solidified powder layer. The intermediate region forms the majority of the volume of the wall. The energy input per length for forming each intermediate region is in particular the standard energy input for the manufacturing of the wall.

[0021] The upper region, also referred to as "upskin", is in particular a region formed from at least one solidified powder layer and the energy input per length for manufacturing the upper region is approximately equal to the energy input per length for manufacturing the intermediate region, but the upper region has a double energy exposure with respect to the intermediate region.

[0022] The energy input per length is in particular the energy per distance of unit that is delivered to the material, in this case the powder.

[0023] Preferably, the lower region has a minimum length approximately equal to 0.05 mm.

[0024] Preferably, the lower region has a thickness approximately equal to 0.12 mm.

[0025] According to another feature, the first wall region is manufactured without an upper region.

[0026] According to another feature, the first wall region is manufactured with an upper region thickness smaller than or equal to 0.06 mm.

[0027] In the case of no upper region or of an upper region with a small thickness, manufacturing defects of the first cooling hole are in particular reduced.

[0028] According to a feature, when the wall is manufactured vertically on a support by additive manufacturing, the lower region is located in an upper portion of the first cooling hole, in particular at an upper edge of the first cooling hole.

[0029] The support is in particular a manufacturing plate on which the wall extends perpendicularly during the additive manufacturing of the wall.

[0030] Forming the upper portion of the first cooling hole in the wall by additive manufacturing is particularly difficult without displacing material, e.g. powder, downwards. The advantage of the lower region in the upper portion of the cooling hole makes it easier to manufacture the cooling hole.

[0031] According to one feature, the lower region is manufactured by a first energy input per unit length to the powder bed, the first energy input per unit length being between 0.0200 J / mm and 0.0300 J / mm.

[0032] Preferably, the lower region is manufactured by a first energy input per unit length to the powder bed, the first energy input per unit length being substantially equal to 0.0250 J / mm.

[0033] According to another feature, the intermediate region around the first cooling hole is manufactured by a second energy input per unit length to the powder bed, the second energy input per unit length being between 0.1300 J / mm and 0.1950 J / mm.

[0034] Preferably, the intermediate region around the first cooling hole is manufactured by a second energy input per unit length to the powder bed, the second energy input per unit length being substantially equal to 0.1625 J / mm.

[0035] According to one feature, the wall is manufactured to have an upper region around the cooling hole, the upper region being manufactured by a third energy input per unit length to the powder bed, the third energy input per unit length being between 0.1300 J / mm and 0.1950 J / mm.

[0036] Preferably, the wall is manufactured to have an upper region around the cooling hole, the upper region being manufactured by a third energy input per unit length to the powder bed, the third energy input per unit length being substantially equal to 0.1625 J / mm.

[0037] Preferably, the third energy input per unit length is substantially equal to the second energy input per unit length, wherein the upper region has twice the energy exposure relative to the intermediate region.

[0038] The lower value of the first energy input per unit length relative to the second energy input per unit length and / or the third energy input per unit length enables less powder to be melted / agglomerated when manufacturing the lower region than when manufacturing the middle or upper region. This results in a reduction of manufacturing defects of the first cooling hole made of the larger volume of the lower region.

[0039] According to another feature, the first cooling hole extends around a longitudinal axis of the first cooling hole, the longitudinal axis of the first cooling hole being substantially orthogonal to the outer surface of the wall.

[0040] Preferably, during the additive manufacturing of the wall, the wall extends substantially perpendicularly to the manufacturing plate.

[0041] This makes it more difficult to manufacture such oriented first cooling holes with a first cooling hole and / or a wall by additive manufacturing, and the manufacturing method according to the application thereby becomes more advantageous.

[0042] According to one feature, the first cooling hole is digitally modeled with a substantially elliptical transverse surface so as to be manufactured with a substantially circular transverse section by selective fusion or selective sintering on a powder bed.

[0043] The pre-modeling of the first cooling hole with a shape different from the intended shape of the hole makes it possible, in particular, for the material to be displaced downward during the melting / agglomeration of the powder at the upper edge of the first cooling hole.

[0044] According to another feature, the wall comprises at least one second cooling hole. The second cooling hole is oriented around a longitudinal axis of the second cooling hole, the longitudinal axis of the second cooling hole being inclined by an angle with respect to the outer surface of the wall, the angle being comprised between 5° and 45°, preferably approximately 20°, in at least one cross-sectional plane of the wall.

[0045] The cross-sectional plane is in particular a longitudinal cross-sectional plane of the wall, the longitudinal cross-sectional plane of the wall comprising a normal to the outer surface of the wall.

[0046] The additive manufacturing method makes it possible in particular to manufacture a second cooling hole with an orientation with respect to the wall, in particular inclined with respect to the wall, which is difficult to achieve by drilling methods known in the prior art, such as laser drilling.

[0047] According to one feature, the second cooling hole comprises an inlet and / or an outlet comprising a circular portion.

[0048] The circular portion at the inlet and / or outlet of the second cooling hole tends to limit the unwanted deposition of material at the inlet and / or outlet of the second cooling hole.

[0049] Another object of the application is an annular combustion chamber for a turbine engine. The combustion chamber comprises an inner wall, an outer wall and a chamber bottom. The inner wall and the outer wall are annular around a longitudinal axis of the combustion chamber. The chamber bottom mechanically connects the inner wall and the outer wall.

[0050] According to the invention, at least a first wall of the inner wall and the outer wall comprises a first annular partition and a second annular partition. The second partition is radially spaced apart from the first partition to form, jointly with the first partition, a cooling duct for the first wall.

[0051] The cooling duct comprises an inlet wall and an outlet wall extending between the first partition and the second partition. At least one of the inlet wall and the outlet wall has at least one cooling hole therethrough, the at least one cooling hole having an axial component along the longitudinal axis of the combustion chamber.

[0052] By means of the combustion chamber according to the invention, the cooling of the first wall is improved. In particular, the flow-through of cooling air from the inlet wall to the outlet wall of the cooling duct enables an improved cooling of the combustion chamber. The cooling duct in particular facilitates a continuous and uniform flow-through of cooling air in the first wall. Since the cooling air flowing through the cooling duct tends to be separated from the hot combustion gases, for example by the first partition, the cooling of the first wall is more effective.

[0053] The invention can optionally comprise one or more of the following features, in combination or not.

[0054] According to one feature, the inlet wall has at least one cooling hole therethrough, the at least one cooling hole having an axial component along the longitudinal axis of the combustion chamber. The outlet wall has at least one cooling hole therethrough, the at least one cooling hole having an axial component along the longitudinal axis of the combustion chamber.

[0055] By facilitating the flow-through of cooling air from the inlet wall to the outlet wall through the cooling holes of both walls, the cooling of the first wall is further improved.

[0056] According to another feature, the first wall has a main hole therethrough for introducing a main flux into the combustion chamber.

[0057] According to another feature, the first wall has a dilution hole therethrough for introducing a dilution flux into the combustion chamber.

[0058] In particular, the cooling duct does not disturb the combustion in the combustion chamber, so that the combustion can be fed by the main flux and / or the dilution flux.

[0059] According to another feature, the first partition has at least one cooling hole therethrough, the at least one cooling hole having a radial component, in particular the first partition has a plurality of cooling holes, the plurality of cooling holes having a radial component.

[0060] These cooling holes with a radial component make it possible in particular to carry out film cooling of the first partition close to the hot combustion gases, thereby improving the cooling of the first wall. These cooling holes with a radial component also make it possible to introduce additional air into the combustion chamber.

[0061] According to one feature, the combustion chamber comprises a second edge inclined with respect to the inlet wall to form an opening flared upstream, and the opening is designed to direct the cooling fluid to the cooling duct inlet.

[0062] The second edge tends to increase the amount of air passing through the cooling duct.

[0063] According to another feature, the first wall comprises an attachment periphery for attaching the first wall to the fairing and / or to the chamber bottom of the combustion chamber. The attachment periphery comprises a first edge inclined with respect to the inlet wall, and at least one hole for introducing fluid into the combustion chamber passes through this first edge.

[0064] The first edge tends to increase the amount of air introduced into the combustion chamber while connecting the first wall to the chamber bottom and / or to the fairing.

[0065] Preferably, the first edge is substantially parallel to the second edge.

[0066] According to one feature, the radial extent of the cooling duct narrows in the downstream direction from the inlet wall of the cooling duct over at least part of the axial extent of the cooling duct.

[0067] This accelerates the air in the cooling duct, thereby increasing the cooling flow rate to cool the first wall. The pressure loss of the cooling air is limited when the cooling air enters the cooling duct.

[0068] According to one feature, the radial extent of the cooling duct widens in the downstream direction to the outlet wall of the cooling duct over at least part of the axial extent of the cooling duct.

[0069] According to another feature, the outlet wall of the cooling duct has at least one hole passing through the outlet wall of the cooling duct for connecting the first wall to the turbine engine wall.

[0070] According to another feature, the outlet wall is radially oriented.

[0071] The outlet wall makes it possible in particular to connect the first wall to the turbine wall while making it possible to evacuate the air from the cooling duct. The air pressure tends to increase at the outlet of the cooling duct to supply cooling air in particular to the high-pressure turbine.

[0072] According to one feature, the first wall comprises a reinforcement extending between the first partition and the second partition to increase the mechanical strength of the first wall.

[0073] Despite the presence of the first wall, the second wall and the cooling duct, the first wall has a satisfactory mechanical strength compared to a solid wall, in particular.

[0074] According to one feature, the first wall comprises a support for a spark plug, the support being configured to guide and support the spark plug in the combustion chamber. The support is in particular integral with the first wall.

[0075] According to another feature, the second wall between the inner wall and the outer wall comprises an annular third partition and an annular fourth partition. The fourth partition is radially spaced apart from the third partition to form, jointly with the third partition, a second cooling duct for cooling the second wall.

[0076] The second cooling duct comprises a second inlet wall and a second outlet wall extending between the third partition and the fourth partition.

[0077] At least one of the second inlet wall and the second outlet wall has at least one cooling hole therethrough, the at least one cooling hole having an axial component along the longitudinal axis of the combustion chamber.

[0078] Thus, the cooling of the outer wall and the cooling of the inner wall in the combustion chamber are improved.

[0079] The application also relates to a turbine engine comprising a combustion chamber as described above. Preferably, the turbine engine is an aircraft turbine engine, such as a turbojet or a turboprop.

[0080] The application also relates to a method for manufacturing a combustion chamber as described above, wherein the first wall and / or the second wall are manufactured by selective melting or selective sintering on a powder bed, in particular by laser.

[0081] The first wall can be additively manufactured. The first wall can have a complex shape. BRIEF DESCRIPTION OF DRAWINGS

[0082] The application will be better understood with the help of the description of exemplary embodiments given by way of indication and not of limitation, read with the help of the appended drawings in which:

[0083] - Figure 1 A turbine engine comprising a wall manufactured according to the additive manufacturing method according to a first embodiment of the application is shown;

[0084] - Figure 2 is a partial schematic view of an additive manufacturing tool for implementing the additive manufacturing method according to a first embodiment of the application;

[0085] - Figure 3 manufacturing of a wall on an additive manufacturing tool when implementing the additive manufacturing method according to the first embodiment is schematically illustrated;

[0086] - Figure 4a structure of a wall close to a cooling hole according to an additive manufacturing method known in the art is schematically illustrated;

[0087] - Figure 4b structure of a wall close to a cooling hole when using the additive manufacturing method according to the first embodiment is schematically illustrated;

[0088] - Figure 5a is a photograph representing a wall comprising cooling holes manufactured by an additive manufacturing method known in the art;

[0089] - Figure 5b is a photograph representing a wall comprising cooling holes manufactured by the additive manufacturing method according to the first embodiment;

[0090] - Figure 6 implementation of the additive manufacturing method according to the first embodiment of the application is schematically illustrated;

[0091] - Figure 7 is a partial schematic view of a longitudinal half cross-sectional view of a turbine engine combustion chamber according to an embodiment of the application;

[0092] - Figure 8 is a partial schematic view of a perspective view of an outer wall of a combustion chamber according to the first embodiment from the inside of the outer wall;

[0093] - Figure 9 is a partial schematic view of an outer wall of a combustion chamber according to the first embodiment from the outer surface of the outer wall;

[0094] - Figure 10 is a partial schematic view of a perspective view of an outer wall and an inner wall of a combustion chamber according to the first embodiment;

[0095] - Figure 11 is a partial schematic view of an upstream end of an outer wall of a combustion chamber according to the first embodiment;

[0096] - Figure 12 is a partial schematic view of a downstream end of an outer wall of a combustion chamber according to the first embodiment. DETAILED DESCRIPTION

[0097] The same, similar or equivalent parts in the different figures have the same reference numerals in order to facilitate the switching from one figure to another.

[0098] Figure 1A double-flow, double-corps turbo engine 1 is shown. The turbo engine 1 is a turbojet engine having a shape of revolution around a longitudinal axis AX.

[0099] The turbo engine 1 comprises, in the path of the primary flow 11 of the primary flux, an air inlet duct 2, a fan 3, a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 7, a high-pressure turbine 8 and a low-pressure turbine 9.

[0100] Generally, the term "air" refers to any gas that can be used as an oxidizer in the turbo engine 1.

[0101] The low-pressure compressor 4, the high-pressure compressor 6, the high-pressure turbine 8 and the low-pressure turbine 9 define a secondary flow stream 13 of a secondary flux that bypasses them.

[0102] The high-pressure compressor 6 and the high-pressure turbine 8 are mechanically connected by a drive shaft of the high-pressure compressor 6, forming a high-pressure corps of the turbo engine 1. Likewise, the low-pressure compressor 4 and the low-pressure turbine 9 are mechanically connected by a turbo engine shaft 1, forming a low-pressure corps of the turbo engine 1.

[0103] The low-pressure compressor 4, the high-pressure compressor 6, the combustion chamber 7, the high-pressure turbine 8 and the low-pressure turbine 9 are surrounded by an internal fairing that extends from the inlet duct 2 to the inside of the low-pressure turbine 9.

[0104] This internal fairing is surrounded by an external fairing that radially outwardly defines the turbo engine with respect to the longitudinal axis AX. In particular at the fan 3, the external fairing radially outwardly defines the secondary flow 13.

[0105] Figure 2 An exemplary tool 20 for manufacturing a component by selective melting or selective sintering on a powder bed according to the manufacturing method according to the first embodiment is shown.

[0106] In the embodiment shown, the component is a wall 10 for an aircraft turbo engine, for example a blade or a peripheral wall of the turbo engine. The wall is designed to withstand particularly high mechanical and / or thermal stresses during operation of the turbo engine. The wall is manufactured by additive manufacturing from a powder 17, which is generally made of a metal material for aeronautics.

[0107] The tool 20 comprises a powder 17 supply slot 23, a manufacturing slot 24 in which the wall blank 10 will be formed, and a third slot, which can be a recycling slot 25 of the remaining powder 17 or a second supply slot.

[0108] The bottom of each tank is formed by a plate that can move in translation on an actuation arm 26 oriented along a vertical axis of the tank. Each plate comprises a metal sheet forming a bed for the powder 17. The plate 27 of the supply tank is configured to move along a first vertical axis Z1-Z1 that is substantially parallel to a second vertical axis Z2-Z2 along which the plate 28 of the manufacturing tank is displaced.

[0109] The actuation of the plate 27 of the supply tank makes it possible to feed the powder 17 into the manufacturing tank 24. When the plate 28 of the manufacturing tank of the manufacturing tank is lowered, the plate of the manufacturing tank of the manufacturing tank makes it possible to form a successive layer 19 of the wall blank 10.

[0110] The tool 20 also comprises a roller spreading member 29 or a doctor blade as shown in Figure 1 , which makes it possible to push the powder 17 from the supply tank 23 into the manufacturing tank 24 and spread it in the supply tank 23, thereby forming a layer 19 of powder having a determined thickness. To this end, the spreading member 29 moves from the supply tank 23 to the recovery tank 25 along a displacement direction indicated by the arrow A along a horizontal scanning plane. The excess powder can be recovered in the collection plate 25.

[0111] The tool 20 also comprises a heating member 30 configured to melt or sinter at least a portion of the layer 19 of powder deposited on the plate 28 of the manufacturing tank in order to obtain, after solidification, a layer 19 of the wall blank 10.

[0112] The heating member 30 comprises, for example, a laser 31 and one or more mirrors 32 for sending a laser beam to the area of the layer 17 of powder to be melted or sintered. Thus, after the layer 17 of powder has been scanned by the energy beam, the manufacturing tank 24 will contain a layer 19 of solidified material surrounded by non-melted or non-sintered powder 17.

[0113] The tool 20 also comprises a second heating member, for example an oven 34, for at least one heat treatment of the wall blank 10 after each solidified layer 19 of material has been cooled.

[0114] With reference to Figure 3 , the plate 28 of the manufacturing tank comprises a lower outer surface S1 and an upper outer surface S2 opposite the lower outer surface S1 and on which the wall blank 10 is attached after the additive manufacturing step 105 of the wall blank 10.

[0115] The wall 10 comprises a lower end 10a, an upper end 10b opposite the lower end 10a, and a main body 12 extending from the lower end 10a to the upper end 10b. The wall comprises a first flat portion defined by a first side surface S3 and a second flat portion defined by a second side surface S4 opposite the first side surface S3.

[0116] In the illustrated embodiment, the wall 10 is generally sheet-like and the second side surface S4 is substantially parallel to the first side surface S3.

[0117] As used herein and unless otherwise specified, the axial or longitudinal direction is the direction parallel to the longitudinal axis Z-Z of the wall 10. In the illustrated embodiment, the longitudinal axis Z-Z of the wall 10 is oriented substantially vertically. The radial or transverse direction is the direction orthogonal to the longitudinal axis Z-Z of the wall and intersecting this axis. The circumferential direction is defined as the direction locally orthogonal to the radial direction and locally orthogonal to the direction of the longitudinal axis Z-Z of the wall. The normal direction Y-Y is the direction substantially orthogonal to the first side surface S3 or to the second side surface S4.

[0118] During the additive manufacturing 105 of the wall blank, the wall blank 10 is attached to the manufacturing plate 28 at its lower end 10a. The wall blank extends substantially perpendicularly to the upper outer surface S2 of the manufacturing plate 28 and forms an angle a with this upper outer surface.

[0119] The wall 10 has a first cooling hole 40 and a second cooling hole 44 passing through the wall.

[0120] Each second cooling hole 44 extends from an inlet 43 to an outlet 45 around a longitudinal axis R1-R1 of the second cooling hole 44, wherein the inlet 43 is open through the first side surface S3 and the outlet 45 is open through the second side surface S4. The longitudinal axis R1-R1 of each second cooling hole 44 is inclined by an angle g with respect to the first side surface S3 and the second side surface S4, the angle g being between 5° and 45° in at least one longitudinal cross-sectional plane of the wall 10 comprising the normal Y-Y of the wall 10.

[0121] In the illustrated embodiment, the longitudinal axis R1-R1 of each second cooling hole 44 is inclined by an angle g with respect to the first side surface S3 and the second side surface S4, the angle g being substantially equal to 20° in the illustrated longitudinal cross-sectional plane. Figure 3

[0122] In the illustrated embodiment, the inlet 43 of each second cooling hole 44 comprises a circular portion 43a. The outlet 45 of each second cooling hole 44 comprises a circular portion 45a.

[0123] ​Each first cooling hole 40 extends from an inlet 41, which is open through the first side surface S3, to an outlet 42, which is open through the second side surface S4, around a longitudinal axis R2-R2 of the first cooling hole 40. The longitudinal axis R2-R2 of each first cooling hole 40 is oriented at an angle β which is substantially perpendicular to the first and second side surfaces S3, S4 of the wall 10.

[0124] As the wall 10 is additively manufactured substantially perpendicular to the manufacturing plate 28, and as the longitudinal axis R2-R2 of each first cooling hole 40 is substantially perpendicular to the first and second side surfaces S3, S4 of the wall 10, the manufacturing of each first cooling hole 40 by additive manufacturing would become more difficult. This is because the material of the wall 10 tends to move downwards during the melting / agglomeration of the powder 17 at the upper edge of each first cooling hole 40. Moreover, the first cooling holes are more difficult to manufacture as they have small dimensions, for example a radius r1 substantially equal to 0.25 mm and an area A1 approximately equal to 0.20 mm2. 2

[0125] The manufacturing method 100 of the wall 10 according to the application aims to at least partially remedy these drawbacks by modifying the additive manufacturing parameters of the wall 10 around each first cooling hole 40, in particular the additive manufacturing parameters in the vicinity of the first cooling hole 40.

[0126] In combination Figure 3 , Figure 4b , Figure 5b and Figure 6 , the wall 10 is additively manufactured with a lower region 19a and an intermediate region 19b. Unlike the wall 10 additively manufactured according to the method schematically illustrated in for example Figure 4a , the main body 12 of this wall is manufactured without an upper region 19c.

[0127] In the present disclosure, the lower region 19a (also referred to as "downskin") is a region formed from at least one solidified powder layer 17 and is manufactured by a unit length of energy input Ea which is lower than the unit length of energy input used to manufacture the intermediate region 19b.

[0128] The intermediate region 19b (also referred to as "inskin") is in particular a region formed from at least one solidified powder layer 17. The intermediate region 19b forms the majority of the volume of the wall 10. The unit length of energy input Eb used to form each intermediate region 19b is in particular the standard unit length of energy input used for the manufacture of the wall 10.

[0129] ​The upper region 19c, also referred to as "upskin", is in particular a region formed from at least one solidified powder layer 17 and is manufactured by a unit length of energy input Ec which is substantially equal to the unit length of energy input used for manufacturing the intermediate region 19b, but which upper region has twice the energy exposure with respect to the intermediate region 19b.

[0130] Each lower region 19a of the wall 10 at least partially defining the first cooling hole 40 has a total thickness ea between 0.06 and 0.22 mm. Each lower region 19a in particular has a total thickness ea substantially equal to 0.12 mm.

[0131] In the present disclosure, the thickness parameter ea of each lower region 19a is also referred to as "thickness of the downskin". This is the total thickness of the lower region 19a in at least one longitudinal cross section of the wall 10.

[0132] In the illustrated embodiment, the total thickness ea of the lower region 19a corresponds to the thickness of the five layers of agglomerated / fused powder 17 in the lower region 19a.

[0133] Each lower region 19a of the wall 10 at least partially defining the first cooling hole 40 is manufactured with a minimum length La between 0.01 and 0.4 mm. Each lower region 19a in particular is manufactured with a minimum length parameter La substantially equal to 0.05 mm.

[0134] In the present disclosure, the minimum length parameter La of the lower region is also referred to as "downskin minimum length". This is the minimum length of powder solidification which enables the formation of the lower region 19a. The downskin minimum length parameter La is compared to the actual displacement length of the laser. The downskin minimum length parameter is less than the actual displacement length of the laser in the lower region 19a so as to enable the manufacture of the lower region 19a.

[0135] In the illustrated embodiment, the minimum length parameter La corresponds to the minimum length of the layers of fused / agglomerated powder in the lower region 19a in at least one longitudinal cross section of the wall 10.

[0136] Each lower region 19a is manufactured by a unit length of first energy input Ea on the powder bed 17 which is between 0.02 J / mm and 0.03 J / mm. Each lower region 19a is manufactured by a unit length of first energy input Ea on the powder bed 17 which is preferably substantially equal to 0.0250 J / mm.

[0137] Each intermediate region 19b is manufactured by a second line energy supply Eb on the powder bed 17, which is between 0.1300 J / mm and 0.1950 J / mm. Each intermediate region 19b is manufactured by a second energy per unit length Eb on the powder bed 17, which is preferably substantially equal to 0.1625 J / mm.

[0138] More generally, the first energy input per unit length Ea is substantially 85% less than the second energy input per unit length Eb. The lower value of the first energy input per unit length Ea compared to the second energy input per unit length Eb makes it possible, in particular, to melt / agglomerate less powder 17 during the manufacture of the lower region 19a than during the manufacture of the intermediate region 19b. This makes it possible to reduce the manufacturing defects of each first cooling hole 40 by increasing the volume of the lower region 19a with respect to the volume of the intermediate region 19b.

[0139] With reference to the drawings Figure 4a and Figure 4b , the wall 10 manufactured according to the additive manufacturing method 100 according to the first embodiment differs from the wall 10 additively manufactured according to the manufacturing method known from the prior art in that the wall 10 manufactured according to the additive manufacturing method according to the first embodiment does not have an upper region 19c at the bottom of each first cooling hole 40 and that the wall comprises a greater volume of lower region 19a at the upper edge of each first cooling hole 40 and that each first cooling hole 40 is delimited at its lower edge by an intermediate region 19b.

[0140] The minimum length La of each lower region 19a of the wall 10 manufactured according to the additive manufacturing method 100 according to the first embodiment is for example substantially 90% less than the minimum length of each lower region 19a of the wall 10 additively manufactured according to the manufacturing method known from the prior art. In combination Figure 3 , Figure 4a and Figure 4b , the minimum length La of each lower region 19a of the wall 10 is in particular determined along the direction X-X.

[0141] The thickness ea of all the layers of the lower region 19a of the wall 10 manufactured according to the additive manufacturing method 100 according to the first embodiment is for example 200% greater than the thickness of all the layers of the lower region 19a of the wall 10 additively manufactured according to the manufacturing method known from the prior art. In combination Figure 3 , Figure 4a and Figure 4b , the total thickness ea of the lower region 19a is in particular determined along the direction Z-Z.

[0142] The manufacturing parameters of each intermediate region 19b of the wall 10 manufactured according to the additive manufacturing method 100 are substantially identical to the manufacturing parameters of the intermediate regions 19b of the wall 10 additively manufactured according to the manufacturing method known from the prior art.

[0143] As mentioned previously, the wall 10 manufactured according to the additive manufacturing method 100 according to the first embodiment does not comprise an upper region 19c.

[0144] In combination Figure 5a and Figure 5b , Figure 5a The third cooling hole 46 illustrated in Figure 5b differs from the first cooling hole 40 illustrated in

[0145] With reference to Figure 4a , the third cooling hole 46 comprises only two layers in the lower region 19a, which is located only on the upper edge of the third cooling hole 46. This third cooling hole comprises four layers in the upper region 19c, which is located only in the lower edge of the third cooling hole 46.

[0146] With reference to Figure 5a , the third cooling hole 46 passing through the wall 10 manufactured according to the manufacturing method known from the prior art has a rather irregularly shaped edge. This third cooling hole comprises a material collapse at its upper edge. Furthermore, this third cooling hole comprises a clearly unsuitable material deposit at the bottom of the third cooling hole 46. The third cooling hole 46 comprises a radius r2 equal to approximately 0.25 mm and a surface area A2 equal to approximately 0.19 mm2, for example. 2

[0147] With reference to Figure 4b , the upper edge of the first cooling hole 40 comprises five agglomerated / fused powder layers in the lower region 19a, which is located only on the upper edge of the first cooling hole 40. Due to the higher number of layers of the lower region 19a of the first cooling hole 40, the total thickness ea of the lower region 19a of the first cooling hole 40 is significantly higher than the total thickness ea of the lower region 19a of the third cooling hole 46. The lower edge of the first cooling hole 40 is formed by the intermediate region 19b. Unlike the third cooling hole 46, the first cooling hole 40 does not have an upper region 19c.

[0148] Along the horizontal direction of Figure 4a and Figure 4b , the minimum length La of each layer of the lower region 19a of the wall 10 surrounding each first cooling hole 40 of the embodiment in Figure 4b is less than the minimum length of each layer of the lower region 19a of the embodiment in Figure 4a .

[0149] With reference to Figure 5b ​The first cooling hole 40 manufactured according to the manufacturing method 100 according to the first embodiment has a more regular shape, in particular at the upper edge and at the bottom of the first cooling hole 40. The radius r1 of the first cooling hole 40 is substantially equal to the radius r2 of the third cooling hole 46. Due to the more regular edge of the first cooling hole 40, the surface area Al of the first cooling hole is about 15% larger than the surface area A2 of the third cooling hole 46.

[0150] Reference will now be made in particular to Figure 6 The additive manufacturing method 100 according to the first embodiment will be described in more detail.

[0151] The manufacturing method 100 first comprises a step 101 of determining additive manufacturing parameters of the wall 10, in particular a value of the minimum length La of each lower region 19a, a value of the thickness parameter ea of all layers of the lower region 19a, a value of the first energy input Ea per unit length and a value of the second energy input Eb per unit length.

[0152] Subsequently, the additive manufacturing method 100 comprises a step of digitally modeling 103 each first cooling hole 40 with a substantially elliptical lateral surface, such that each first cooling hole 40 is manufactured with a substantially circular lateral cross-section.

[0153] This digital modeling 103 of each first cooling hole 40 with a surface shape that is different from the intended shape of the hole enables in particular a downward material displacement when the upper edge of each first cooling hole 40 melts / agglomerates the powder 17.

[0154] The manufacturing method 100 continues with a step of additively manufacturing 105 the wall 10 on the powder bed 17 by selective melting or selective sintering, in particular by a laser, layer by layer. The first cooling holes 40 and the second cooling holes 44 are made through the wall 10 while manufacturing the wall 10.

[0155] The energy beam applied to the powder bed 17 to form each lower region 19a and each intermediate region 19b is moved linearly back and forth. After the additive manufacturing step 105, the wall blank 10 is attached to the manufacturing plate 28 at its lower end 10a.

[0156] The additive manufacturing method 100 according to the first embodiment enables in particular to make each second cooling hole 44 with an orientation with respect to each side surface S3, S4 that is difficult to achieve with drilling methods known from the prior art, such as laser drilling, in particular when the angle γ is less than or equal to 20°.

[0157] The rounded portion 43a at the inlet of each second cooling hole 44 tends to limit the unwanted material deposition at the inlet 43 of each second cooling hole 44 during the additive manufacturing 105. The rounded portion 45a at the outlet of each second cooling hole 44 tends to limit the unwanted material deposition at the outlet 45 of each second cooling hole 44 during the additive manufacturing 105.

[0158] The additive manufacturing step 105 comprises a rapid cooling of the wall blank 10 after the melting or sintering of the powder 17, which can create mechanical stresses (in particular shrinkage) and structural changes in the wall blank 10.

[0159] The manufacturing method 100 comprises heating 106, 108 the wall blank 10. This heating 106 comprises in particular a first stress relief heat treatment, the purpose of which is to reduce the thermal stresses, residual mechanical stresses and structural changes created in the wall blank 10 during the additive manufacturing step 105. This heating 106, 108 can also comprise a second heat treatment 108 to increase the robustness and / or the lifetime of the wall blank 10. The heating 106, 108 generally takes place at a temperature above 1000°C.

[0160] Finally, the method 100 for manufacturing the wall 10 comprises machining 110 the wall blank 10, in particular separating the lower end 10a of the wall blank 10 from the manufacturing slab 28. This machining 110 comprises, for example, electro-erosive machining of the wall 10.

[0161] The manufacturing method 100 can also comprise machining 112 the manufacturing slab 28. This machining 112 comprises, for example, electro-erosive machining, grinding or sandblasting of the manufacturing slab 28 for the manufacture of the next wall 10.

[0162] By means of the additive manufacturing method 100 according to the invention, it is facilitated to manufacture a wall 10 of a turbine engine having at least one first cooling hole 40 of small size. The geometry of each first cooling hole 40 is in particular improved. The additive manufacturing method 100 according to the invention makes it possible in particular to manufacture a first cooling hole 40 having a smaller radius r1.

[0163] The manufacturing method 100 of the wall 10 tends to be more reproducible. It also facilitates the manufacture of a first cooling hole 40 having a more uniform geometry in the wall 10.

[0164] In particular, during the manufacturing method 100, the minimum length La of each lower region 19a is reduced and the thickness of each lower region 19a is increased. Subsequently, in particular in the absence of upper regions 19c, the wall 10 is manufactured with a greater volume of lower region 19a close to each first cooling hole 40 with respect to the intermediate region 19b. This results in a more precise, uniform and easier to reproduce geometry of each first cooling hole 40, in particular a reduction of manufacturing defects of each first cooling hole 40.

[0165] In the absence of upper regions 19c, manufacturing defects of each first cooling hole 40 are reduced. In particular, in the absence of upper regions 19c, an improper deposition of material at the bottom of each first cooling hole 40 is limited.

[0166] Figure 7 A combustor 2 of an aircraft turbine engine is schematically illustrated. The combustor 2 is annular about a longitudinal axis X-X of the turbine engine.

[0167] The combustor comprises an outer casing wall 22 and an inner casing wall 24 connected by a combustor bottom 28, a dome 27, an outer wall 25 and an inner wall 26.

[0168] The outer wall 25, the inner wall 26, the dome 27 and the combustor bottom 28 collectively define a combustion tube of the combustor within which combustion of the combustor 2 takes place.

[0169] The combustor 2 further comprises at least one spark plug 6, an injector 5, an injection system 3 and a diffuser 7.

[0170] The outer casing wall 22 defines the combustor 2 radially outwardly with respect to the longitudinal axis X-X of the turbine engine. The inner casing wall 24 defines the combustor 2 radially inwardly with respect to the longitudinal axis X-X of the turbine engine. The inner casing wall is mechanically connected to an inner shell 90 for attaching the inner wall 26.

[0171] The outer casing wall 22 and the outer wall 25 collectively define a first airflow passage 21. Similarly, the inner casing wall 24 and the combustor inner wall 26 collectively define a second airflow passage 23.

[0172] In the context of the present disclosure, a longitudinal or axial direction is a direction generally parallel to the longitudinal axis X-X of the turbine engine. A radial direction is a direction generally orthogonal to and intersecting the longitudinal axis X-X of the turbine engine. A circumferential direction is a direction around the longitudinal axis X-X of the turbine engine.

[0173] An "upstream" direction and a "downstream" direction are defined by the general flow direction of air and fuel in the combustor 2. The directions also generally correspond to the general flow direction of exhaust gases in the turbine engine.

[0174] Generally speaking, the term "air" refers to any gas that can be used as oxidizer in the combustion chamber 2 of the turbine engine.

[0175] The outer wall 25 and the inner wall 26 are coaxial rotating walls around the longitudinal axis X-X of the turbine engine, the inner wall being symmetrical with the outer wall with respect to the longitudinal axis Y-Y of the injection system 3 as shown. Figure 7 The inner wall and the outer wall can each extend 360° around the longitudinal axis X-X of the turbine engine or be segmented angularly.

[0176] The outer wall 25 and the inner wall 26 each comprise a main orifice 81 for introducing a main air flux into the combustion tube and a dilution orifice 82 for introducing a dilution air flux into the combustion tube. Each of the outer wall and the inner wall will be described in detail below.

[0177] The dome 27 extends from the upstream of the outer wall 25 and the inner wall 26 located upstream of the chamber bottom 28. The dome comprises a central opening for housing the corresponding injection system 3 and the injectors 5.

[0178] The chamber bottom 28 comprises an opening for mounting the injection system 3 in which the fuel injectors 5 are engaged.

[0179] Each spark plug 6 is mounted through the outer wall 25 of the combustion chamber. Each spark plug extends transversely to the wall by its longitudinal axis Z-Z which is substantially orthogonal to the longitudinal axis Y-Y of the injection system 3 of the injector 5 located in the vicinity of the spark plug 6.

[0180] The spark plug 6 is used to ignite a piece of air-fuel mixture in the combustion chamber 2 so that the flame then spreads to the adjacent pieces of air-fuel mixture to ignite the combustion chamber 2.

[0181] The injection systems 3 are mounted to the chamber bottom 28 by being spaced apart in the circumferential direction.

[0182] Each injection system 3 comprises from upstream to downstream a sliding feedthrough 34, a swirler 32, a Venturi 35 and a mixing bowl 31. The sliding feedthrough 34, the swirler 32 and the mixing bowl 31 together form an air supply member 30 for producing a piece of fuel-air mixture in which the fuel is injected by the corresponding injector 5.

[0183] Each injection system 3 is connected to one of the fuel injectors 5, said one of the fuel injectors being mounted in the sliding feedthrough 34 at the injector nose. The sliding feedthrough 34 can comprise an air supply orifice.

[0184] The swirler 32 is integrally mounted with the mixing bowl 31. The swirler generally comprises first stage vanes and second stage vanes, the function of which is to rotate the air driven around the axis Y-Y of the injection system 3. The vanes of the first stage of the swirler 32 can rotate in the same direction or in the opposite direction to the vanes of the second stage of the swirler 32.

[0185] The mixing bowl 31 has a flared shape that rotates substantially around the longitudinal axis Y-Y of the injection system 3. It comprises a through hole for supplying air to the combustion chamber 2. The mixing bowl is attached to the chamber bottom 28.

[0186] The diffuser 7 is configured to supply hot pressurized air along the arrow A to the combustion chamber 2, in particular to the injection system 3, the main orifice 81 and the dilution orifice 82.

[0187] The pressurized air is in particular used for the combustion or the cooling of the combustion chamber 2. A part of the air is introduced into the combustion chamber 2 at the central opening of the dome 27, while another part of the air flows to the airflow passages 21 and 23. The air supplied to the injection system 3 flows from the central opening of the dome 27, in particular through the vanes of the injection system 32 and the through hole of the mixing bowl 31. The airflow in the passages 21 and 23, indicated by the arrow B, enters the combustion chamber 2 through the main orifice 81 and the dilution orifice 82. Figure 7

[0188] In combination Figure 8 to Figure 12 , the outer wall 25 comprises a first upstream attachment periphery 70, a first partition 40, a second partition 42, a cooling duct 41 located between the first partition 40 and the second partition 42, a stiffener 44, and a support 29 for each spark plug 6. The outer wall 25 defines radially outwards a combustion tube of the combustion chamber 2.

[0189] Each spark plug support 29 is configured to guide and support the corresponding spark plug 6 in the combustion tube through the outer wall 25. In the illustrated embodiment, each spark plug support 29 is made in one piece with the outer wall 25.

[0190] The first upstream attachment periphery 70 comprises a first upstream attachment edge 71 and a second upstream attachment edge 73. The first upstream attachment periphery is configured to attach the outer wall 25 to the dome 27 and / or to the chamber bottom 28.

[0191] The first upstream attachment edge 71 is located radially inwards of the second upstream attachment edge 73. The first upstream attachment edge extends substantially along the entire circumferential length of the outer wall 25. The first upstream attachment edge 71 is inclined with respect to the first inlet wall 46 of the first cooling duct 41.

[0192] ​The first upstream attachment edge 71 has at least one first hole 83 extending through the first upstream attachment edge, the first hole 83 having a radial component and being located axially close to the first air inlet 45 of the first cooling duct 41. Each first hole 83 serves to introduce air into the combustion duct and / or to cool the first upstream attachment edge 71 in particular by air film. The first upstream attachment edge 71 tends to increase the amount of air introduced into the combustion duct of the combustion chamber 2 while helping to connect the outer wall 25 to the chamber bottom 28 and / or to the fairing 27.

[0193] In the illustrated embodiment, the first upstream attachment edge 71 has two rows of first holes 83 extending through the first upstream attachment edge, each row of first holes extending along substantially the entire circumferential length of the first upstream attachment edge 71.

[0194] The second upstream attachment edge 73 is parallel to the first upstream attachment edge 71. It extends along substantially the entire circumferential length of the outer wall 25. The second upstream attachment edge 73 is inclined with respect to the first inlet wall 46 of the first cooling duct 41 to form a V-shaped opening opening upstream.

[0195] The second upstream attachment edge 73 is designed to co-direct the cooling air towards the first air inlet 45 of the first cooling duct 41 with the first inlet wall 46 while enabling the outer wall 25 to be fixed to the fairing 27 and / or to the chamber bottom 28 by the first upstream attachment edge 71. The second upstream attachment edge 73 tends to increase the amount of air circulating through the first cooling duct 41.

[0196] More particularly with reference to Figure 8 and Figure 9 Each stiffener 44 of the outer wall 25 extends radially from the first partition 40 to the second partition 42. Some of the stiffeners 44 extend axially from the first inlet wall 46 of the first cooling duct 41 for example to the first outlet wall 48. Other of the stiffeners 44 extend axially from the dilution hole 82 to the first outlet wall 48.

[0197] The stiffeners 44 serve to increase the mechanical strength of the outer wall 25. Despite the first partition 40, the second partition 42 and the first cooling duct 41, the outer wall 25 can have a satisfactory mechanical strength compared to a solid outer wall thanks to the presence of the stiffeners 44.

[0198] In combination Figure 8 to Figure 12The first partition 40 of the outer wall 25 is an inner partition of the outer wall 25. The first partition defines the outer wall 25 radially inwardly. The first partition extends axially from an upstream end 40a to a downstream end 40b. The first partition is connected to the first upstream attachment edge 71 and to the first inlet wall 46 at the upstream end 40a. The first partition is connected to the first outlet wall 48 at the downstream end 40b. The first partition extends substantially along the entire circumferential length of the outer wall 25.

[0199] The first partition 40 has at least one second hole 89 passing through the first partition, the at least one second hole 89 having a radial component and being axially located between the main hole 81 and the downstream end 40b. Each second hole 89 is used to introduce air into the combustion pipe and / or to cool the first partition 40, in particular by air film.

[0200] In the illustrated embodiment, the first partition 40 is substantially equidistant from the longitudinal axis X-X of the turbine engine from its upstream end 40a to its downstream end 40b. The first partition 40 has a plurality of second holes 89 passing through the first partition, the second holes extending axially from the main hole 81 to the downstream end 40b and being substantially uniformly distributed.

[0201] The second holes 89 extend substantially along the entire circumferential length of the first partition 40.

[0202] The first partition 40 has a substantially constant thickness from its upstream end 40a to its downstream end 40b. The thickness of the first partition 40 is for example between 35% and 55% of the thickness of the outer wall 25.

[0203] The second partition 42 of the outer wall 25 is an outer partition of the outer wall 25. The second partition defines the outer wall 25 radially outwardly. The second partition 42 is radially spaced apart from the first partition 40 to form the first cooling duct 41 with the first partition 40.

[0204] The second partition 42 extends axially from an upstream end 42a to a downstream end 42b. The second partition is connected to the first inlet wall 46 at the upstream end 42a. The second partition is connected to the first outlet wall 48 at the downstream end 42b. The second partition extends substantially along the entire circumferential length of the outer wall 25.

[0205] In the illustrated embodiment, the second partition 42 has no cooling orifice. The second partition has only the support 29 of the spark plug 6, the main hole 81 and the dilution hole 82 passing through the second partition.

[0206] In the illustrated embodiment, the second partition 42 approaches the longitudinal axis X-X of the turbine engine from its upstream end 42a to an intermediate portion 43 of the second partition 42, which is strictly located between the upstream end 42a and the downstream end 42b. The intermediate portion 43 is in particular located substantially equidistant axially from the upstream end 42a and the downstream end 42b. The second partition 42 extends away from the longitudinal axis X-X of the turbine engine from the intermediate portion 43 to its downstream end 42b.

[0207] The second partition 42 has a substantially constant thickness from its upstream end 42a to its downstream end 42b. The thickness of the second partition 42 is for example between 12% and 35% of the thickness of the outer wall 25.

[0208] The first cooling duct 41 comprises a first air inlet 45 and a first air outlet 47. This first cooling duct is radially internally delimited by the first partition 40. This first cooling duct is radially externally delimited by the second partition 42. This first cooling duct is upstream delimited by the upstream end 40a of the first partition 40, the upstream end 42a of the second partition 42 and the first inlet wall 46. This first cooling duct is downstream delimited by the downstream end 40b of the first partition 40, the downstream end 42b of the second partition 42 and the first outlet wall 48. The first cooling duct 41 is configured to cool the outer wall 25, in particular by the air film passing through the second holes 89, and by the contact of the cooling air with the first partition 40 and the second partition 42.

[0209] The radial extent of the first cooling duct 41 narrows in the downstream direction from the first inlet wall 46 to the intermediate portion 43 of the second partition 42. The ratio of the radial extent e2 at the intermediate portion 43 to the radial extent el at the first inlet wall 46 is for example between 10% and 30%.

[0210] The radial extent of the first cooling duct 41 increases in the downstream direction from the intermediate portion 43 to the first outlet wall 48. The ratio of the radial extent e2 at the intermediate portion 43 to the radial extent e3 at the first outlet wall 48 is for example between 20% and 40%.

[0211] The first air inlet 45 comprises a first inlet wall 46. The first inlet wall 46 extends from the first partition 40 to the second partition 42. The first inlet wall 46 is inclined upstream relative to the radial direction towards the second partition 42. This first inlet wall is mechanically connected to the first upstream attachment edge 71 and to the second upstream attachment edge 73 near the upstream end 40a of the first partition 40. The first inlet wall 46 extends substantially along the entire circumferential length of the outer wall 25.

[0212] The first inlet wall 46 is configured to partially seal the first cooling duct 41 upstream by regulating the air speed and pressure at the first inlet 45.

[0213] The first inlet wall 46 has at least one first inlet hole 85 therethrough, the at least one first inlet hole 85 having an axial component. Each first inlet hole 85 is for introducing air through the first inlet wall 46 generally axially into the first cooling duct 41.

[0214] In the illustrated embodiment, the first inlet wall 46 has two rows of first inlet holes 85 therethrough, each row of first inlet holes extending generally along the entire circumferential length of the first inlet wall 46 and being radially spaced apart from one another. Each first inlet hole 85 is oriented generally axially along the longitudinal axis X-X of the turbine engine.

[0215] The first outlet 47 includes a first outlet wall 48. The first outlet wall 48 extends from the first partition 40 to the second partition 42. The first outlet wall is oriented generally radially to serve as a planar support for a flange for attachment to a turbine wall to which it is to be connected. The first outlet wall 48 extends generally along the entire circumferential length of the outer wall 25.

[0216] The first outlet wall 48 is configured to partially seal the first cooling duct 41 in a downstream direction by regulating the air speed and pressure at the first outlet 47. The first outlet wall is configured to mechanically connect the outer wall 25 to a turbine wall mounting flange.

[0217] The first outlet wall 48 has at least one first outlet hole 87 therethrough, the at least one first outlet hole having an axial component. Each first outlet hole 87 is for discharging air through the first outlet wall 48 generally axially to the first cooling duct 41. The first outlet wall 48 has at least one first attachment hole 74 therethrough from the outer wall 25 to a turbine wall of the turbine engine, such as a high pressure turbine wall of the turbine engine. Each attachment hole 74 is for accommodating an attachment component, such as a screw of a nut, for fastening the outer wall 25 to the turbine wall.

[0218] In the illustrated embodiment, the first outlet wall 48 has one row of first outlet holes 87 therethrough along generally the entire circumferential length of the first outlet wall 48. Each first outlet hole 87 is oriented generally axially along the longitudinal axis X-X of the turbine engine. The first outlet wall 48 has one row of first attachment holes 74 therethrough extending generally along the entire circumferential length of the first outlet wall 48 and being radially spaced apart from the one row of first outlet holes 87.

[0219] Referring to Figure 10The inner wall 26 comprises a second upstream attachment periphery 72, a third partition 50, a fourth partition 52, a second cooling duct 51 located between the third partition 50 and the fourth partition 52, a stiffener (not shown) and an inner attachment collar 90. The inner wall 26 defines, radially inside, a combustion pipe of the combustion chamber 2.

[0220] The second upstream attachment periphery 72 comprises a third upstream attachment edge 75 and a fourth upstream attachment edge 77. This second upstream attachment periphery is configured to attach the inner wall 26 to the fairing 27 and / or to the chamber bottom 28.

[0221] The third upstream attachment edge 75 is located radially inside the fourth upstream attachment edge 77. This third upstream attachment edge extends substantially along the entire circumferential length of the inner wall 26. The third upstream attachment edge 75 is inclined with respect to the second inlet wall 56 of the second cooling duct 51.

[0222] The third upstream attachment edge 75 has at least one third hole 84 passing through the third upstream attachment edge, the third hole 84 having a radial component and being located axially close to the second air inlet 55 of the second cooling duct 51. The third upstream attachment edge 75 tends to increase the amount of air introduced into the combustion pipe of the combustion chamber 2, while helping to connect the inner wall 26 to the chamber bottom 28 and / or to the fairing 27.

[0223] Each third hole 84 serves to introduce air into the combustion pipe and / or to cool the third upstream attachment edge 75, in particular by air film.

[0224] In the illustrated embodiment, the third upstream attachment edge 75 has two rows of third holes 84 passing through the third upstream attachment edge, each of the two rows extending substantially along the entire circumferential length of the third upstream attachment edge 75.

[0225] The fourth upstream attachment edge 77 is parallel to the third upstream attachment edge 75. This fourth upstream attachment edge extends substantially over the entire circumferential length of the inner wall 26. The fourth upstream attachment edge 77 is inclined with respect to the second inlet wall 56 of the second cooling duct 51 to form a V-shaped opening opening upstream.

[0226] The fourth upstream attachment edge is designed to direct cooling air towards the second air inlet 55 of the second cooling duct 51 jointly with the second inlet wall 56, while enabling the inner wall 26 to be fixed to the fairing 27 and / or to the chamber bottom 28 by the third upstream attachment edge 75. The fourth upstream attachment edge 77 tends to increase the amount of air circulating through the second cooling duct 51.

[0227] Each of the reinforcements of the inner wall 26 extends radially from the third partition 50 to the fourth partition 52. Some of the reinforcements extend axially from, for example, the second inlet wall 56 to the second outlet wall 58 of the second cooling duct 51. Other of the reinforcements extend axially from the dilution hole 82 to the second outlet wall 58.

[0228] The reinforcements serve to increase the mechanical strength of the inner wall 26. Despite the third partition 50, the fourth partition 52 and the second cooling duct 51, the inner wall 26 can have a satisfactory mechanical strength compared to a solid inner wall thanks to the presence of the reinforcements.

[0229] The third partition 50 of the inner wall 26 is an outer partition of the inner wall 26. This third partition radially outwardly bounds the inner wall 26. This third partition extends axially from an upstream end 50a to a downstream end 50b. This third partition is connected at the upstream end 50a to the third upstream attachment edge 75 and to the second inlet wall 56. This third partition is connected at the downstream end 50b to the second outlet wall 58. This third partition extends substantially along the entire circumferential length of the inner wall 26.

[0230] The third partition 50 has at least one second hole 89 passing through the third partition, the at least one second hole 89 having a radial component and being axially located between the main hole 81 and the downstream end 50b. Each second hole 89 serves to introduce air into the combustion tube and / or to cool the third partition 50 in particular by air film.

[0231] In the illustrated embodiment, the third partition 50 is substantially equidistant from the longitudinal axis X-X of the turbine engine from its upstream end 50a to its downstream end 50b. The third partition 50 has a plurality of second holes 89 passing through the third partition, the second holes extending axially from the main hole 81 to the downstream end 50b and being substantially uniformly distributed. The second holes 89 extend substantially along the entire circumferential length of the third partition 50.

[0232] The third partition 50 has a substantially constant thickness from its upstream end 50a to its downstream end 50b. The thickness of the third partition 50 is, for example, between 35% and 55% of the thickness of the inner wall 26.

[0233] The fourth partition 52 of the inner wall 26 is an inner partition of the inner wall 26. This fourth partition radially inwardly bounds the inner wall 26. The fourth partition 52 is radially spaced apart from the third partition 50 to form the second cooling duct 51 with the third partition 50.

[0234] This fourth partition 52 extends axially from an upstream end 52a to a downstream end 52b. This fourth partition is connected at the upstream end 52a to the first inlet wall 56. This fourth partition is connected at the downstream end 52b to the second outlet wall 58. This fourth partition extends substantially along the entire circumferential length of the inner wall 26.

[0235] In the illustrated embodiment, the fourth partition 52 is devoid of cooling orifices. It has only the main hole 81 and the dilution hole 82 passing through the fourth partition.

[0236] In the illustrated embodiment, the fourth partition 52 is proximate to the longitudinal axis X-X of the turbine engine from its upstream end 52a to an intermediate portion 53 of the fourth partition 52, which is strictly located between the upstream end 52a and the downstream end 52b. The intermediate portion 53 is in particular located substantially equidistant in the axial direction from the upstream end 52a and the downstream end 52b. The fourth partition 52 extends away from the longitudinal axis X-X of the turbine engine from the intermediate portion 53 to its downstream end 52b.

[0237] The fourth partition 52 has a substantially constant thickness from its upstream end 52a to its downstream end 52b. The thickness of the fourth partition 52 is for example between 12% and 35% of the thickness of the inner wall 26.

[0238] The second cooling duct 51 comprises a second air inlet 55 and a second air outlet 57. It is radially outwardly delimited by the third partition 50 and radially inwardly delimited by the fourth partition 52. It is defined upstream by the upstream end 50a of the third partition 50, the upstream end 52a of the fourth partition 52 and the second inlet wall 56. It is defined downstream by the downstream end 50b of the third partition 50, the downstream end 52b of the fourth partition 52 and the second outlet wall 58. The second cooling duct 51 is configured to cool the inner wall 26, in particular by the air film passing through the second hole 89, and the outer wall by the contact of the cooling air with the third partition 50 and the fourth partition 52.

[0239] The radial extent of the second cooling duct 51 narrows in the downstream direction from the second inlet wall 56 to the intermediate portion 53 of the fourth partition 52. The ratio of the radial extent e5 at the intermediate portion 53 to the radial extent e4 at the second inlet wall 56 is for example between 35% and 45%.

[0240] The radial extent of the second cooling duct 51 increases in the downstream direction from the intermediate portion 53 to the second outlet wall 58. The ratio of the radial extent e5 at the intermediate portion 53 to the radial extent e6 at the second outlet wall 58 is for example between 55% and 65%.

[0241] The second air inlet 55 comprises a second inlet wall 56. The second inlet wall 56 extends from the third partition 50 to the fourth partition 52. The second inlet wall is inclined upstream relative to the radial direction towards the fourth partition 52. This second inlet wall is mechanically connected to the third upstream attachment edge 75 and to the fourth upstream attachment edge 77 near the upstream end 50a of the third partition 50. The second inlet wall 56 extends substantially along the entire circumferential length of the inner wall 26.

[0242] The second inlet wall 56 is configured to partially seal the second cooling duct 51 upstream by regulating the air speed and pressure at the second air inlet 55.

[0243] The second inlet wall 56 has at least one second inlet hole 86 therethrough, the at least one second inlet hole having an axial component. Each second inlet hole 86 serves to introduce air substantially axially through the second inlet wall 56 into the second cooling duct 51.

[0244] In the illustrated embodiment, the second inlet wall 56 has two rows of second inlet holes 86 therethrough, the two rows of second inlet holes extending substantially along the entire circumferential length of the second inlet wall 56 and being radially spaced apart from each other. Each second inlet hole 86 is oriented substantially axially along the longitudinal axis X-X of the turbine engine.

[0245] The second air outlet 57 comprises a second outlet wall 58. The second outlet wall 58 extends from the third partition 50 to the fourth partition 52. This second outlet wall is oriented substantially radially to serve as a planar support for a flange for attachment to the turbine wall to which it is to be connected. The second outlet wall 58 extends substantially along the entire circumferential length of the inner wall 26.

[0246] The second outlet wall 58 is configured to partially seal the second cooling duct 51 in the downstream direction by regulating the air speed and pressure at the second air outlet 57. This second outlet wall is configured to mechanically connect the inner wall 26 to a turbine wall attachment flange.

[0247] The second outlet wall 58 has at least one second outlet hole 88 therethrough, the at least one second outlet hole having an axial component. Each second outlet hole 88 serves to discharge air substantially axially through the second outlet wall 58 to the second cooling duct 51. The second outlet wall 58 has at least one second attachment hole 78 therethrough from the inner wall 26 up to a turbine wall of the turbine engine, for example a high-pressure turbine wall of the turbine engine. Each second attachment hole 78 serves to accommodate an attachment member, such as a screw, for fastening the inner wall 26 to the turbine wall.

[0248] In the illustrated embodiment, the second outlet wall 58 has a row of second outlet holes 88 therethrough that extends substantially along the entire circumferential length of the second outlet wall 58. Each second outlet hole 88 is oriented substantially axially along the longitudinal axis X-X of the turbine engine. The second outlet wall 58 has a row of second attachment holes 78 therethrough that extends substantially along the entire circumferential length of the second outlet wall 58 and is radially spaced apart from the row of second outlet holes 88.

[0249] In combination Figure 7 and Figure 10 The inner attachment collar 90 of the inner wall 26 projects radially inwardly and upstream from the second outlet wall 58. The inner attachment collar 90 comprises a downstream portion 94 and an upstream attachment rim 92. The inner attachment collar 90 serves to attach the inner wall 26 to the inner casing wall 24 of the combustion chamber 2.

[0250] The downstream portion 94 extends axially upstream from the second outlet wall 58. The downstream portion comprises a plurality of downstream apertures 95. The upstream attachment rim 92 extends radially inwardly from an upstream end of the downstream portion 94. The upstream attachment rim 92 comprises a plurality of attachment holes 93 for attaching the upstream attachment rim 92 to an attachment rim of the inner casing wall 24 that supports the upstream attachment rim by means of attachment members, each attachment member comprising for example a screw and a nut.

[0251] The outer wall 25 and the inner wall 26 of the combustion chamber 2 are each manufactured by selective melting or selective sintering on a powder bed, in particular by means of a laser. In other words, in the illustrated embodiment, the outer wall 25 and the inner wall 26 are each made by additive manufacturing.

[0252] By means of the combustion chamber 2, the cooling of the outer wall 25 and the cooling of the inner wall 26 are improved.

[0253] In particular, the flow-through of cooling air from the first inlet wall 46 to the first outlet wall 48 of the first cooling duct 41 makes it possible to improve the cooling of the outer wall 25.

[0254] The first cooling duct 41 in particular facilitates a continuous and uniform flow-through of cooling air in the outer wall 25. Since the cooling air that flows through the first cooling duct 41 tends to be separated from the hot combustion gases, for example by means of the first partition 40, the cooling of the outer wall 25 is more effective.

[0255] The combustion is provided by means of the main flow-through through the main apertures 81 and the dilution flow-through through the dilution apertures 82 of the outer wall 25, such that the first cooling duct 41 does not, for example, interfere with the combustion in the combustion tube of the combustion chamber 2.

[0256] The cooling of the outer wall 25 is further improved by facilitating the flow of cooling air from the first inlet hole 85 of the first inlet wall 46 to the first outlet hole 87 of the first outlet wall 48.

[0257] The second holes 89 in the outer wall 25 in particular enable a film cooling of the first wall 40 close to the hot combustion gases in the combustion tube to improve the cooling of the first wall 40. The second holes 89 also enable additional air to be introduced into the combustion tube of the combustion chamber 2 through the outer wall 25 to facilitate combustion.

[0258] When the first cooling duct 41 narrows in the downstream direction from the first air inlet 45, the cooling air in the first cooling duct 41 is accelerated, thereby increasing the cooling rate to cool the outer wall 25. The pressure loss of the cooling air is also limited when the cooling air enters the first cooling duct 41.

[0259] The first outlet wall 48 in particular enables the outer wall 25 to be connected to a turbine wall while enabling air to be discharged from the first cooling duct 41. The air pressure tends to increase at the first outlet 47 to supply cooling air to a high pressure turbine for example.

[0260] In particular, thanks to the presence of the first partition 40, the second partition 42 and the first cooling duct 41, the outer wall 25 can be additively manufactured, enabling the outer wall 25 to have a complex shape.

[0261] In addition, in particular, the flow of cooling air from the second inlet wall 56 of the second cooling duct 51 to the second outlet wall 58 enables the cooling of the inner wall 26 to be improved.

[0262] The second cooling duct 51 in particular facilitates a continuous and uniform flow of cooling air in the inner wall 26. Since the cooling air flowing in the second cooling duct 51 tends to be separated from the hot combustion gases, for example by the third partition 50, the cooling of the inner wall 26 is more effective.

[0263] The combustion is provided by the main flux through the main holes 81 and the dilution flux through the dilution holes 82 of the inner wall 26, so that the second cooling duct 51 does not, for example, interfere with the combustion in the combustion tube of the combustion chamber 2.

[0264] The cooling of the inner wall 26 is further improved by facilitating the flow of cooling air from the second inlet hole 86 of the second inlet wall 56 to the second outlet hole 88 of the second outlet wall 88.

[0265] The second holes 89 in the inner wall 26 in particular enable a film cooling of the third wall 50 close to the hot combustion gases in the combustion tube to improve the cooling of the third wall 50. The second holes 89 also enable additional air to be introduced into the combustion tube of the combustion chamber 2 through the inner wall 26 to facilitate combustion.

[0266] When the second cooling duct 51 narrows in the downstream direction from the second air inlet 55, the cooling air in the second cooling duct 51 is accelerated, thereby increasing the cooling rate to cool the inner wall 26. The pressure loss of the cooling air is also limited when the cooling air enters the second cooling duct 51.

[0267] The second outlet wall 58 in particular enables the inner wall 26 to be connected to a turbine wall, while enabling air to be discharged from the second cooling duct 51. The air pressure tends to increase at the second outlet 57 of the second cooling duct 51, for example to supply cooling air to a high-pressure turbine.

[0268] In particular, thanks to the presence of the third partition 50, the fourth partition 52 and the second cooling duct 51, the inner wall 26 can be additively manufactured, so that it can have a complex shape.

[0269] Of course, the person skilled in the art can make various modifications to the invention described above, without departing from the scope of the invention. In particular, the structure of the tool 20, the structure of the wall 10 and the manufacturing method 100 can be changed.

[0270] The number, the geometry and the distribution of the first cooling holes 40 and of the second cooling holes 44 can be changed. For example, the wall 10 can comprise only first cooling holes 40.

[0271] Additionally alternatively, at least one second cooling hole 44 in the wall can be devoid of a circular portion. In this case, the inlet 43 and / or the outlet 45 of the wall can be machined after the additive manufacturing step 105.

[0272] Alternatively, the wall 10 can be manufactured with an upper region 19c having a thickness, for example less than or equal to 0.06 mm, in the vicinity of the first cooling holes 40.

[0273] In this case, the thickness parameter of the upper skin region 19c, also called "thickness of the upskin", is in particular defined as the thickness of all the layers of the upper skin region 19c manufactured by so-called upskinning.

[0274] By thin upper skin region 19c, the manufacturing defects of each first cooling hole 40 are reduced compared to a wall 10 additively manufactured according to the methods known in the prior art. In particular, the undesirable material deposition at the bottom of each first cooling hole 40 is limited.

[0275] Each upper region 19c of the wall 10 is manufactured, for example, by a third energy input per length Ec on the powder bed 17, which is between 0.1300 J / mm and 0.1950 J / mm, preferably 0.1625 J / mm.

[0276] In particular, the third energy input per length Ec is approximately equal to the second energy input per length Eb, wherein the upper region 19c has twice the energy exposure relative to the middle region 19b.

[0277] The lower value of the first energy input per length Ea relative to the third energy input per length Ec enables, in particular, less melting / agglomeration of the powder 17 during the manufacturing of the lower region 19a than during the manufacturing of the upper region 19c. This enables a reduction of manufacturing defects of the first cooling hole 40 by increasing the volume of the lower region 19a.

[0278] In general, the first energy input per length Ea, the second energy input per length Eb and / or the third energy input per length Ec, in particular along the wall 10, can have different values. The third energy input per length Ec can in particular have a different value than the second energy input per length Eb.

[0279] The manufacturing method 100 can not comprise the machining 110 of the wall blank 10 and / or the machining 112 of the plate-shaped piece 28.

[0280] In particular, only the outer wall 25 can comprise the two partitioning portions 40, 42. In this case, the cooling of the outer wall 25 is in particular improved relative to the cooling of the inner wall 26.

[0281] Furthermore alternatively, only the inner wall 26 can comprise the two partitioning portions 50, 52. In this case, the cooling of the inner wall 26 is in particular improved relative to the cooling of the outer wall 25.

[0282] The air inlet of the first cooling duct 41 can be radially oriented and / or at a distance from the first inlet wall 46. The air outlet of the first cooling duct 41 can be radially oriented and / or at a distance from the first outlet wall 48.

[0283] The air inlet of the second cooling duct 51 can be radially oriented and / or at a distance from the second inlet wall 56. The air outlet of the second cooling duct 51 can be radially oriented and / or at a distance from the second outlet wall 58.

[0284] Alternatively, the first partitioning portion wall 40 has no cooling hole. Alternatively, the third partitioning portion wall 50 can have no cooling hole.

[0285] Alternatively, the first upstream attachment perimeter 70 is spaced from the first air inlet 45 of the first cooling duct 41 so as not to promote air entry into the first cooling duct 41.

[0286] The second upstream attachment perimeter 72 can be spaced from the second inlet 55 of the second cooling duct 51 so as not to promote air entry into the second cooling duct 51.

[0287] Alternatively, the radial extent of the first cooling duct 41 is substantially constant. The radial extent of the second cooling duct 51 can be substantially constant.

[0288] Alternatively, the first outlet wall 48 is devoid of attachment holes 74. In this case, the outer wall 25 can comprise additional attachment flanges for attachment to the turbine casing.

[0289] The second outlet wall 58 can be devoid of attachment holes 78. In this case, the inner wall 26 can comprise additional attachment flanges for attachment to the turbine casing.

[0290] The outer wall 25 and / or the inner wall 26 can be devoid of stiffeners, for example, when the thickness of the partitions 40, 50, 42, 52 of the outer wall 25 and / or of the inner wall 26 is sufficient to give them a satisfactory mechanical rigidity.

[0291] The outer wall 25 and / or the inner wall 26 can be manufactured by means other than selective melting or selective sintering on a powder bed, in particular by casting or by another additive manufacturing method.

Claims

1. An additive manufacturing method (100) for a wall (10) of a turbine engine, wherein, The wall (10) includes a first cooling hole (40), wherein the manufacturing method (100) includes additive manufacturing (101) of the wall (10) by selective melting or selective sintering on a powder bed (17). The wall (10) is characterized in that it is manufactured to have a lower region (19a) at least partially surrounding the first cooling hole (40), the lower region at least partially defining the first cooling hole, the lower region having a total thickness (ea) between 0.06 mm and 0.22 mm in at least one longitudinal cross-section of the wall (10), wherein a first energy input per unit length for manufacturing the lower region (19a) is less than a second energy input per unit length for manufacturing the intermediate region (19b), the intermediate region forming most of the volume of the wall (10). When the wall (10) is manufactured substantially vertically on the support (28) by additive manufacturing, the lower region (19a) is located in the upper portion of the first cooling hole (40). The wall (10) is manufactured to have an upper region (19c) surrounding the first cooling hole (40) with a thickness of less than or equal to 0.06 mm.

2. The additive manufacturing method (100) according to claim 1, wherein, The lower region (19a) is manufactured to have a minimum lower region length (La) between 0.01 mm and 0.4 mm, wherein the minimum lower region length (La) is the minimum powder curing length that enables the lower region (19a) to be formed.

3. The additive manufacturing method (100) according to claim 1, wherein, The lower region (19a) has a minimum lower region length (La) equal to 0.05 mm, and / or the lower region (19a) has a total thickness (ea) equal to 0.12 mm.

4. The additive manufacturing method (100) according to claim 1, wherein, The energy input per unit length used to create the upper region (19c) is equal to the energy input per unit length used to create the middle region (19b) which forms most of the volume of the wall (10), but the upper region has twice the energy exposure relative to the middle region (19b).

5. The additive manufacturing method (100) according to claim 1, wherein, The support member (28) is a manufactured plate-shaped member.

6. The additive manufacturing method (100) according to claim 1, wherein, The lower region (19a) is manufactured by a first energy input (Ea) per unit length on the powder bed (17), the first energy input per unit length being between 0.0200 J / mm and 0.0300 J / mm, and / or The central region surrounding the first cooling hole (40) is manufactured by a second energy input (Eb) per unit length of the powder bed (17), the second energy input per unit length being between 0.1300 J / mm and 0.1950 J / mm.

7. The additive manufacturing method (100) according to claim 6, wherein, The lower region (19a) is manufactured by a first energy input (Ea) per unit length on the powder bed (17), the first energy input per unit length being 0.0250 J / mm, and / or The central region surrounding the first cooling hole (40) is manufactured by a second energy input (Eb) per unit length of the powder bed (17), the second energy input per unit length being 0.1625 J / mm.

8. The additive manufacturing method (100) according to claim 1, wherein, The wall (10) is manufactured to have an upper region (19c) surrounding the cooling hole (40), the upper region being manufactured by a third energy input (Ec) per unit length on the powder bed (17) between 0.1300 J / mm and 0.1950 J / mm.

9. The additive manufacturing method (100) according to claim 8, wherein, The wall (10) is manufactured to have an upper region (19c) surrounding the cooling hole (40), the upper region being manufactured by a third energy input (Ec) per unit length on the powder bed (17) of 0.1625 J / mm, and / or Wherein, the third energy input (Ec) per unit length is equal to the second energy input (Eb) per unit length, wherein the upper region (19c) has twice the energy exposure relative to the middle region (19b).

10. The additive manufacturing method (100) according to claim 1, wherein, The first cooling hole (40) extends around the longitudinal axis (R2-R2) of the first cooling hole, and the longitudinal axis of the first cooling hole is orthogonal to the outer surface (S3, S4) of the wall (10).

11. The additive manufacturing method (100) according to claim 10, wherein, During the additive manufacturing (101) of the wall (10), the wall (10) extends perpendicular to the support (28).

12. The additive manufacturing method (100) according to claim 1, wherein, The first cooling hole (40) is digitally modeled as having a generally elliptical transverse surface so as to be manufactured as having a generally circular transverse cross section by selective melting or selective sintering on a powder bed (17).

13. The additive manufacturing method (100) according to claim 1, wherein, The wall (10) includes at least one second cooling hole (44) oriented about a longitudinal axis (R1-R1) of the second cooling hole, the longitudinal axis of the second cooling hole being inclined at an angle (γ) relative to the outer surface (S3, S4) of the wall, the angle being between 5° and 45° in at least one cross-sectional plane of the wall (10).

14. The additive manufacturing method (100) according to claim 1, wherein, The wall (10) includes at least one second cooling hole (44) oriented about a longitudinal axis (R1-R1) of the second cooling hole, the longitudinal axis of the second cooling hole being inclined at an angle (γ) relative to the outer surface (S3, S4) of the wall, the angle being 20° in at least one cross-sectional plane of the wall (10).

15. The additive manufacturing method (100) according to claim 14, wherein, The inlet (43) and / or outlet (45) of the second cooling hole (44) are made with circular portions (43a, 45a).

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