CA2467846C - Method of manufacturing a hollow blade for a turbine engine - Google Patents
Method of manufacturing a hollow blade for a turbine engine Download PDFInfo
- Publication number
- CA2467846C CA2467846C CA2467846A CA2467846A CA2467846C CA 2467846 C CA2467846 C CA 2467846C CA 2467846 A CA2467846 A CA 2467846A CA 2467846 A CA2467846 A CA 2467846A CA 2467846 C CA2467846 C CA 2467846C
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- CA
- Canada
- Prior art keywords
- preform
- blade
- manufacturing
- unit
- additional element
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 44
- 238000009792 diffusion process Methods 0.000 claims abstract description 21
- 238000000034 method Methods 0.000 claims abstract description 21
- 238000003466 welding Methods 0.000 claims description 10
- 238000001125 extrusion Methods 0.000 claims description 3
- 238000003756 stirring Methods 0.000 claims description 3
- 238000003754 machining Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 5
- 238000000576 coating method Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000003475 lamination Methods 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Forging (AREA)
Abstract
The invention relates to a method of manufacturing a hollow blade for turbine engine comprising a foot and a rotor blade, the method comprising a production stage of a blade preform (14) bearing a rotor blade part and a foot part, this production stage of the blade preform comprising the following operations: - the making of a unit (28) of at least two parts (30, 32) stacked and diffusion bonded together, in such a way that they solely form the rotor blade part of the preform; - the making of an additional element (34) intended to wholly form the foot part of the preform; and - the assembling of the additional element to the unit so as to obtain the blade preform.
Description
METHOD OF MANUFACTURING A HOLLOW BLADE FOR A TURBINE
ENGINE
TECHNICAL FIELD
The invention generally relates to the field of methods of manufacturing blades for turbine engine, such as hollow fan blades, or any other type of rotor or stator blades for turbine engine.
STATE OF THE PRIOR ART
Usually, a hollow fan blade for turbine engine comprises a relatively thick foot used to attach this blade into a rotor disk, this foot being radially extended towards the outside by a thin aerodynamic part, called rotor blade.
From the prior art, it is known a method of manufacturing such a hollow blade, principally based on the use of the diffusion bonding technique, associated with that of superplastic forming.
Indeed, in this method of the prior art, two or three component parts of the blade are firstly defined, then made separately before being stacked and assembled to each other via the diffusion bonding technique, with the purpose of obtaining a preform of the desired blade.
Subsequently, an airfoil profiling of the previously fabricated preform is carried out, then bulging via gas pressure and with superplastic forming of this preform, in order to achieve a blade substantially bearing its finished shape.
As was mentioned above, a production stage of the blade preform requires the making of two external parts,
ENGINE
TECHNICAL FIELD
The invention generally relates to the field of methods of manufacturing blades for turbine engine, such as hollow fan blades, or any other type of rotor or stator blades for turbine engine.
STATE OF THE PRIOR ART
Usually, a hollow fan blade for turbine engine comprises a relatively thick foot used to attach this blade into a rotor disk, this foot being radially extended towards the outside by a thin aerodynamic part, called rotor blade.
From the prior art, it is known a method of manufacturing such a hollow blade, principally based on the use of the diffusion bonding technique, associated with that of superplastic forming.
Indeed, in this method of the prior art, two or three component parts of the blade are firstly defined, then made separately before being stacked and assembled to each other via the diffusion bonding technique, with the purpose of obtaining a preform of the desired blade.
Subsequently, an airfoil profiling of the previously fabricated preform is carried out, then bulging via gas pressure and with superplastic forming of this preform, in order to achieve a blade substantially bearing its finished shape.
As was mentioned above, a production stage of the blade preform requires the making of two external parts,
2 and possibly a central part intended to be interposed between these two external parts, with the purpose of being used as a stringer later on.
The manufacturing of the external parts is typically carried out through the machining of supply elements that necessarily have relatively large initial dimensions, as each of the two machined external parts must have two radially facing sections of significantly different thickness, these sections respectively being used to define the foot part of the blade preform and the rotor blade part of this said preform.
Thus, the manufacturing of the external parts intended to constitute at least partially the blade preform, for example obtained via lamination, generates very high material costs and machining costs, and hence this method of manufacturing the hollow blade is not completely optimised.
To face up to this major inconvenience, it has been proposed to produce the blade preform by means of a single diffusion bonding stage implying a stacking of at least five parts, of which some extend radially along the entire length of the preform, and others only along the foot part of the latter.
However, this method, which is notably disclosed in the documents US-A-4 822 823 and EP-A-1 188 197, has the inconvenience that major difficulties in the implementing of the diffusion bonding technique appear when the unit to be welded has extremely variable thicknesses (foot/rotor blade), and a large number of stacked parts.
The manufacturing of the external parts is typically carried out through the machining of supply elements that necessarily have relatively large initial dimensions, as each of the two machined external parts must have two radially facing sections of significantly different thickness, these sections respectively being used to define the foot part of the blade preform and the rotor blade part of this said preform.
Thus, the manufacturing of the external parts intended to constitute at least partially the blade preform, for example obtained via lamination, generates very high material costs and machining costs, and hence this method of manufacturing the hollow blade is not completely optimised.
To face up to this major inconvenience, it has been proposed to produce the blade preform by means of a single diffusion bonding stage implying a stacking of at least five parts, of which some extend radially along the entire length of the preform, and others only along the foot part of the latter.
However, this method, which is notably disclosed in the documents US-A-4 822 823 and EP-A-1 188 197, has the inconvenience that major difficulties in the implementing of the diffusion bonding technique appear when the unit to be welded has extremely variable thicknesses (foot/rotor blade), and a large number of stacked parts.
3 Furthermore, significant problems are also encountered in ensuring good leak tightness around the foot part of the stacked parts.
OBJECT OF THE INVENTION
The purpose of the invention is therefore to propose a method of manufacturing a hollow blade for turbine engine, resolving at least partially the aforementioned inconveniences associated with the method implemented in the prior art.
More precisely, the purpose of the invention is to present a method of manufacturing a hollow blade whose production stage of the blade preform engenders significantly reduced manufacturing costs compared to those encountered in the prior art.
To accomplish this, the object of the invention is a method of manufacturing hollow blades for turbine engine comprising a foot and a rotor blade, the method comprising a production stage of the blade preform bearing a rotor blade part and a foot part, the production stage of the preform being performed in such a way that it comprises a unit of at least two parts stacked and diffusion bonded together. According to the invention, the production stage of the blade preform comprises the following operations:
- the making of the unit of at least two parts stacked and diffusion bonded together, in such a way that it solely forms the rotor blade part of the preform;
- the making of an additional element intended to wholly form the foot part of the preform; and
OBJECT OF THE INVENTION
The purpose of the invention is therefore to propose a method of manufacturing a hollow blade for turbine engine, resolving at least partially the aforementioned inconveniences associated with the method implemented in the prior art.
More precisely, the purpose of the invention is to present a method of manufacturing a hollow blade whose production stage of the blade preform engenders significantly reduced manufacturing costs compared to those encountered in the prior art.
To accomplish this, the object of the invention is a method of manufacturing hollow blades for turbine engine comprising a foot and a rotor blade, the method comprising a production stage of the blade preform bearing a rotor blade part and a foot part, the production stage of the preform being performed in such a way that it comprises a unit of at least two parts stacked and diffusion bonded together. According to the invention, the production stage of the blade preform comprises the following operations:
- the making of the unit of at least two parts stacked and diffusion bonded together, in such a way that it solely forms the rotor blade part of the preform;
- the making of an additional element intended to wholly form the foot part of the preform; and
4 - the assembling of the additional element onto the unit so as to obtain the blade preform.
Advantageously, in the method of manufacturing according to the invention, the unit of at least two parts stacked and diffusion bonded together is not intended to constitute the entire blade preform, but only the rotor blade part of the latter.
Consequently, the making of this diffusion bonded unit no longer integrates the rather costly production of two external parts each intended to have two sections of significantly different thickness and respectively be used to define the foot part of the rotor part of the blade preform. On the contrary, as this welded unit does not constitute the foot part of the preform, its two external parts can thus be wisely defined so that each of them has a relatively even thickness, thus naturally engendering a significant reduction in the material costs and machining costs.
Furthermore, another advantage of the invention resides in the non-integration of the foot part during the diffusion bonding stage, which makes it possible to avoid being confronted with the implementation difficulties of this welding technique encountered when the unit to be welded has extremely variable thicknesses (foot/rotor blade), and a large number of stacked parts. Indeed, the diffusion bonded unit being envisaged to solely constitute the rotor blade part of the preform, it can consequently be manufactured simply thanks to the stacking of only two or three parts, each having a substantially even thickness.
Furthermore, the non-integration of the foot part during the diffusion bonding stage makes it possible to considerably facilitate the leak tightness between the stacked parts intended to be welded, this leak
Advantageously, in the method of manufacturing according to the invention, the unit of at least two parts stacked and diffusion bonded together is not intended to constitute the entire blade preform, but only the rotor blade part of the latter.
Consequently, the making of this diffusion bonded unit no longer integrates the rather costly production of two external parts each intended to have two sections of significantly different thickness and respectively be used to define the foot part of the rotor part of the blade preform. On the contrary, as this welded unit does not constitute the foot part of the preform, its two external parts can thus be wisely defined so that each of them has a relatively even thickness, thus naturally engendering a significant reduction in the material costs and machining costs.
Furthermore, another advantage of the invention resides in the non-integration of the foot part during the diffusion bonding stage, which makes it possible to avoid being confronted with the implementation difficulties of this welding technique encountered when the unit to be welded has extremely variable thicknesses (foot/rotor blade), and a large number of stacked parts. Indeed, the diffusion bonded unit being envisaged to solely constitute the rotor blade part of the preform, it can consequently be manufactured simply thanks to the stacking of only two or three parts, each having a substantially even thickness.
Furthermore, the non-integration of the foot part during the diffusion bonding stage makes it possible to considerably facilitate the leak tightness between the stacked parts intended to be welded, this leak
5 tightness being necessary for the implementing of the diffusion bonding technique. Indeed, the leak tightness at the foot part of the stacking is known to those skilled in the art as being very difficult to produce, so that not having to care for it constitutes a real advantage.
Moreover, the separate making of the additional element presents the possibility of carrying out all sorts of intermediary machining operations on this element, before it is assembled onto the diffusion bonded unit obtained at the same time.
Moreover, the additional element not being intended to enter into the constitution of the rotor blade part of the blade preform but solely to wholly form the foot part of the said preform, it is obvious that the manufacturing costs can also be minimised, notably due to their minor radial length.
The invention therefore envisages the making of the blade preform using a plurality of previously made parts prior to being assembled, notably via diffusion bonding for some of them, none of these parts extending along the entire radial length of the preform, which thus makes it possible to easily overcome the inconveniences directly linked to the extensive variation of thickness of the blade preform along its length.
Moreover, the separate making of the additional element presents the possibility of carrying out all sorts of intermediary machining operations on this element, before it is assembled onto the diffusion bonded unit obtained at the same time.
Moreover, the additional element not being intended to enter into the constitution of the rotor blade part of the blade preform but solely to wholly form the foot part of the said preform, it is obvious that the manufacturing costs can also be minimised, notably due to their minor radial length.
The invention therefore envisages the making of the blade preform using a plurality of previously made parts prior to being assembled, notably via diffusion bonding for some of them, none of these parts extending along the entire radial length of the preform, which thus makes it possible to easily overcome the inconveniences directly linked to the extensive variation of thickness of the blade preform along its length.
6 Preferably, the operation of assembling each additional element to the unit is implemented using a technique taken from among the group constituted of linear friction welding and of friction stir welding, these techniques being preferred in that they are relatively easy to implement, reliable, inexpensive and barely destructive metallurgically speaking.
Preferably, the manufacturing stage of the blade preform is followed by the following stages:
- airfoil profiling of the preform; and - bulging via gas pressure and superplastic forming of the airfoil profiling preform.
It can be envisaged that the additional element intended to wholly form the foot part of the preform is made via extrusion, which constitutes a particularly beneficial advantage in terms of manufacturing costs.
Indeed, this inexpensive technique to be implemented, consists, from a material billet and through an appropriate die, in making a profile of the additional element bearing the desired geometry.
Other advantages and characteristics of the invention will appear in the detailed non-restrictive description below.
BRIEF DESCRIPTION OF THE DRAWINGS
This description will be made in relation to the annexed drawings among which;
- figure 1 represents a perspective view of a standard hollow blade far turbine engine;
- figure 2 represents a diagrammatic perspective view of a blade preform obtained during the
Preferably, the manufacturing stage of the blade preform is followed by the following stages:
- airfoil profiling of the preform; and - bulging via gas pressure and superplastic forming of the airfoil profiling preform.
It can be envisaged that the additional element intended to wholly form the foot part of the preform is made via extrusion, which constitutes a particularly beneficial advantage in terms of manufacturing costs.
Indeed, this inexpensive technique to be implemented, consists, from a material billet and through an appropriate die, in making a profile of the additional element bearing the desired geometry.
Other advantages and characteristics of the invention will appear in the detailed non-restrictive description below.
BRIEF DESCRIPTION OF THE DRAWINGS
This description will be made in relation to the annexed drawings among which;
- figure 1 represents a perspective view of a standard hollow blade far turbine engine;
- figure 2 represents a diagrammatic perspective view of a blade preform obtained during the
7 implementing of the manufacturing stage of the preform of the method of manufacturing according to the invention; and - figures 3a to 3d diagrammatically illustrate the embodiment stages of the method of manufacturing according to the invention.
DETAILED PRESENTATION OF THE PREFERRED EMBODIMENTS
In reference to figure 1, we can notice a standard hollow blade 1 for turbine engine (not represented), for example made of titanium or one of its alloys.
This hollow blade 1, of fan rotor blade type with large chord, comprises a foot 2 extended by a rotor blade 4 in a radial direction.
The rotor blade 4, intended to be placed in the circulation path of an airflow of the turbine engine, has two external surfaces 6 and 8, respectively called upper surface 6 and lower surface 8, connected by a leading edge 10 and a trailing edge 12.
Figure 2 represents a blade preform 16, such as is intended to be obtained during a manufacturing stage of the blade preform of the manufacturing method according to the invention.
This preform 14 comprises a foot part 16 of variable and large thickness, which is extended in a radial direction by a rotor blade part 18. As can be seen in figure 2, the foot part 16 has an internal radial section 20 of a high average thickness E, this section 20 being radially extended externally by an external radial section 22 of an average thickness a inferior to the average thickness E. For information
DETAILED PRESENTATION OF THE PREFERRED EMBODIMENTS
In reference to figure 1, we can notice a standard hollow blade 1 for turbine engine (not represented), for example made of titanium or one of its alloys.
This hollow blade 1, of fan rotor blade type with large chord, comprises a foot 2 extended by a rotor blade 4 in a radial direction.
The rotor blade 4, intended to be placed in the circulation path of an airflow of the turbine engine, has two external surfaces 6 and 8, respectively called upper surface 6 and lower surface 8, connected by a leading edge 10 and a trailing edge 12.
Figure 2 represents a blade preform 16, such as is intended to be obtained during a manufacturing stage of the blade preform of the manufacturing method according to the invention.
This preform 14 comprises a foot part 16 of variable and large thickness, which is extended in a radial direction by a rotor blade part 18. As can be seen in figure 2, the foot part 16 has an internal radial section 20 of a high average thickness E, this section 20 being radially extended externally by an external radial section 22 of an average thickness a inferior to the average thickness E. For information
8 purposes it is noted that the internal radial section 20 is later intended to ensure the fixing of the blade in the rotor disk of the turbine engine, notably thanks to two projection parts 23a and 23b positioned on either side of a central part 23c slotted into the extension of the external radial section 22 of the foot part 16.
Furthermore, the rotor blade part 18 of the preform 14 has a radially internal end 24 of thickness e' substantially equal to the average thickness e, and a radially external end 26 of thickness a " inferior to the thickness e'. However, the rotor blade part 18 of the preform 14 has a substantially even thickness.
Furthermore, it is indicated that there is not clear demarcation between the radially internal end 24 of the rotor blade part 18 and the external radial section 22 of the foot part 16 of the preform 14, as these elements are substantially aligned. Nevertheless, a fictitious junction plan P diagrammatically represented in figure 2 shows the commonly accepted theoretical separation between the foot part 16 and the rotor blade part 18 of the preform 14.
In a preferred embodiment of the method of manufacturing according to the invention, a manufacturing stage of the blade preform 14 is carried out in the aforementioned manner, making reference to figures 3a to 3c.
First of all a unit 28 is made of at least two parts 30 and 32 stacked and diffusion bonded together, the only two parts 30 and 32 visible in figure 3a respectively constituting the upper and lower external
Furthermore, the rotor blade part 18 of the preform 14 has a radially internal end 24 of thickness e' substantially equal to the average thickness e, and a radially external end 26 of thickness a " inferior to the thickness e'. However, the rotor blade part 18 of the preform 14 has a substantially even thickness.
Furthermore, it is indicated that there is not clear demarcation between the radially internal end 24 of the rotor blade part 18 and the external radial section 22 of the foot part 16 of the preform 14, as these elements are substantially aligned. Nevertheless, a fictitious junction plan P diagrammatically represented in figure 2 shows the commonly accepted theoretical separation between the foot part 16 and the rotor blade part 18 of the preform 14.
In a preferred embodiment of the method of manufacturing according to the invention, a manufacturing stage of the blade preform 14 is carried out in the aforementioned manner, making reference to figures 3a to 3c.
First of all a unit 28 is made of at least two parts 30 and 32 stacked and diffusion bonded together, the only two parts 30 and 32 visible in figure 3a respectively constituting the upper and lower external
9 parts of the unit 28. In this regard, it is indicated that a third part (not represented) can also be inserted between the external parts 30 and 32, so as to constitute a stinger later on. Indeed, the unit 28, being intended to solely and wholly form the rotor blade part 18 of the preform 14, can therefore be classically made using two identical external parts with grooved internal surfaces, or even with three parts of which the two identical external parts have substantially smooth internal surfaces in contact with the third intermediary part.
In this preferred embodiment of the invention, the unit 28 solely forming the rotor blade part 18 of the preform 14 has a substantially even thickness, the same as the two identical external parts 30 and 32 constituting this unit 28. Thus, the technique to obtain the parts 30 and 32 via lamination is therefore particularly appropriate, and completely optimised in terms of material costs and machining costs, as the supply elements necessary for the manufacturing of the parts 30 and 32 can easily have dimensions similar to the final dimensions that these said parts 30 and 32 must have.
In the case when the unit 28 is solely constituted of two identical external parts 30 and 32, once these have been made as described above, they are then diffusion bonded together, in a similar manner to that encountered in the prior art in order to carry out the assembling of the different component parts of the preform. In this respect and in a continuous manner, it is noted that the diffusion bonding operation is preceded by a depositing operation of fuel rod coating according to a set pattern, the coatings being applied to the internal surfaces 30a and 32a in contact with the external parts 30 and 32.
5 At the same time as the manufacturing of the hollow unit 28 solely and wholly forming the rotor blade part 18 of the preform 14, a single additional element 34 is made, intended to solely and wholly form the foot part 16 of the said preform 14. Thus, it is
In this preferred embodiment of the invention, the unit 28 solely forming the rotor blade part 18 of the preform 14 has a substantially even thickness, the same as the two identical external parts 30 and 32 constituting this unit 28. Thus, the technique to obtain the parts 30 and 32 via lamination is therefore particularly appropriate, and completely optimised in terms of material costs and machining costs, as the supply elements necessary for the manufacturing of the parts 30 and 32 can easily have dimensions similar to the final dimensions that these said parts 30 and 32 must have.
In the case when the unit 28 is solely constituted of two identical external parts 30 and 32, once these have been made as described above, they are then diffusion bonded together, in a similar manner to that encountered in the prior art in order to carry out the assembling of the different component parts of the preform. In this respect and in a continuous manner, it is noted that the diffusion bonding operation is preceded by a depositing operation of fuel rod coating according to a set pattern, the coatings being applied to the internal surfaces 30a and 32a in contact with the external parts 30 and 32.
5 At the same time as the manufacturing of the hollow unit 28 solely and wholly forming the rotor blade part 18 of the preform 14, a single additional element 34 is made, intended to solely and wholly form the foot part 16 of the said preform 14. Thus, it is
10 naturally specified that the unit 28 and the additional element 34 each have a respective geometry substantially identical to the geometry of the rotor blade part 18 and of the foot part 16 of the preform 14 represented in figure 2.
As is shown in figure 3b, the additional element 34 therefore comprises a part 36 of considerable thickness similar to the internal radial section 20 represented in figure 2, as well as a part 38 of inferior thickness similar to the external radial section 22 represented in the said figure 2. The element 34 can consequently be easily made via extrusion, this proven low cost technique consisting, from a material billet and through an appropriate die, in making a profile of the additional element 34 bearing the desired geometry. In this way, with such a technique, it is possible to manufacture the additional elements 34 one after the other, via single stripping.
Once the unit 28 and the additional element 34 have been simultaneously made, preferably in a titanium alloy, they are then assembled in such a way so as to
As is shown in figure 3b, the additional element 34 therefore comprises a part 36 of considerable thickness similar to the internal radial section 20 represented in figure 2, as well as a part 38 of inferior thickness similar to the external radial section 22 represented in the said figure 2. The element 34 can consequently be easily made via extrusion, this proven low cost technique consisting, from a material billet and through an appropriate die, in making a profile of the additional element 34 bearing the desired geometry. In this way, with such a technique, it is possible to manufacture the additional elements 34 one after the other, via single stripping.
Once the unit 28 and the additional element 34 have been simultaneously made, preferably in a titanium alloy, they are then assembled in such a way so as to
11 substantially obtain the geometry of the preform 14, as illustrated in figure 3c.
This assembling can thus be performed via welding, by putting an internal radial surface 40 of the unit 28 into contact with an external radial surface 42 of the additional element 34. These surfaces 40 and 42 are substantially flat and jointly define a flat contact zone 44, approximately placed in a location identical to that of the fictitious junction plane P represented in figure 2, in comparison to the foot part 16 and rotor blade part 18 of the preform 14.
By way of illustration, the assembling operation of the additional element 34 to the unit 28 is preferably done via linear friction welding, or by friction stir welding. These known welding techniques advantageously allow the welded zone to keep the metallurgical characteristics compatible with the diffusion bonding and superplastic forming techniques, and ensure mechanical properties in compliance with the specifications of the preform.
Of course, this welding operation is followed by a machining operation of geometric reconditioning of the welded zone.
Following the manufacturing stage of the blade preform 14 which has just been described, standard stages are then carried out first of all aiming at airfoil profiling the preform 14, so that it has a substantially twisted shape as illustrated in figure 3d.
Then, still in a continuous manner, bulging via gas pressure and superplastic forming stage makes it possible to obtain the blade 1 such as represented in
This assembling can thus be performed via welding, by putting an internal radial surface 40 of the unit 28 into contact with an external radial surface 42 of the additional element 34. These surfaces 40 and 42 are substantially flat and jointly define a flat contact zone 44, approximately placed in a location identical to that of the fictitious junction plane P represented in figure 2, in comparison to the foot part 16 and rotor blade part 18 of the preform 14.
By way of illustration, the assembling operation of the additional element 34 to the unit 28 is preferably done via linear friction welding, or by friction stir welding. These known welding techniques advantageously allow the welded zone to keep the metallurgical characteristics compatible with the diffusion bonding and superplastic forming techniques, and ensure mechanical properties in compliance with the specifications of the preform.
Of course, this welding operation is followed by a machining operation of geometric reconditioning of the welded zone.
Following the manufacturing stage of the blade preform 14 which has just been described, standard stages are then carried out first of all aiming at airfoil profiling the preform 14, so that it has a substantially twisted shape as illustrated in figure 3d.
Then, still in a continuous manner, bulging via gas pressure and superplastic forming stage makes it possible to obtain the blade 1 such as represented in
12 figure 1, this stage being generally followed by a final machining intended to strictly give the blade 1 the desired airfoil profile.
Of course, various modifications can be introduced by those skilled in the art into the method of manufacturing the hollow blade 1 which has just been described, solely by way of non-restrictive illustration.
Of course, various modifications can be introduced by those skilled in the art into the method of manufacturing the hollow blade 1 which has just been described, solely by way of non-restrictive illustration.
Claims (4)
1. Method of manufacturing a hollow blade (1) for turbine engine comprising a foot (2) and a rotor blade (4), said method comprising a production stage of the blade preform (14) bearing a rotor blade part (18) and a foot part (16), the production stage of the preform (14) being performed in such a way that it comprises a unit (28) of at least two parts (30, 32) stacked and diffusion bonded together, characterised in that the production stage of said blade preform (14) comprises the following operations:
- the making of said unit (28) of at least two parts (30, 32) stacked and diffusion bonded together, in such a way that they solely form said rotor blade part (18) of the preform (14);
- the making of an additional element (34) intended to wholly form said foot part (16) of the preform (14); and - the assembling of the additional element (34) to the unit (28) so as to obtain said blade preform (14).
- the making of said unit (28) of at least two parts (30, 32) stacked and diffusion bonded together, in such a way that they solely form said rotor blade part (18) of the preform (14);
- the making of an additional element (34) intended to wholly form said foot part (16) of the preform (14); and - the assembling of the additional element (34) to the unit (28) so as to obtain said blade preform (14).
2. Manufacturing method set forth in claim 1, characterised in that the assembling operation of the additional element (34) to said unit (28) is implemented using a technique taken from among the group constituted of linear friction welding and of friction stir welding.
3. Manufacturing method set forth in claim 1 or claim 2, characterised in that the manufacturing stage of the blade preform (14) is followed by the following stages:
- airfoil profiling of said preform (14); and - bulging via gas pressure and superplastic forming of said airfoil profiling preform (14).
- airfoil profiling of said preform (14); and - bulging via gas pressure and superplastic forming of said airfoil profiling preform (14).
4. Manufacturing method set forth in any one of claims 1 to 3, characterised in that the additional element (34) intended to wholly form said foot part (16) of the preform (14) is made via extrusion.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0350185A FR2855440B1 (en) | 2003-05-27 | 2003-05-27 | METHOD FOR MANUFACTURING A HOLLOW DAWN FOR TURBOMACHINE |
FR0350185 | 2003-05-27 |
Publications (2)
Publication Number | Publication Date |
---|---|
CA2467846A1 CA2467846A1 (en) | 2004-11-27 |
CA2467846C true CA2467846C (en) | 2011-07-19 |
Family
ID=33104533
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CA2467846A Expired - Lifetime CA2467846C (en) | 2003-05-27 | 2004-05-19 | Method of manufacturing a hollow blade for a turbine engine |
Country Status (8)
Country | Link |
---|---|
EP (1) | EP1481755B1 (en) |
JP (1) | JP4130423B2 (en) |
CA (1) | CA2467846C (en) |
DE (1) | DE602004020422D1 (en) |
ES (1) | ES2323461T3 (en) |
FR (1) | FR2855440B1 (en) |
RU (1) | RU2338886C2 (en) |
UA (1) | UA83793C2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107530909A (en) * | 2015-04-29 | 2018-01-02 | 赛峰航空器发动机 | It is equipped with the blade of the platform including supporting leg |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8016561B2 (en) * | 2006-07-11 | 2011-09-13 | General Electric Company | Gas turbine engine fan assembly and method for assembling to same |
JP4757750B2 (en) * | 2006-09-11 | 2011-08-24 | パナソニック株式会社 | Imaging device |
CN102037247B (en) * | 2008-03-28 | 2015-06-24 | 株式会社Ihi | Blade of a gas turbine engine for an airplane, and a method for manufacturing the same |
FR2953430B1 (en) * | 2009-12-03 | 2012-03-02 | Snecma | PROCESS FOR MAKING A TURBOMACHINE METAL TURBINE REINFORCEMENT |
US8905707B2 (en) * | 2010-12-21 | 2014-12-09 | Hamilton Sundstrand Corporation | Bearing cooling control in an air cycle machine |
CN105736462B (en) * | 2014-12-12 | 2018-03-06 | 中国航发商用航空发动机有限责任公司 | hollow blade and aero-engine |
FR3063663B1 (en) * | 2017-03-13 | 2021-02-26 | Mecachrome France | PROCESS FOR MANUFACTURING COMPLEX SHAPED METAL ALLOY PARTS |
CN114700599B (en) * | 2022-05-18 | 2023-02-28 | 中国航空制造技术研究院 | Blade based on discharge plasma diffusion welding |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CH238023A (en) * | 1943-07-31 | 1945-06-15 | Sulzer Ag | Turbomachine blades and processes for their manufacture |
FR970578A (en) * | 1948-08-19 | 1951-01-05 | Bohler & Cie Ag Geb | Hollow blades for turbines, in particular for gas turbines, and method for their manufacture |
US2767460A (en) * | 1950-02-08 | 1956-10-23 | Robbins Engineering Company | Turbine blade and method of making same |
GB789659A (en) * | 1956-08-31 | 1958-01-22 | Gen Motors Corp | Improvements relating to the manufacture of metal blades having curved surfaces |
US3982854A (en) * | 1971-12-20 | 1976-09-28 | General Electric Company | Friction welded metallic turbomachinery blade element |
US4882823A (en) * | 1988-01-27 | 1989-11-28 | Ontario Technologies Corp. | Superplastic forming diffusion bonding process |
US5469618A (en) * | 1993-12-06 | 1995-11-28 | General Electric Company | Method for manufacturing hollow airfoils (two-piece concept) |
GB0022531D0 (en) * | 2000-09-14 | 2000-11-01 | Rolls Royce Plc | A method of manufacturing an article by diffusion bonding |
US6537682B2 (en) * | 2001-03-27 | 2003-03-25 | The Boeing Company | Application of friction stir welding to superplastically formed structural assemblies |
-
2003
- 2003-05-27 FR FR0350185A patent/FR2855440B1/en not_active Expired - Fee Related
-
2004
- 2004-05-19 JP JP2004148939A patent/JP4130423B2/en not_active Expired - Lifetime
- 2004-05-19 CA CA2467846A patent/CA2467846C/en not_active Expired - Lifetime
- 2004-05-25 DE DE200460020422 patent/DE602004020422D1/en not_active Expired - Lifetime
- 2004-05-25 EP EP20040102296 patent/EP1481755B1/en not_active Expired - Lifetime
- 2004-05-25 ES ES04102296T patent/ES2323461T3/en not_active Expired - Lifetime
- 2004-05-26 RU RU2004116118/06A patent/RU2338886C2/en active
- 2004-05-27 UA UA20040504057A patent/UA83793C2/en unknown
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107530909A (en) * | 2015-04-29 | 2018-01-02 | 赛峰航空器发动机 | It is equipped with the blade of the platform including supporting leg |
CN107530909B (en) * | 2015-04-29 | 2020-08-21 | 赛峰航空器发动机 | Blade equipped with a platform comprising a leg |
Also Published As
Publication number | Publication date |
---|---|
CA2467846A1 (en) | 2004-11-27 |
JP2004353666A (en) | 2004-12-16 |
EP1481755B1 (en) | 2009-04-08 |
RU2004116118A (en) | 2006-01-10 |
ES2323461T3 (en) | 2009-07-16 |
FR2855440A1 (en) | 2004-12-03 |
FR2855440B1 (en) | 2006-07-14 |
EP1481755A1 (en) | 2004-12-01 |
UA83793C2 (en) | 2008-08-26 |
JP4130423B2 (en) | 2008-08-06 |
RU2338886C2 (en) | 2008-11-20 |
DE602004020422D1 (en) | 2009-05-20 |
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