Turbomachine component, turbomachine having it and method of manufacturing it

Abstract

The invention relates to a turbomachine component (1) of a turbomachine, comprising a wall (10) having at least one cooling bore (3) obliquely at a predetermined angle (α) with respect to the thickness direction (Z), the cooling bore (3) comprising a metering portion (31) delimited by a metering surface (310), and a diffusion portion (32) delimited by a diffusion surface (320). The invention is characterized in that the diffusion surface (320) is connected to the metering surface (310) by a connecting surface (35), which is inclined relative to a downstream portion (312) of the metering surface (310) and relative to a downstream portion (323) of the diffusion surface (320), such that the connecting surface (35) forms a step at the junction therebetween. Figure for abstract: Figure. 1

Description

Title of the invention: Turbomachine component, Payant turbomachine and method of manufacturing the same

[0001] The invention relates to a turbomachine component, a turbomachine comprising this component, as well as a method of manufacturing the latter.

[0002] The field of the invention relates in particular to turbomachine blades.

[0003] Turbomachine blades are subjected to high temperatures during operation of the turbomachine, which may exceed the melting temperature of the material(s) of these blades, and therefore require means for cooling these blades.

[0004] One of the known ways to cool these blades is to drill through holes in their wall to cool them by pumping effect on the one hand and by film cooling on the other hand. These holes made in the walls are supplied by cooler air feeding internal cooling cavities of the blades.

[0005] Document FR-A-3 106 157 describes a turbomachine component having through cooling holes, comprising a bore extending into a flared mouth.

[0006] Methods are known for manufacturing these through holes by so-called advanced drilling, obtained by electro-erosion machining (in English: Electro Discharge Machining) using an electrode.

[0007] A disadvantage of these manufacturing processes is their complexity and the high time spent making each hole. Another disadvantage is the non-quality rate linked to the machining of holes, which remains high.

[0008] An objective of the invention is to obtain a turbomachine component, a turbomachine provided with this component, as well as a method of manufacturing the latter, which overcome the drawbacks mentioned above.

[0009] For this purpose, a first object of the invention is a turbomachine component, intended to be cooled by a gaseous cooling fluid, comprising a wall having a first surface and a second surface, which is opposite the first surface, the distance which separates the first surface and the second surface defining a thickness direction of the wall, at least one cooling bore passing through the wall opening on the one hand, at the first surface and, on the other hand, at the second surface, the cooling bore being oblique by a predetermined angle (a) in a section plane comprising the thickness direction and being configured to allow in operation a flow of gaseous fluid going from upstream to downstream, from the first surface to the second surface, the cooling bore comprising a metering portion, which opens onto the first surface and which is delimited by a metering surface, and a diffusion portion, which opens onto the second surface and which is delimited by a diffusion surface, the diffusion portion having a passage cross-section, which is larger than the passage cross-section of the metering portion, characterized in that the diffusion surface is connected to the metering surface by a connecting surface, which, in the section plane comprising the thickness direction, is inclined relative to a downstream portion of the metering surface and relative to a downstream portion of the diffusion surface, so that the connecting surface forms a step at the junction between the downstream portion of the metering surface and the downstream portion of the diffusion surface.

[0010] According to one embodiment of the invention, the first surface is an internal surface of the component, at least partially delimiting an internal cavity of the component, and the second surface is an external surface of the component.

[0011] According to one embodiment of the invention, the diffusion surface has a cylindrical portion whose axis of revolution is inclined according to the predetermined angle.

[0012] According to one embodiment of the invention, the connecting surface comprises a first lateral lobe and a second lateral lobe, the lobes being located on either side of a median direction of the cooling bore, the median direction being substantially parallel to a direction going from upstream to downstream and to a first tangent plane taken at the intersection of the first surface and the metering surface and / or to a second tangent plane taken at the intersection of the second surface and the diffusion surface.

[0013] According to one embodiment of the invention, the first side lobe and the second side lobe are symmetrical with respect to the median direction of the cooling bore.

[0014] According to one embodiment of the invention, the connecting surface is formed by a blind hole forming part of the diffusion portion.

[0015] According to one embodiment of the invention, the connecting surface is substantially flat.

[0016] According to one embodiment of the invention, the connecting surface is substantially parallel to a first tangent plane taken at the intersection of the first surface and the dosing surface and / or is substantially parallel to a second tangent plane taken at the intersection of the second surface and the diffusion surface.

[0017] According to one embodiment of the invention, the predetermined angle is greater than or equal to 30° and less than or equal to 60° relative to the thickness direction.

[0018] According to one embodiment of the invention, the turbomachine component consists of a turbomachine blade.

[0019] According to one embodiment of the invention, the turbomachine component consists of a turbomachine turbine blade.

[0020] According to one embodiment of the invention, the turbomachine component consists of a turbomachine turbine blade.

[0021] A second object of the invention is a turbomachine comprising at least one turbomachine component as described above.

[0022] A third subject of the invention is a method for manufacturing a turbomachine component from a part having a wall having a first surface and a second surface which is opposite the first surface, the distance which separates the first surface and the second surface defining a thickness direction of the wall, the method comprising during a first step, a movement of an electroerosion electrode having a rectilinear pin, which ends with a free end against the second surface in the wall, the electrode being inclined at a predetermined angle relative to the thickness direction to produce in the wall a first drilling part, which is cylindrical and passes through a second opening of the second surface to a first opening of the first surface, which is inclined at the predetermined angle and which goes in a direction going from upstream to downstream and from the first surface to the second surface,characterized in that the method further comprises the following steps: during a second step, partial withdrawal of the electroerosion electrode having the pin inclined at the predetermined angle in the first drilling part, to position the free end of the electroerosion electrode at a first non-zero distance from the first opening at the predetermined angle and at a second non-zero distance from the second opening at the predetermined angle, during a third step, moving the electroerosion electrode having the pin inclined at the predetermined angle in the direction from upstream to downstream, to produce in the wall from the first drilling part a second drilling part, the part having the first drilling part and the second drilling part forming the turbomachine component as described above,whose cooling bore is formed by the first bore part and the second bore part.

[0023] According to one embodiment of the invention, the second drilling part comprises a cylindrical portion, the axis of revolution of this cylindrical portion being parallel to the first drilling part at the predetermined angle.

[0024] The invention will be better understood on reading the description which follows, given solely by way of non-limiting example with reference to the figures below of the attached drawings.

[0025] [Fig. 1] represents a schematic view in vertical section of the wall of a turbomachine component according to an embodiment of the invention.

[0026] [Fig.2] represents a partial schematic top view of the wall of a turbomachine component according to a first embodiment of the invention.

[0027] [Fig.3] represents a schematic partial perspective view of the wall of a turbomachine component according to the first embodiment of the invention.

[0028] [Fig.4] represents a partial schematic top view of the wall of a turbomachine component according to a second embodiment of the invention.

[0029] [Fig.5] represents a schematic partial perspective view of the wall of a turbomachine component according to the second embodiment of the invention.

[0030] [Fig.6] schematically represents an initial stage of a manufacturing process of the turbomachine component according to one embodiment of the invention.

[0031] [Fig.7] schematically represents a first step of a manufacturing process of the turbomachine component according to an embodiment of the invention.

[0032] [Fig.8] schematically represents a second step of a manufacturing process of the turbomachine component according to an embodiment of the invention.

[0033] [Fig.9] schematically represents a third step of a manufacturing process of the turbomachine component according to an embodiment of the invention.

[0034] [Fig. 10] schematically represents a fourth step of a method of manufacturing the turbomachine component according to an embodiment of the invention.

[0035] [Fig. 11] schematically represents an example of a turbomachine in which the turbomachine component according to an embodiment of the invention can be used.

[0036] [Fig. 12] Schematic perspective view of a turbomachine blade forming the turbomachine component according to one embodiment of the invention.

[0037] An example embodiment of a turbomachine component 1 and a method of manufacturing the latter are described in more detail below with reference to FIGS. 1 to 12.

[0038] The turbomachine component 1 comprises a wall 10 having a first surface 11 and a second surface 12, which are distant from each other relative to a local thickness direction Z of the wall 10, normal to them. One (or more) through bores 3, going from the first surface 11 to the second surface 12, is provided in the wall 10. The cooling bore 3 passes through the wall 10 (or is open). The cooling bore 3 is oblique at an angle a predetermined with respect to the thickness direction Z, namely in a cutting plane containing the thickness direction Z. The cooling bore 3 is oblique and goes both in a direction SI going from upstream to downstream and from the first surface 11 to the second surface 12. The cooling bore 3 makes it possible to pass a cooling fluid from the first surface 11 to the second surface 12. The direction S1 is a direction locally included in the first surface 11 and in the second surface 12. The other lateral direction Y of the first surface 11 and of the second surface 12 is perpendicular to the direction SI and to the local thickness direction Z.

[0039] According to one embodiment of the invention, the first surface 11 is an internal surface of the component 1, delimiting an internal cavity 25 of the component 1, and the second surface 12 is an external surface of the component 1. As shown by way of example in [Fig. 12], the component 1 may have another wall 20 which delimits the internal cavity 25 with the first internal surface 11 of the wall 10. In a first embodiment of the component 1, the other wall 20 is not of the same type as the wall 10 and does not include cooling holes 3. In a second embodiment of the component 1, the other wall 20 is of the same type as the wall 10 and includes one (or more) cooling holes 3 as described for the wall 10.

[0040] The cooling bore 3 comprises a metering portion 31, which opens through a first opening 111 onto the first surface 11 and which is delimited by a metering surface 310, and a diffusion portion 32, which opens through a second opening 121 onto the second surface 12 and which is delimited by a diffusion surface 320. The diffusion portion 32 has a second fluid passage cross-section, which is larger (or wider) than a first fluid passage cross-section of the metering portion 31. The direction SI going from upstream to downstream therefore goes from the metering portion 31 to the diffusion portion 32, from the first opening 111 to the second opening 121, from the metering surface 310 to the diffusion surface 320 and from the first fluid passage cross-section to the second fluid passage cross-section.The direction SI is substantially parallel to a first tangent plane PI taken at the intersection of the first surface 11 and the dosing surface 310, that is to say at the level of the opening 111 and / or is substantially parallel to a second tangent plane P2 taken at the intersection of the second surface 12 and the diffusion surface 320, that is to say at the level of the opening 121.

[0041] The diffusion surface 320 is connected to the dosing surface 310 by a connecting surface 35, which is inclined relative to a downstream part 312 of the dosing surface 310 and relative to a downstream part 323 of the diffusion surface 320. The downstream part 312 of the metering surface 310 is downstream in the direction SI relative to an upstream portion 313 of the metering surface 310. The downstream portion 323 of the diffusion surface 320 is downstream in the direction SI relative to an upstream portion 324 of the diffusion surface 320. The connecting surface 35 is downstream in the direction SI relative to the upstream portion 313 of the metering surface 310. The downstream portion 323 of the diffusion surface 320 is offset by the connecting surface 35 relative to the downstream portion 312 of the metering surface 310. The connecting surface 35 forms a step 35 (or an edge 35) at the junction between the downstream portion 312 of the metering surface 310 and the downstream portion 323 of the diffusion surface 320. The connecting surface 35 is at a first non-zero distance DI from the first opening 111 along the predetermined angle a and at a second non-zero distance D2 from the second opening 121 along the predetermined angle a.The connecting surface is therefore inclined in the cutting plane comprising the thickness direction Z relative to the downstream part 312 of the dosing surface 310 and relative to the downstream part 323 of the diffusion surface 320.

[0042] The invention thus makes it possible to reduce the manufacturing time of the turbomachine component, while having good cooling efficiency of the wall 10 by a fluid (for example air) passing through the cooling bore 3 from the first opening 111 to the second opening 121 in the fluid flow direction F. The diffusion portion 32, which is located downstream and wider than the metering portion 31, allows the recirculation of a film of cooling fluid in this diffusion portion 32, and thus to delay the mixing of this fluid with the hot air in the vein on the second surface 12 against the wall 10.

[0043] According to one embodiment of the invention, the diffusion surface 320 has a cylindrical portion whose axis of revolution is inclined according to the predetermined angle α. The metering surface 310 may have a cylindrical portion whose axis of revolution is inclined according to the predetermined angle α. According to one embodiment, the diffusion surface 320 is cylindrical according to the predetermined angle α and is parallel to the metering surface 310, also cylindrical according to the predetermined angle α. The upstream portion 324 of the diffusion surface 320 may extend according to the predetermined angle α the upstream portion 313 of the metering surface 310.For example, the metering surface 310 and the diffusion surface 320 may be cylindrical and in the shape of a portion of an ellipse (for example in FIGS. 2 and 3) or in the shape of several portions of an ellipse (for example in FIGS. 4 and 5) in planes parallel to the first surface 11 and / or to the second surface 12, i.e. parallel to a first tangent plane PI taken at the intersection of the first surface 11 and the metering surface 310 and containing the direction SI and the other lateral direction Y and / or to a second tangent plane P2 taken at the intersection of the second surface 12 and the diffusion surface 320 and containing the direction SI and the other lateral direction Y.

[0044] The turbomachine component 1 may be, for example, a turbomachine blade, in particular one (or more) turbomachine turbine blades.

[0045] A method of manufacturing the turbomachine component 1 by machining using an electro-erosion electrode 501 is described below with reference to FIGS. 6 to 10. The electro-erosion electrode 501 comprises a straight pin 503 ending in a free end 502 and is used to produce the cooling bore 3.

[0046] During an initial step E0 in [Fig.6], the wall 10 of the turbomachine component 1, initially formed by a part 1a, is provided.

[0047] Then, during a first step E1 in [Fig. 7], the rectilinear pin 503 of the electroerosion electrode 501 is moved against the second surface 12 in the wall 10, the rectilinear pin 503 being inclined at the predetermined angle a, to produce a first drilling portion 41 in the wall 10. The first drilling portion 41 is cylindrical and passes through (or emerges from) the second opening 121 of the second surface 12 to the first opening 111 of the first surface 11 at the predetermined angle a. The first drilling portion 41 is inclined at the predetermined angle a and goes in the direction S1 from upstream to downstream and from the first surface 11 to the second surface 12.

[0048] Then, during a second step E2 in [Fig. 8], the pin 503 of the electroerosion electrode 501 inclined at the predetermined angle a is partially removed from the first drilling part 41, in order to position the free end 502 of the electroerosion electrode in the first drilling part 41 at a first non-zero distance DI from the first opening 111 at the predetermined angle a and at a second non-zero distance D2 from the second opening 121 at the predetermined angle a.

[0049] Then, during a third step E3 in [Fig. 9], the rectilinear pin 503 of the electroerosion electrode 501 inclined at the predetermined angle a is moved in the direction SI going from upstream to downstream, to produce in the wall 10 from the first drilling part 41 one (or more) second drilling parts 42. The second drilling part 42 forms the downstream part of the diffusion portion 32. The second drilling part 42 is cylindrical at the predetermined angle a and is parallel to the first drilling part 41 at the predetermined angle a. The second drilling part 42 communicates with the first drilling part 41. The second drilling part 42 is produced by scanning the rectilinear pin 503 of the electroerosion electrode 501 which is inclined at the predetermined angle a to have the desired shape of the downstream part of the diffusion portion 32.The second drilling part 42 does not open towards the first surface 11. The third step E3 can be carried out several times to produce several second ones. drilling parts 42, such as for example the second drilling part 42a and the other second drilling part 42b in Figures 4 and 5.

[0050] Thus, in [Fig. 10], during the fourth step E4 after the third step E3, we obtain the turbomachine component 1 formed by the part 1a having the first drilling part 41 and the second drilling part 42. The cooling drilling 3 is formed by the first drilling part 41 and by the second drilling part 42. The first drilling part 41 and the second drilling part(s) 42 are delimited by the metering surface 310, the diffusion surface 320 and the connecting surface 35.

[0051] According to one embodiment of the invention, the second drilling part 42 comprises a cylindrical portion, the axis of revolution of this cylindrical portion being parallel to the first drilling part 41 along the predetermined angle α. Thus, the second drilling part 42 can be cylindrical along the predetermined angle α and be parallel to the first drilling part 41 along the predetermined angle α.

[0052] According to one embodiment of the invention, the connecting surface 35 is formed by a downstream blind hole 33 (or non-opening) forming part of the diffusion portion 32. The blind hole 33 is formed by the second drilling part 42.

[0053] The connecting surface 35 may be substantially planar in a plane distant from the first surface 11 and the second surface 12 and may for example be substantially parallel to the first tangent plane PI taken at the intersection of the first surface 11 and the dosing surface 310 and / or is substantially parallel to the second tangent plane P2 taken at the intersection of the second surface 12 and the diffusion surface 320.

[0054] According to one embodiment of the invention, the predetermined angle a is greater than or equal to 30° and less than or equal to 60° relative to the thickness direction (Z).

[0055] Figures 2 and 3 show a first example of a possible shape for the cooling bore 3. [Fig. 2] shows a top view of the shape of the second opening 121 in the second surface 12, the other parts of the wall 10 located under the second surface 12 not being shown. [Fig. 3] shows a perspective view of the cooling bore 3, the parts of the wall 10 not being shown. In Figures 2 and 3, the second bore part 42 is located in the extension in the direction SI downstream relative to the first bore part 41 above the connecting surface 35.

[0056] In Figures 2 and 3, the manufacturing method according to the invention makes it possible to have in the diffusion surface 320 connecting the first drilling part 41 to the second drilling part 42 a transition zone 321, which is flat in planes parallel to the direction SI and to the direction Z of local thickness. This avoids in this transition zone 321 a narrowing of the fluid passage cross-section of the cooling drilling 3 in the direction SI towards the downstream, which would cause disturbances of the air film cooling (detachment, recirculation) reducing the cooling efficiency of the drilling. Such a narrowing of the fluid passage cross-section of the cooling drilling 3 in the direction SI downstream, causing disturbances of the air film cooling (detachment, recirculation) reducing the cooling efficiency of the drilling, is caused by the manufacturing methods of the state of the art in which the pin 503 of the electroerosion electrode 501 is completely removed from the metering portion 31 to produce the diffusion portion 32.

[0057] Figures 4 and 5 show a second example of a possible shape for the cooling hole 3. [Fig. 4] shows a top view of the shape of the second opening 121 in the second surface 12, the parts of the wall 10 located under the second surface 12 not being shown. [Fig. 5] shows a perspective view of the cooling hole 3, the other parts of the wall 10 not being shown.

[0058] According to an embodiment of the invention, shown by way of example in Figures 4 and 5, the connecting surface 35 comprises a first edge 35a in the shape of a lobe (or curved and concave) and a second edge 35b in the shape of a lobe (or curved and concave), which are located on either side of a median direction S10 of the cooling bore 3 or of a median plane of the cooling bore 3. The median direction S10 of the cooling bore 3 is substantially parallel to the direction S1 going from upstream to downstream and to the first tangent plane P1 and / or to the second tangent plane P2. The median plane of the cooling bore 3 contains the direction S1 and the thickness direction Z. The connecting surface 35 comprises a downstream hollow 35c located between the first edge 35a in the shape of a lobe and the second edge 35b in the shape of a lobe.

[0059] According to an embodiment of the invention, shown by way of example in Figures 4 and 5, the first lobe-shaped edge 35a and the second lobe-shaped edge 35b are symmetrical with respect to the median direction S10 of the cooling bore 3 or to the median plane of the cooling bore 3. The downstream hollow 35c may be located on the median direction S10 of the bore or on the median plane of the cooling bore 3.

[0060] According to an embodiment of the invention, shown by way of example in Figures 4 and 5, the first lobe-shaped edge 35a and the second lobe-shaped edge 35b are flat and in the same plane.

[0061] According to an embodiment of the invention, shown by way of example in Figures 4 and 5, the downstream part 323 of the diffusion surface 320 comprises a first downstream surface 323a in the form of a lobe and a second downstream surface 323b in the form of a lobe, which are located on either side of the median direction S10 of the cooling bore 3 described above or of a median plane of the cooling bore 3 described above. An upstream-facing projection 323c may be located on the downstream portion 323 of the diffusion surface 320 between the first lobe-shaped downstream surface 323a and the second lobe-shaped downstream surface 323b. The projection 323c is connected to the downstream recess 35c.

[0062] According to an embodiment of the invention, shown by way of example in Figures 4 and 5, the first lobe-shaped downstream surface 323a and the second lobe-shaped downstream surface 323b are symmetrical with respect to the median direction S10 of the cooling bore 3 or to the median plane of the cooling bore 3. The projection 323c may be located on the median direction S10 of the bore or on the median plane of the cooling bore 3.

[0063] According to an embodiment of the invention, in Figures 4 and 5, two second drilling portions 42, namely the second drilling portion 42a and the other second drilling portion 42b are produced during the third step E3. This second drilling portion 42a and the other second drilling portion 42b delimit the first downstream surface 323a in the form of a lobe and the downstream surface 323a in the form of a lobe, the first edge 35a in the form of a lobe and the second edge 35b in the form of a lobe. The second drilling portion 42a is located downstream of the first drilling portion 41 and widens beyond the first drilling portion 41 in a first direction Y1 of the other lateral direction of Y. The other second drilling part 42b is located downstream of the first drilling part 41 and widens beyond the first drilling part 41 in a second direction Y2 of the other lateral direction Y, opposite to the first direction Y1.

[0064] The structure shown in Figures 4 and 5 also makes it possible to avoid, in the transition zone 322 of the diffusion surface 320 connecting the first drilling part 41 to the second drilling parts 42a, 42b, a narrowing of the fluid passage cross-section of the cooling drilling 3 in the direction SI towards the downstream, which would cause disturbances in the air film cooling (detachment, recirculation) reducing the cooling efficiency of the drilling.

[0065] The manufacturing method according to the invention also makes it possible to remove a step compared to the manufacturing methods of the prior art in which the pin 503 of the electroerosion electrode 501 is completely removed from the metering portion 31 to produce the diffusion portion 32, which simplifies the production of the cooling bore 3 and thus reduces its cost. The manufacturing method according to the invention is quick to implement and makes it possible to improve the strength of the cooling bore 3. In addition, the manufacturing method according to the invention makes it possible to reduce non-conformities in production.

[0066] An example of an aeronautical turbomachine T, in which the turbomachine component 1 according to the invention can be used, is described below in more detail with reference to [Fig. 1 1].

[0067] As is known, the turbomachine T shown in [Fig. 1 1] is intended to be installed on an aircraft not shown to propel it into the air.

[0068] The gas turbine engine assembly or turbomachine T extends around an axis AX or axial direction AX (or first longitudinal direction AX mentioned below) oriented from upstream to downstream. In [Fig.l 1], the terms "upstream", respectively "downstream" or "front", respectively "rear", or "left" respectively "right" or "axially" are taken along the general direction of the gases which flow in the turbomachine along the axis AX. The direction going from the inside to the outside is the radial direction DR (or third height direction DR mentioned below) starting from the axis AX.

[0069] The turbomachine T is for example a double-spool turbomachine. The turbomachine T comprises a first stage formed by a rotary fan 280 and a gas generator 130, located downstream of the rotary fan 280. Central to the turbomachine, the gas generator 130 comprises, from upstream to downstream in the direction of gas flow, a low-pressure compressor CBP1, a high-pressure compressor CHP1, a combustion chamber 160, a high-pressure turbine THP1 and a low-pressure turbine TBP1, which delimit a primary gas flow FPL

[0070] The rotary fan 280 includes a set of rotary fan blades 2 extending radially outwardly from a rotary fan hub 250. The rotary fan blades 2 are externally surrounded by a fan housing 300.

[0071] The turbomachine T has an upstream intake end 290 located upstream of the fan 280, and a downstream exhaust end 311. The turbomachine T also comprises an inter-stream casing 360 which delimits a primary stream in which circulates the primary flow FP1 which passes downstream of the fan 280 through the low pressure compressor CBP1, the high pressure compressor CHP1, the high pressure turbine THP1 and the low pressure turbine TBP1.

[0072] The inter-vein casing 360 comprises, from upstream to downstream, a casing 361 of the low pressure compressor CBP1, an intermediate casing 260, which is interposed between the low pressure compressor CBP1 and the high pressure compressor CHP1, a casing 362 of the high pressure compressor CHP1, a casing 363 of the high pressure turbine THP1 and a casing 190 of the low pressure turbine TBP1.

[0073] The low pressure compressor CBP1 and the high pressure compressor CHP1 may each comprise one or more stages, each stage being formed by a set of fixed blades (or stator blades) and a set of rotating blades (or rotor blades).

[0074] The fixed blades 101 of the low pressure compressor CBP1 are fixed to the casing 361. The rotary blades 102 of the low pressure compressor CBP1 are fixed to a first rotary transmission shaft 410.

[0075] The fixed blades 103 of the high pressure compressor CHP1 are fixed to the casing 362. The rotary blades 104 of the high pressure compressor CHP1 are fixed to a second rotary transmission shaft 400.

[0076] The high pressure turbine THP1 and the low pressure turbine TBP1 may each comprise one or more stages, each stage being formed by a set of fixed blades (or stator blades) and a set of rotating blades (or rotor blades).

[0077] The fixed blades 105 of the high pressure turbine THP1 are fixed to the casing 363. The rotary blades 106 of the high pressure turbine THP1 are fixed to the second rotary transmission shaft 400.

[0078] The fixed blades 107 of the low pressure turbine TBP1 are fixed to the casing 190. The rotary blades 108 of the low pressure turbine TBP1 are fixed to the first rotary transmission shaft 410.

[0079] The rotating blades 108 of the low-pressure turbine TBP1 drive the rotating blades 102 of the low-pressure compressor CBP1 in rotation about the axis AX under the effect of the thrust of the gases coming from the combustion chamber 160. The rotating blades 106 of the high-pressure turbine THP1 drive the rotating blades 104 of the high-pressure compressor CHP1 in rotation about the axis AX under the effect of the thrust of the gases coming from the combustion chamber 160.

[0080] The rotary fan blades 2 are upstream of the blades 101, 102, 103, 104, 105, 106, 107 and 108 and are of a different shape from these.

[0081] In operation, air flows through the rotary fan 280 and a first portion FP1 (primary flow FP1) of the air flow is routed through the low pressure compressor CBP1 and the high pressure compressor CHP1, in which the air flow is compressed and sent to the combustion chamber 160. The hot combustion products (not shown in the figures) from the combustion chamber 160 are used to drive the turbines THP1 and TBP1 and thus produce the thrust of the turbomachine T. The turbomachine T also comprises a secondary vein 390 which is used to pass a secondary flow FS1 of the air flow discharged from the rotary fan 280 around the inter-vein casing 360. More specifically, the secondary vein 390 extends between an inner wall 201 of a fairing 200 or nacelle 200 and the inter-vein casing 360 surrounding the gas generator 130, the fan casing 300 being the upstream part of this fairing 200 or nacelle 200.340 arms connect the housing. intermediate 260 to the internal wall 201 of the fairing 200 in the secondary vein 390 of the secondary flow FS1.

[0082] The turbomachine component 1 may be, for example, one or more of the blades 101 and / or one or more of the blades 102 and / or one or more of the blades 103 and / or one or more of the blades 104 and / or one or more of the blades 105 and / or one or more of the blades 106 and / or one or more of the blades 107 and / or one or more of the blades 108.

[0083] In particular, the turbomachine component 1 may be, for example, one or more of the rotary blades 106 of the high-pressure turbine THP1.

[0084] [Fig. 12] represents an exemplary embodiment of a rotary blade 106 of the high-pressure turbine THP1. The turbomachine blade 106 comprises a blade 21, a root 22 intended to be housed in a housing of a disc (not shown) of the second rotary transmission shaft 400 and a platform 23 intended to delimit radially inwards the duct 1 IA for the passage of the primary flow FP1, this passage duct 1 IA being delimited outwards by the casing 363 of the high-pressure turbine THP1. During operation of the turbomachine T, the blade 21 is located in the duct 1 IA for the passage of the primary flow FP1 and consequently exposed to the hot gas coming from the combustion chamber 160. The turbomachine T comprises a cooling circuit for conveying fresh air (cooling fluid) into an internal cavity 25 of the blade 106.The blade 106 comprises the cooling holes 3 connecting the internal surface of the blade 21, which is formed by the first surface 11, to the external surface of the blade 21, which is formed by the second surface 12. The first surface 11 partly delimits the internal cavity 25. The second surface 12 is exposed to the primary flow FP1 in the passage duct 1 IA. The cooling holes 3 make it possible to evacuate a portion of the fresh air circulating in the internal cavity 25 of the blade 106 so as to form on the second surface 12 a film of fresh air protecting the blade 21 from the hot combustion gases 10A of the primary flow FP1 in the passage duct 1 IA.

[0085] Of course, the structure described above with reference to [Fig. 12] could also be provided for one or more of the blades 101 and / or one or more of the blades 102 and / or one or more of the blades 103 and / or one or more of the blades 104 and / or one or more of the blades 105 and / or one or more of the blades 107 and / or one or more of the blades 108.

[0086] Of course, the embodiments, features, possibilities and examples described above can be combined with each other or selected independently of each other.

Claims

1. Claims Method for manufacturing a turbomachine component (1) from a part (1a) having a wall (10) having a first surface (11) and a second surface (12) which is opposite the first surface (11), the distance which separates the first surface (11) and the second surface (12) defining a thickness direction (Z) of the wall (10), the method comprising during a first step (El), a movement of an electroerosion electrode (501) having a rectilinear pin (503), which ends with a free end (502) against the second surface (12) in the wall (10), the electrode (501) being inclined at a predetermined angle (a) relative to the thickness direction (Z) to produce in the wall (10) a first drilling part (41), which is cylindrical and passes through a second opening (121) of the second surface (12) to a first opening (111) of the first surface (11), which is inclined at the predetermined angle (a) and which goes in a direction (SI) going from upstream to downstream and from the first surface (11) to the second surface (12), characterized in that the method further comprises the following steps: during a second step (E2), partial withdrawal of the electro-erosion electrode (501) having the spindle (503) inclined at the predetermined angle (a) in the first drilling part (41), to position the free end (502) of the electro-erosion electrode (501) at a first non-zero distance (D1) from the first opening (111) at the predetermined angle (a) and at a second non-zero distance (D2) from the second opening (121) at the predetermined angle (a), during a third step (E3), moving the electroerosion electrode (501) having the spindle (503) inclined at the predetermined angle (a) in the direction (SI) from upstream to downstream, to produce in the wall (10) from the first drilling part (41) a second drilling part (42), the part (la) having the first drilling part (41) and the second drilling part (42) forming the turbomachine component (1) intended to be cooled by a gaseous cooling fluid, comprising the wall (10) and at least one drilling (3) cooling through the wall (10) opening on the one hand to the first surface (11) and, on the other hand, to the second surface (12), the cooling bore (3) being formed by the first bore part (41) and the second bore part (42), the cooling bore (3) being oblique by the predetermined angle (a) in a section plane comprising the thickness direction (Z) and being configured to allow in operation a flow of gaseous fluid (SI) going from upstream to downstream, from the first surface (11) to the second surface (12), the cooling bore (3) comprising a metering portion (31), which opens onto the first surface (11) and which is delimited by a metering surface (310), and a diffusion portion (32), which opens onto the second surface (12) and which is delimited by a diffusion surface (320), the diffusion portion (32) having a passage cross-section,which is larger than the passage cross-section of the metering portion (31), the diffusion surface (320) being connected to the metering surface (310) by a connecting surface (35), which, in the section plane comprising the thickness direction (Z), is inclined relative to a downstream portion (312) of the metering surface (310) and relative to a downstream portion (323) of the diffusion surface (320), so that the connecting surface (35) forms a step at the junction between the downstream portion (312) of the metering surface (310) and the downstream portion (323) of the diffusion surface (320).,

2. Method according to claim 1, characterized in that the first surface (11) is an internal surface of the component (1), at least partly delimiting an internal cavity (25) of the component, and the second surface (12) is an external surface of the component (1).

3. Method according to any one of the preceding claims, characterized in that the diffusion surface (320) has a cylindrical portion whose axis of revolution is inclined according to the predetermined angle (a).

4. Method according to any one of the preceding claims, characterized in that the connecting surface (35) comprises a first lateral lobe (35a) and a second lateral lobe (35b), the lobes being located on either side of a median direction (S 10) of the cooling bore (3), the median direction (S 10) being substantially parallel to a direction (SI) going from upstream to downstream and to a first tangent plane (PI) taken at the intersection of the first surface (11) and the dosing surface (310) and / or at a second tangent plane (P2) taken at the intersection of the second surface (12) and the diffusion surface (320).

5. Method according to claim 4, characterized in that the first side lobe (35a) and the second side lobe (35b) are symmetrical with respect to the median direction (S 10) of the cooling bore (3).

6. Method according to any one of the preceding claims, characterized in that the connecting surface (35) is formed by a blind bore (33) forming part of the diffusion portion (32).

7. A method according to any one of the preceding claims, characterized in that the bonding surface (35) is substantially planar.

8. Method according to any one of the preceding claims, characterized in that the connecting surface (35) is substantially parallel to a first tangent plane (P1) taken at the intersection of the first surface (11) and the dosing surface (310) and / or is substantially parallel to a second tangent plane (P2) taken at the intersection of the second surface (12) and the diffusion surface (320).

9. Method according to any one of the preceding claims, characterized in that the predetermined angle (a) is greater than or equal to 30° and less than or equal to 60° relative to the thickness direction (Z).

10. A method according to any one of the preceding claims, characterized in that the turbomachine component (1) consists of a turbomachine turbine blade (106).

11. Method according to any one of the preceding claims, characterized in that the second drilling part (42) comprises a cylindrical portion, the axis of revolution of this cylindrical portion being parallel to the first drilling part (41) at the predetermined angle (a).

Images