EP2099585B1 - Dispositif et procédé pour grenailler la surface d'une pièce de turbine à gaz - Google Patents

Dispositif et procédé pour grenailler la surface d'une pièce de turbine à gaz Download PDF

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Publication number
EP2099585B1
EP2099585B1 EP07846396A EP07846396A EP2099585B1 EP 2099585 B1 EP2099585 B1 EP 2099585B1 EP 07846396 A EP07846396 A EP 07846396A EP 07846396 A EP07846396 A EP 07846396A EP 2099585 B1 EP2099585 B1 EP 2099585B1
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EP
European Patent Office
Prior art keywords
component
peening
surface area
partial surfaces
blasting
Prior art date
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Active
Application number
EP07846396A
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German (de)
English (en)
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EP2099585A1 (fr
Inventor
Erwin Bayer
Max Niegl
Holger Polanetzki
Thomas Peschke
Thomas Dautl
Philipp THÜMMLER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
Priority date (The priority date 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 date listed.)
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Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2099585A1 publication Critical patent/EP2099585A1/fr
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Publication of EP2099585B1 publication Critical patent/EP2099585B1/fr
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Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C5/00—Devices or accessories for generating abrasive blasts
    • B24C5/005—Vibratory devices, e.g. for generating abrasive blasts by ultrasonic vibrations
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/47—Burnishing
    • Y10T29/479—Burnishing by shot peening or blasting

Definitions

  • the invention relates to a device and a method for surface blasting, in particular for ultrasonic shot peening, a component of a gas turbine of the type specified in the preambles of claims 1 and 11 respectively.
  • FR 2 815 280 as known, wherein the rotor blades of a rotor designed as a blisk can be shot peened to improve the fatigue strength.
  • the device comprises a holding device, with which the rotor is rotatably mounted about its axis of rotation. By rotating the rotor whose rotor blades are passed through a blasting chamber, on the underside of a vibration device in the form of an ultrasonic sonotrode with an at least approximately horizontally extending, the blasting material acts on or accelerating surface is arranged.
  • the blasting chamber is thereby bounded both axially - ie in the region of the broad sides of the rotor - as well as radially - ie in the region of the rotor blades - the blisk by corresponding chamber walls. Since, in particular, the chamber walls of the blasting chamber, which are arranged radially to the rotor, are incapable of holding all the balls within the central blasting chamber, depending on the position of the respective rotor blades, they are each preceded or arranged in the radial direction of the rotor by two further chambers. Within these further chambers, balls passing over from the central beam chamber equipped with the sonotrode are collected and returned via corresponding channels.
  • Object of the present invention is therefore to provide a device and a method of the type mentioned, with which the surface area of the component to be machined can be blasted and solidified extremely uniform.
  • the surface of the vibration device divided into at least two adjacent sub-surfaces, each comprising an overlap part, by means of which a part of the machined Surface region of the component can be processed both by acted upon by one and the other sub-surface blasting.
  • the method according to the invention it is provided in this case to process the corresponding part of the surface area of the component to be machined one behind the other by blasting material acted on by the respective overlapping parts.
  • the invention is initially provided, instead of providing one oscillating surface, at least two adjacent oscillating sub-surfaces, by means of which it is possible to make a more individual adaptation to the respective surface sub-regions of the component.
  • Such an adaptation can be, for example, that the two surfaces are arranged at different angles or act on a different or a different amount of blasting material.
  • individual partial areas of the entire surface area of the component to be radiated can be blasted more individually in order to achieve a desired and as homogeneous as possible solidification.
  • each of the sub-surfaces has an overlap part with which respective blasting material can be accelerated in the direction of this part of the surface area to be processed.
  • it is achieved by the two overlapping parts that even in the intermediate space between the two sub-surfaces a homogeneous and good consolidation of the part of the machinable surface area of the component lying at this point is possible.
  • the two adjacent sub-surfaces may lie in a common plane. This is possible in particular if the surface area of the component to be radiated has a lower complexity. If the two sub-surfaces lie in a common plane, then it is also conceivable that these are assigned to a common vibration device.
  • a surface area of the component is to be blasted of greater complexity, it has proved to be particularly advantageous in a further embodiment of the invention if the two sub-surfaces are arranged at an angle to one another, so that the two sub-surfaces are optimally aligned with the respective part to be radiated can be adapted to be processed surface area.
  • the two adjacent sub-surfaces are each assigned a separate blasting chamber, so that there is a division into at least two sub-chambers, in which there is always a constant amount of blasting material and thereby a uniform blasting result can be realized.
  • a transition-free blasting between the two sub-surfaces which are acted upon by the different vibration devices.
  • a synchronous double-sided blasting of thin-walled components is possible by means of the two partial surface areas arranged within the respective blast chambers, without it being possible for an unirradiated or insufficient blasted area to occur in the boundary region of the two chambers.
  • the synchronous blasting of the thin-walled components in particular ensures that they are not unintentionally deformed.
  • the separation between the two sub-surfaces is particularly easily realized by a partition, which may be formed in cross-section, for example, S-shaped.
  • a partition which may be formed in cross-section, for example, S-shaped.
  • the partition wall it would also be conceivable to form the partition wall as a flat wall, which then however has to run obliquely so that the blasting material acted upon by the two overlapping areas can each come to that part of the surface area of the component to be machined which lies between the two sub-surfaces.
  • chamber walls of the blasting chamber are partially formed by slider walls.
  • Such slide walls have the particular advantage that they can be moved to the component so after positioning of the component within the device that no blasting material can escape from the blasting chamber.
  • the device according to the invention can be used in particular for surface blasting of rotors designed as blisk, since such blisks often have a relatively complex surface geometry. Accordingly, it is possible with the device according to the invention to solidify the complex surface geometry extremely homogeneous.
  • the rotor is rotatable about its axis of rotation, whereby the part of the surface region of the rotor to be machined in a row can be acted upon by both the one and the other part surface accelerated blasting material.
  • the advantages of the device according to the invention are also to be regarded as advantages of the method according to the invention. It would also be conceivable in the method according to the invention that the at least two sub-surfaces are aligned relative to the surface area of the component or the rotor to be radiated.
  • FIG. 1 is a schematic perspective view of a rotatable rotor of a gas turbine in the form of a blisk 10 schematically visible.
  • Fig. 2 which shows the blisk 10 in a schematic sectional view, the basic individual areas of which are more clearly recognizable.
  • a blisk disk 12 can be seen, on whose outer peripheral side a multiplicity of rotor blades 14 are arranged.
  • the blisk disk 12 is essentially an in Fig. 2 line-shaped, outer peripheral side sheet 16 visible, radially inwardly or in the drawing down a Unterblattform Scheme 18 connects.
  • the lower sheet-forming region 18 merges radially inwards into a disk neck 20, which connects the lower sheet-forming region to a disk body 22.
  • the radially inner end of the disk body 22 is formed by a hub 24, which is a counterweight to the rotor blades 14.
  • From the disk body 22 is on the right in the drawing page of the blisk disk 12 from a wing 26 which comprises a web 28 and a substantially U-shaped portion 30.
  • the blisk 10 is designed to be rotatable or rotationally symmetrical about a rotation axis R overall.
  • FIG. 1 An apparatus for shot peening a lower portion of the blisk disk 12 is shown in FIG Fig. 1 a holding device 32 by two symbolically indicated bearing blocks 34, via which the blisk 10 is rotatably supported about its axis of rotation R or stored.
  • a blasting chamber arrangement 36 indicated by dashed lines, which in conjunction with Fig. 2 becomes more apparent.
  • the blasting chamber arrangement 36 comprises two methods which will be described in more detail below separate jet chambers 38, 40, which in the present case in each case one of the respective blasting material acting on part surface 42, 44 of a respective vibration device 46, 48 is assigned.
  • the vibration devices 46, 48 are designed as ultrasonic sonotrodes with which a blasting material introduced within the respective blasting chamber 38, 40 can be accelerated, for example in the form of spheres. Accordingly, in the present case, a radially inner surface area of the blisk disk 12 can be shot peened, which is located in - Fig. 2 viewed from the left side of the disk body 22 to the U-shaped portion 30 of the wing 26 extends. This surface area can be machined or solidified around the blisk disk 12 by rotating the blisk 10 mounted on the holding device 32 about its axis of rotation R. As a result, the blisk 10 is positioned or positioned relative to the oscillating sub-surfaces 42, 44 of the respective vibration device 46, 48 by means of the holding device 32.
  • each outer side radial chamber walls 50, 52 and a further explained in more detail central partition 54 can be seen.
  • 40 chamber walls are also provided.
  • the chamber walls 50, 52 can be designed to be flexible or provided with seals, not shown, so that no blasting material between these and the blisk disk 12 can escape. However, at least the chamber walls 50, 52 are brought so close to the blisk disk 12, that at most results in a gap which is significantly smaller than the diameter of the blasting material used.
  • the part 64 of the surface area comes within both a blasting chamber 38 and the other blasting chamber 40, in which the associated blasting material is accelerated via the respective sub-surface 42, 44.
  • the direction of rotation of the blisk 10 is shown by the arrow 65.
  • the portion 64 of the surface area of the blisk disk 12 first passes through the blasting chamber 38 and then the blasting chamber 40, so that the part 64 is successively acted upon by blasting material accelerated by one and the other sub-surface 42, 44.
  • the rotational movement of the component 10 it would also be conceivable, in particular for non-rotationally symmetrical components, to move it in a linear movement relative to the partial surface 42, 44.
  • the arrangement of the two overlapping parts 58 makes it possible, on the one hand, to use separate jet chambers 38, 40, for example, to arrange the partial surfaces 42, 44 at an angle to one another or to introduce an adapted quantity of abrasive material or to exert a corresponding jet intensity on the partial surface to be machined.
  • the partition wall 54 is S-shaped in the present embodiment. However, it would rather also be conceivable to use a flat partition wall 54 which extends obliquely between the two radial end faces 56.
  • the chamber walls on the front side 56 partially by slide walls 66, 68 formed, which are displaceable in the direction of the arrows 67, 69.
  • slide walls 66, 68 could also be used to separate the two blasting chambers 38, 40 in the region of the partition wall 54 closely from one another.
  • both sub-surfaces 42, 44 lie in a common plane. As a result, it is conceivable to operate both surfaces 42, 44 also by means of a common vibration device 46 or 48.
  • FIG. 4 a two-stage blisk 10, which thus comprises two blisk disks 12, which is associated with an outer peripheral side circumferential arrangement of associated rotary blades 14.
  • the blisk 10 terminates on a radially encircling wing 70 and on the other side on a radially encircling flange 72.
  • three blasting chambers 74, 76, 78 are provided, each of the blasting chambers 74 , 76, 78 a partial surface 80, 82, 84 having vibration means 86, 88, 90 is provided.
  • the partial surface 80 is arranged at an angle or V-shaped relative to the two other partial surfaces 82, 84.
  • the two sub-surfaces 82, 84 are arranged in a plane.
  • the two outer blast chambers 74, 78 comprise outer chamber walls 92, 94, through which the blast chambers 74, 78 are closed relative to the flange 72 and the wing 70, respectively.
  • the parts 108, 110 are indicated by the lines 112 in FIG Fig. 5 indicated by dashed lines.
  • the middle partial surface 82 has two overlapping parts 102, 104, which are arranged with the respective corresponding overlapping parts 100, 106 in the region of the respective part 108, 110 of the blisk disc 12 to be processed.
  • individually adjustable conditions prevail within the three jet chambers 74, 76, 78, so that the blisk disk 12 can be surface-blasted extremely in line with needs and in a homogeneous manner.
  • the respective partition walls 96, 98 are again S-shaped formed stepped, so that in the course of the rotation of the blisk 10 shown by the arrow 114, the parts 108, 110 of the respective hub 24 both above the respective one and the other overlap part 100, 102, 104, 106 are arranged and accordingly with blasting the different jet chambers 74, 76, 78 are acted upon.
  • the portion 108, 110 of the surface area of the blisk disk 12 passes through in the direction of the blisk upon rotation Arrow 114, first, the blasting chamber 82 and then the blasting chamber 80 and 84, so that the respective part 108, 110 in succession is acted upon both by the one and by the other part surface 82 and 80 and 84 accelerated blasting material.
  • a plurality of sliding walls 120, 122, 124, 126 are provided, with which the undercut contour of the two disk body 22 and the scar 24 can be closed, so that a blasting material from the respective blasting chamber 74, 76, 78 can escape.
  • the sliding walls 120, 122, 124, 126 are displaceable along the arrows 127 for this purpose.
  • the sub-surfaces 42, 44 and 80, 82, 84 each extend obliquely to a perpendicular to the axis of rotation R. As included within the scope of the invention, however, it is to be considered that the sub-surfaces 42, 44 or 80, 82, 84 are also parallel to Rotation axis R or perpendicular to a vertical axis of rotation R could run.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)

Claims (14)

  1. Dispositif de grenaillage de surface, en particulier de grenaillage par ultrasons, d'un composant (10) d'une turbine à gaz, comprenant au moins un dispositif vibratoire (46, 48 ; 86, 88, 90) présentant une surface (42, 44 ; 80, 82, 84) de projection de la grenaille, et un dispositif de maintien (34) au moyen duquel une zone de surface du composant (10) peut être positionnée par rapport à la surface du dispositif vibratoire (46, 48 ; 86, 88, 90), la surface du dispositif vibratoire (46, 48 ; 86, 88, 90) étant divisée en au moins deux surfaces partielles (42, 44 ; 80, 82, 84) contiguës, qui comprennent chacune une plage de chevauchement (58, 60 ; 100, 102, 104), et au moyen desquelles une partie (64 ; 108, 110) de la zone de surface du composant (10) peut être traitée par la grenaille projetée depuis l'une ou l'autre des surfaces partielles (42, 44 ; 80, 82, 84), caractérisé en ce qu'à chacune des deux surfaces partielles (42, 44 ; 80, 82, 84) contiguës est affecté un compartiment de grenaillage (38, 40 ; 74, 76, 78) séparé.
  2. Dispositif selon la revendication 1, caractérisé en ce que les deux surfaces partielles (42, 44 ; 80, 82, 84) contiguës sont situées sur un plan commun.
  3. Dispositif selon la revendication 1, caractérisé en ce que les deux surfaces partielles (42, 44 ; 80, 82, 84) contiguës sont disposées angulairement l'une par rapport à l'autre.
  4. Dispositif selon l'une des revendications précédentes, caractérisé en ce qu'à chacune des deux surfaces partielles (42, 44 ; 80, 82, 84) contiguës est affecté un dispositif vibratoire (46, 48 ; 86, 88, 90) séparé.
  5. Dispositif selon l'une des revendications précédentes, caractérisé en ce qu'une paroi de séparation (54 ; 96, 98) est disposée entre les deux surfaces partielles (42, 44 ; 80, 82, 84) contiguës.
  6. Dispositif selon la revendication 5, caractérisé en ce que la paroi de séparation (54 ; 96, 98) présente une section sensiblement en forme de S.
  7. Dispositif selon la revendication 5, caractérisé en ce que les deux compartiments de grenaillage (38, 40 ; 74, 76, 78) sont séparés l'un de l'autre par la paroi de séparation (54 ; 96, 98).
  8. Dispositif selon l'une des revendications 6 ou 7, caractérisé en ce que des parois (50, 52 ; 92, 94) du compartiment de grenaillage (38, 40 ; 74, 76, 78) sont partiellement formées par des parois de palettes (66, 68 ; 120, 122, 124, 126).
  9. Dispositif selon l'une des revendications précédentes, caractérisé en ce que la zone de surface du composant est affectée à un rotor, en particulier à un disque aubagé monobloc (10).
  10. Dispositif selon l'une des revendications précédentes, caractérisé en ce que le composant (10) est rotatif autour de son axe de rotation (R), la partie (64 ; 108, 110) de la zone de surface du rotor (10) pouvant être successivement traitée par la grenaille projetée depuis l'une ou l'autre des surfaces partielles (42, 44 ; 80, 82, 84).
  11. Procédé de grenaillage de surface, en particulier de grenaillage par ultrasons, d'un composant (10) d'une turbine à gaz, où une zone de surface du composant (10) et une surface (42, 44 ; 80, 82, 84) de projection de la grenaille d'un dispositif vibratoire (46, 48 ; 86, 88, 90) sont positionnées l'une par rapport à l'autre et déplacées l'une par rapport à l'autre lors du grenaillage de surface, caractérisé en ce qu'une partie (64 ; 108, 110) de la zone de surface du composant (10) est successivement traitée par la grenaille projetée par des plages de chevauchement (58, 60 ; 100, 102, 104) respectives d'au moins deux surfaces partielles (42, 44 ; 80, 82, 84) contiguës de la surface du dispositif vibratoire (46, 48 ; 86, 88, 90), lesdites deux surfaces partielles (42, 44 ; 80, 82, 84) contiguës étant affectées chacune à un compartiment de grenaillage (38, 40 ; 74, 76, 78) séparé correspondant.
  12. Procédé selon la revendication 11, caractérisé en ce que la partie (64 ; 108, 110) de la zone de surface du composant (10) est déplacée par les compartiments de grenaillage (38, 40 ; 74, 76, 78) affectés aux surfaces partielles (42, 44 ; 80, 82, 84) correspondantes.
  13. Procédé selon les revendications 11 et 12, caractérisé en ce que le composant (10) est tourné autour d'un axe de rotation (R) pour le grenaillage de surface de la partie (64 ; 108, 110) de la zone de surface du composant (10).
  14. Procédé selon l'une des revendications 11 à 13, caractérisé en ce que la zone de surface du composant (10) est positionnée par rapport aux deux surfaces partielles (42, 44 ; 80, 82, 84) au moyen d'un dispositif de maintien (34).
EP07846396A 2006-12-13 2007-12-05 Dispositif et procédé pour grenailler la surface d'une pièce de turbine à gaz Active EP2099585B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006058675A DE102006058675A1 (de) 2006-12-13 2006-12-13 Vorrichtung und Verfahren zum Oberflächenstrahlen eines Bauteils einer Gasturbine
PCT/DE2007/002198 WO2008071164A1 (fr) 2006-12-13 2007-12-05 Dispositif et procédé pour grenailler la surface d'une pièce de turbine à gaz

Publications (2)

Publication Number Publication Date
EP2099585A1 EP2099585A1 (fr) 2009-09-16
EP2099585B1 true EP2099585B1 (fr) 2011-06-29

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Application Number Title Priority Date Filing Date
EP07846396A Active EP2099585B1 (fr) 2006-12-13 2007-12-05 Dispositif et procédé pour grenailler la surface d'une pièce de turbine à gaz

Country Status (6)

Country Link
US (1) US8499597B2 (fr)
EP (1) EP2099585B1 (fr)
AT (1) ATE514527T1 (fr)
CA (1) CA2671733C (fr)
DE (1) DE102006058675A1 (fr)
WO (1) WO2008071164A1 (fr)

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Publication number Priority date Publication date Assignee Title
DE102008010847A1 (de) * 2008-02-25 2009-08-27 Rolls-Royce Deutschland Ltd & Co Kg Verfahren und Vorrichtung zum Kugelstrahlverfestigen von Bliskschaufeln
DE102010001287A1 (de) * 2010-01-27 2011-07-28 Rolls-Royce Deutschland Ltd & Co KG, 15827 Verfahren und Vorrichtung zur Oberflächenverfestigung von Bliskschaufeln
US10493594B2 (en) * 2016-04-12 2019-12-03 General Electric Company Apparatus and method for peening of machine components
US11298799B2 (en) * 2018-05-03 2022-04-12 General Electric Company Dual sided shot peening of BLISK airfoils
CN115351731B (zh) * 2022-10-19 2023-02-03 成都市鸿侠科技有限责任公司 一种异形复杂曲面用夹紧机构
CN116770036A (zh) * 2023-06-21 2023-09-19 安徽理工大学 一种渐进型撞针式超声喷丸表面强化设备

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Publication number Priority date Publication date Assignee Title
US3482423A (en) * 1968-02-26 1969-12-09 Metal Improvement Co Blade peening masking apparatus
FR2801236B1 (fr) * 1999-11-18 2001-12-21 Snecma Procede et machine de grenaillage par ultrasons de pieces sur une roue
GB2356588B (en) * 1999-11-25 2003-11-12 Rolls Royce Plc Processing tip treatment bars in a gas turbine engine
FR2814099B1 (fr) 2000-09-21 2002-12-20 Snecma Moteurs Grenaillage transversal par ultrassons des aubes sur un rotor
US7028378B2 (en) * 2000-10-12 2006-04-18 Sonats-Societe Des Nouvelles Applications Des Techniques De Surfaces Method of shot blasting and a machine for implementing such a method
FR2815280B1 (fr) * 2000-10-12 2003-01-03 Sonats Soc Des Nouvelles Appli Machine et procede de grenaillage
FR2816537B1 (fr) * 2000-11-16 2003-01-17 Snecma Moteurs Procede et installation de grenaillage par ultrasons des alveoles annulaires d'attache d'aubes sur un rotor
FR2816636B1 (fr) * 2000-11-16 2003-07-18 Snecma Moteurs Grenaillage des sommets des aubes refroidies
US20060021410A1 (en) * 2004-07-30 2006-02-02 Sonats-Societe Des Nouvelles Applications Des Techniques De Surfaces Shot, devices, and installations for ultrasonic peening, and parts treated thereby
DE102004037954A1 (de) * 2004-08-05 2006-03-16 Mtu Aero Engines Gmbh Vorrichtung zum Oberflächenstrahlen von Bauteilen
FR2907360B1 (fr) * 2006-10-20 2009-05-22 Sonats Soc Des Nouvelles Appli Procedes et installations de grenailles.

Also Published As

Publication number Publication date
WO2008071164A1 (fr) 2008-06-19
ATE514527T1 (de) 2011-07-15
US8499597B2 (en) 2013-08-06
DE102006058675A1 (de) 2008-06-19
EP2099585A1 (fr) 2009-09-16
CA2671733A1 (fr) 2008-06-19
CA2671733C (fr) 2014-11-25
US20100043512A1 (en) 2010-02-25

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