WO2014170616A1 - Procédé de déformation par grenaillage pour l'assemblage de deux pièces de turbomachine - Google Patents
Procédé de déformation par grenaillage pour l'assemblage de deux pièces de turbomachine Download PDFInfo
- Publication number
- WO2014170616A1 WO2014170616A1 PCT/FR2014/050942 FR2014050942W WO2014170616A1 WO 2014170616 A1 WO2014170616 A1 WO 2014170616A1 FR 2014050942 W FR2014050942 W FR 2014050942W WO 2014170616 A1 WO2014170616 A1 WO 2014170616A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- piece
- turbomachine
- shot blasting
- blasting operation
- parts
- Prior art date
Links
Classifications
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/10—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening
-
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the method of prestressing shot blasting in particular is a mechanical treatment intended to improve the mechanical properties of a metal part by surface hardening. It is based on the structural transformation of materials.
- the conventional method consists in putting the metal parts under superficial compression, by the projection of small steel balls, glass or ceramic. This micro-grinding operation creates a compressed zone which is the seat of internal compressive stresses by which the resistance is increased.
- the invention thus has, according to one of its aspects, a method of deformation of at least one turbomachine part by shot blasting for assembling a first turbomachine part with a second turbomachine part, comprising the steps of:
- the deformation of the turbomachine part can thus advantageously allow the assembly of the part with another part.
- the shot blasting process is advantageously used to allow the deformation of at least one turbomachine part.
- the deformation undergone by the part during shot blasting is thus desired and used to allow its assembly.
- the method according to the invention may further comprise one or more of the following characteristics taken separately or in any possible technical combinations.
- the deformation undergone by the part during shot blasting can make it possible to modify its dimensions, such as, for example, height, thickness, diameter.
- the blasting assembly can be used alone to assemble the first and second parts, or even in combination with one or more known assembly solutions according to the prior art, for example by gluing.
- the first and second turbomachine parts can be made of different materials.
- means for protecting said at least one part, in particular the second part can be placed on the surface thereof during the shot blasting operation.
- the protection means may for example prevent a risk of damage to a composite material part.
- One or more tools for blasting operation simulation can for example be used in the method according to the invention to predict the deformation of the workpiece and define the parameters of the blasting operation accordingly.
- the additional holding means may be an adhesive holding means, in particular glue.
- At least one of the first and second parts may comprise, on a portion located at said at least one area undergoing the shot blasting operation, means for reinforcing the assembly of the first part and the second room.
- the invention also relates, according to another of its aspects, a turbomachine, characterized in that it comprises at least one piece deformed by the implementation of the method as defined above.
- the turbomachine according to the invention may comprise any of the previously mentioned characteristics, taken separately or in any technically possible combination with other characteristics.
- FIG. 3 illustrates, in section, the use of an additional adhesive holding means for assembling the two turbomachine parts of FIG. 1,
- FIGS. 4A and 4B illustrate, in section and in part, the use of reinforcing means in the form of a surface state suitable for assembling the two turbine engine parts of FIG. 1
- FIGS. 5A and 5B illustrate, in section, the use of reinforcement means in the form of complementary hooked forms for the assembly of the two turbomachine parts of FIG. 1.
- FIG. 1, and FIGS. 2A, 2B and 2C show an example of two turbomachine parts, intended to be deformed by the implementation of the method according to the invention.
- Figures 3, 4A-4B and 5A-5B, described below, illustrate various solutions for strengthening the mechanical strength of the assembly of the two pieces of turbomachine obtained by shot blasting.
- the method according to the invention is implemented to allow the assembly of a first part 1 of a turbomachine with a second part 2 of a turbomachine.
- FIG. 1 represents, in perspective and in an unassembled manner, the first part 1 and the second part 2.
- the first and second turbomachine parts 1 are, for example, intended to constitute a blade of a turbomachine blade.
- the first part 1 constitutes the metal leading edge of the blade
- the second part 2 constitutes the CMO composite material core of the blade.
- FIGS. 2A, 2B and 2C successively illustrate the assembly steps of the first part 1 and the second part 2, during the implementation of the method according to the invention.
- FIG. 2A two zones A are defined on which shot blasting operations G will be carried out to allow the deformation of at least the leading edge 1, intended to be assembled on the core 2, according to the arrow Fl.
- shot blasting operations G are carried out on the zones A, previously defined on the leading edge 1, in order to allow the assembly of the leading edge 1 on the core 2.
- protection means 3 placed for example at the junctions between the leading edge 1 and the core 2, are used to avoid any risk of damage to the core 2 of composite material.
- the shot blasting operations G consist of the generation of a mechanical pinching force of the leading edge 1 of metallic material on the core 2 of composite material, which is itself induced by the compression of the flanks of the leading edge 1.
- a mechanical pinching force of the leading edge 1 of metallic material on the core 2 of composite material which is itself induced by the compression of the flanks of the leading edge 1.
- the second part 2 may be coated on either side of a layer of adhesive 4 before coming to position the first part 1 thereon, and to perform the shot blasting operation G.
- the presence of such a bond bonded to the interface between the first part 1 and the second part 2 can make it possible to bring the two parts 1 and 2 into contact, and in particular the interface between the metallic material of the first part 1 and the material composite of the second piece 2, with a certain pressure and in a more homogeneous way.
- the following shot peening operation G to ensure a mechanical holding of the two parts 1 and 2 may be a way to improve the strength of the two parts 1 and 2, obtained by the glued connection. More precisely, the shot peening operation G makes it possible to bring the surface of the leading edge 1 back onto the face of the core 2 opposite by inducing reinforcement of the bonding.
- FIGS. 4A-4B and 5A-5B illustrate, in section, the use of reinforcing means 5, 6a, 6b of the assembly of the first 1 and second 2 pieces.
- the reinforcing means correspond to a surface state adapted to the first part 1 .
- the first piece 1 comprises a surface intended to come into contact with the second piece 2, which has a geometric fit to the interface formed with the second piece 2 to enhance the strength of the assembly.
- the surface of the first piece 1 is for example rough, as shown in Figure 4A. Having a surface having a certain roughness may allow a partial depression of the first part 1 in the second part 2 during the shot blasting operation G, as shown in Figure 4B. More particularly, since the metallic material of the leading edge 1 has a hardness greater than that of the composite material of the core 2, the roughness peaks of the matched surface state 5 of the first part 1 become embedded in the surface. 2 during the deformation of the leading edge 1 by shot blasting G, which introduces a hooking effect improving the strength of the assembly.
- the second component 2 may, if necessary, be coated with a coating.
- layer of hitched protection also called “sacrificial”, for example glue or other coating, intended to allow the micro penetration of the roughness peaks of the surface state adapted 5 of the first part 1 and to avoid, or at least to limit, damage to the second piece 2.
- the reinforcing means also correspond to complementary hooked forms 6a and 6b for the assembly of the two parts 1 and 2.
- the hooked forms 6a male and hooked forms 6b female are complementary, so as to allow penetration into each other during the shot blasting operation G, as shown in Figure 5B.
- a "mechanical lock” effect is obtained which makes it possible to further strengthen the assembly obtained by shot blasting G of the first 1 and second 2 pieces.
- leading edge 1 of metallic material can be blasted on the core 2 of composite material by virtue of a complementarity of the surface states of these two parts 1 and 2.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/784,194 US20160032741A1 (en) | 2013-04-18 | 2014-04-17 | Shot peening deformation process for assembling two parts of a turbomachine |
GB1518336.1A GB2527018A (en) | 2013-04-18 | 2014-04-17 | Shot peening deformation process for assembling two parts of a turbomachine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1353534 | 2013-04-18 | ||
FR1353534A FR3004669B1 (fr) | 2013-04-18 | 2013-04-18 | Procede de deformation par grenaillage pour l'assemblage de deux pieces de turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014170616A1 true WO2014170616A1 (fr) | 2014-10-23 |
Family
ID=48613997
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2014/050942 WO2014170616A1 (fr) | 2013-04-18 | 2014-04-17 | Procédé de déformation par grenaillage pour l'assemblage de deux pièces de turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US20160032741A1 (fr) |
FR (1) | FR3004669B1 (fr) |
GB (1) | GB2527018A (fr) |
WO (1) | WO2014170616A1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3041684B1 (fr) * | 2015-09-28 | 2021-12-10 | Snecma | Aube comprenant un bouclier de bord d'attaque et procede de fabrication de l'aube |
CN109551376B (zh) * | 2018-11-21 | 2021-09-10 | 中国航发哈尔滨东安发动机有限公司 | 离心叶轮喷丸强度精准获取方法 |
FR3096399B1 (fr) * | 2019-05-21 | 2021-05-28 | Safran Aircraft Engines | Aube de turbomachine à bord d’attaque métallique intégré et procédé pour l’obtenir |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2007137902A1 (fr) | 2006-05-26 | 2007-12-06 | Siemens Aktiengesellschaft | Dispositif de projection |
FR2908678A1 (fr) | 2007-11-27 | 2008-05-23 | Sonats Soc Des Nouvelles Appli | Procede de grenaillage d'un percage |
WO2008071162A1 (fr) | 2006-12-13 | 2008-06-19 | Mtu Aero Engines Gmbh | Procédé et dispositif pour grenailler la surface d'un élément d'une pièce de turbine à gaz |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4738594A (en) * | 1986-02-05 | 1988-04-19 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Blades for axial fans |
US5165859A (en) * | 1992-06-26 | 1992-11-24 | Hudson Products Corporation | Leading edge protection for fan blade |
US5210946A (en) * | 1992-06-26 | 1993-05-18 | Hudson Products Corporation | Leading edge protection for fan blade |
US6037004A (en) * | 1997-12-19 | 2000-03-14 | United Technologies Corporation | Shield and method for protecting an airfoil surface |
US6607358B2 (en) * | 2002-01-08 | 2003-08-19 | General Electric Company | Multi-component hybrid turbine blade |
FR2863191B1 (fr) * | 2003-12-04 | 2007-04-20 | Snecma Moteurs | Masque de protection pour le traitement de surface d'aubes de turbomachines |
US7217102B2 (en) * | 2005-06-30 | 2007-05-15 | General Electric Campany | Countering laser shock peening induced airfoil twist using shot peening |
US7805839B2 (en) * | 2007-12-31 | 2010-10-05 | Turbine Engine Components Technologies Corporation | Method of manufacturing a turbine fan blade |
CN102639287A (zh) * | 2009-11-30 | 2012-08-15 | 斯奈克玛 | 制造用于涡轮发动机叶片的金属加强件的方法 |
FR2978931B1 (fr) * | 2011-08-10 | 2014-05-09 | Snecma | Procede de realisation d'un renfort de protection du bord d'attaque d'une pale |
-
2013
- 2013-04-18 FR FR1353534A patent/FR3004669B1/fr active Active
-
2014
- 2014-04-17 WO PCT/FR2014/050942 patent/WO2014170616A1/fr active Application Filing
- 2014-04-17 GB GB1518336.1A patent/GB2527018A/en not_active Withdrawn
- 2014-04-17 US US14/784,194 patent/US20160032741A1/en not_active Abandoned
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2007137902A1 (fr) | 2006-05-26 | 2007-12-06 | Siemens Aktiengesellschaft | Dispositif de projection |
WO2008071162A1 (fr) | 2006-12-13 | 2008-06-19 | Mtu Aero Engines Gmbh | Procédé et dispositif pour grenailler la surface d'un élément d'une pièce de turbine à gaz |
FR2908678A1 (fr) | 2007-11-27 | 2008-05-23 | Sonats Soc Des Nouvelles Appli | Procede de grenaillage d'un percage |
Also Published As
Publication number | Publication date |
---|---|
GB2527018A (en) | 2015-12-09 |
FR3004669A1 (fr) | 2014-10-24 |
FR3004669B1 (fr) | 2015-05-15 |
GB201518336D0 (en) | 2015-12-02 |
US20160032741A1 (en) | 2016-02-04 |
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