EP2697014A1 - Procédé de fabrication d'une partie de rotor monobloc et partie de rotor monobloc - Google Patents

Procédé de fabrication d'une partie de rotor monobloc et partie de rotor monobloc

Info

Publication number
EP2697014A1
EP2697014A1 EP12715668.5A EP12715668A EP2697014A1 EP 2697014 A1 EP2697014 A1 EP 2697014A1 EP 12715668 A EP12715668 A EP 12715668A EP 2697014 A1 EP2697014 A1 EP 2697014A1
Authority
EP
European Patent Office
Prior art keywords
blade elements
blade
rolled
base body
elements
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.)
Withdrawn
Application number
EP12715668.5A
Other languages
German (de)
English (en)
Inventor
Goetz G. FELDMANN
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2697014A1 publication Critical patent/EP2697014A1/fr
Withdrawn legal-status Critical Current

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
    • 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
    • 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
    • B23P9/00—Treating or finishing surfaces mechanically, with or without calibrating, primarily to resist wear or impact, e.g. smoothing or roughening turbine blades or bearings; Features of such surfaces not otherwise provided for, their treatment being unspecified
    • B23P9/02—Treating or finishing by applying pressure, e.g. knurling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B39/00—Burnishing machines or devices, i.e. requiring pressure members for compacting the surface zone; Accessories therefor
    • B24B39/04—Burnishing machines or devices, i.e. requiring pressure members for compacting the surface zone; Accessories therefor designed for working external surfaces of revolution
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D7/00—Modifying the physical properties of iron or steel by deformation
    • C21D7/02—Modifying the physical properties of iron or steel by deformation by cold working
    • C21D7/04—Modifying the physical properties of iron or steel by deformation by cold working of the surface
    • C21D7/08—Modifying the physical properties of iron or steel by deformation by cold working of the surface by burnishing or the like
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F05D2230/26—Manufacture essentially without removing material by rolling
    • 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
    • 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
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49332—Propeller making

Definitions

  • the invention relates to a method for producing a one-piece rotor region according to the preamble of claim 1 and an integral rotor portion according to the closer defined in the preamble of claim 9. Art.
  • dynamic loads are caused by the interaction of the flow profiles with the turbulent flow, which also results in blade vibrations.
  • the sum of the dynamic part loads leads to the occurrence of high-frequency oscillations during operation, especially in the area of rotating blades of compressors and also of fans or in general of integral rotor sections of jet engines, which lead to highly dynamic loading of the rotor blades.
  • blades of compressors or blowers of jet engines are designed such that the dynamic operating loads do not exceed the fatigue strength or only defined and a fatigue strength and a defined level of fatigue resistance is ensured.
  • there is always a premature crack initiation and sometimes even an uncontrolled failure of fan and compressor blades which is mainly due to damage to the blades due to foreign bodies.
  • Such foreign body damage is impact damage caused by the impact of hard foreign bodies.
  • the foreign bodies are generally stones and fragments of screws, nuts, washers and the like, which are located on the runway and the runway.
  • the blade elements and integral therewith executed annular base body be designed appropriately massive ⁇ lead.
  • the undesirably high use of material increases the overall weight and manufacturing costs of a jet engine, which is not desirable.
  • the rotor blades and thus integrally executed annular body of a rotor area with ⁇ means shot peening, wherein during the ball ⁇ jet process in the near-surface regions of the blades residual stresses are generated, which counteract a resulting from a foreign body damage or vibration stress cracking and its crack propagation to the desired extent ,
  • the disadvantage here is that the surfaces of rotor blades which have been subsequently solidified by means of shot peening have a low surface quality which, after the post-consolidation process, has to be improved again during costly and therefore costly reworking steps.
  • the width ⁇ ren is a uniform machining of blades or blade elements of the one-piece rotor areas by means of shot peening rebounds and downs ⁇ shadowing can not be guaranteed for example due because surface areas 4,000ufi ⁇ ger be hit by ball elements than other surface areas, which in turn adversely affect the life ⁇ permanent effects, such as softening effects, and reproducible processing results are not guaranteed.
  • a solidification of one-piece rotor areas by means of shot peening is therefore also very inaccurate and moreover expensive due to the use of compressed air.
  • the present invention is therefore based on the object to provide a method for producing a one-piece rotor section, preferably a jet engine, avail ⁇ supply, by means of which one-piece rotor sections with high resistance to foreign body damage and against vibration loads at the same time low component weight can be produced.
  • the invention has for its object to provide a one-piece rotor area available, which is characterized by a high resistance to foreign body damage and vibration loads, is inexpensive to produce and whose surface is designed with a low roughness. According to the invention this object is achieved with a method having the features of claim 1 and with a einstü ⁇ ckigen rotor portion having the features of patent claim. 9
  • a jet drive ⁇ which comprises an annular base body and a plurality of circumferentially distributed blade elements which extend substantially radially from the base body, are in the blade elements via an intervening between blade elements rolling tool Deep rolling introduced in surface near ⁇ areas residual stresses.
  • a portion of a blade element Zvi ⁇ rule areas of the rolling tool is arranged in each case and the longitudinal sides of the blade element to be deep rolled at the same time.
  • the roller tool is radially inserted between the blade elements and the surfaces of the blade elements ⁇ be rolled.
  • Characterized in that the surfaces of the blade elements are rolled tightly ⁇ is a same consists of an annular body and a plurality of circumferentially spaced vane members formed integral rotor portion, preferably a jet engine ⁇ work, compared to non nachverloomen rotor areas with less material and therefore smaller overall weight and or higher resistance to foreign body damage and vibration loads executable.
  • the rolling tool is introduced radially between the blade elements, there is a simple way also the possibility of integral rotor sections with a high resistance to ⁇ run against foreign body damage and vibration loads, which have a plurality of axially in succession arranged on the main body blade elements. This is not possible with methods known from practice, in which the rolling tool is introduced in the axial direction between the blade elements, due to the low Ab ⁇ states between the individual blade element rows.
  • the surfaces of the blade elements are at least partially solid rolled by sequentiel ⁇ les radial retraction.
  • the surfaces of the blade elements are rolled at least in regions by sequential axial traversing.
  • the surfaces of the blade members at least partially firmly rolled by belie ⁇ bige travel paths of the rolling tool along the surfaces of the blade members, the surfaces of the blade elements are providable with a time required for the generation of a homogeneous flow around the blade elements surface structure.
  • a resistance of a one-piece rotor region is in a further advantageous variant of the invention Increases the process by that transition areas between the surfaces of the blade elements and the surface of the body between the blade elements are rolled by means of a rolling tool.
  • a resistance to foreign body damage and vibration loads of a one-piece rotor area characterized by a low weight can be further improved if the surface of the base body is firmly rolled between the blade elements by means of a rolling tool.
  • a rolling force can be varied to optimal, the surfaces of the blade elements selectively with the ge ⁇ geninate respectively for increasing the resistance to foreign object damage and vibration loads near-surface compressive residual stress.
  • the one-piece rotor section according to the invention has an annular body and a plurality of distributed over the circumference of the body blade elements which extend radially We ⁇ sentlichen from the base body. Since at least the blade elements have a solidly rolled surface, the one-piece rotor region according to the invention is characterized by a lower weight compared to non-after-solidified rotor regions or only partially solidified one-piece rotor regions at least for the same resistance to foreign body damage and vibration loads and cost in the field of blade elements without additional manufacturing steps cost a surface characterized by a high surface quality. leads, which supports a homogeneous flow around the blade elements un ⁇ .
  • connection areas between surfaces of the vane elements and an oil are also have connection areas between surfaces of the vane elements and an oil. ier surface of the body on a hard-rolled surface, both a resistance to foreign body damage and vibration loads and a homogeneous flow around the one-piece rotor area is guaranteed.
  • Figure 1 is a highly schematic longitudinal sectional view of a jet engine, which is designed with a einstü ⁇ ckigen rotor region.
  • FIG. 2 is an enlarged detail view of a show ⁇ felimplantations of the one-piece rotor portion of FIG. 1.
  • Fig. 3 is a side view of a rolling tool
  • Fig. 1 shows a longitudinal sectional view of a jet engine ⁇ plant 1, which is designed with a bypass duct 2. Furthermore, the jet engine 1 is formed with an inlet region 3, which is followed downstream by a fan 4 in a manner known per se. Again downstream of the fan 4, the fluid flow in the jet engine 1 is divided into a secondary flow and a core flow, wherein the secondary flow through the bypass channel 2 and the core flow into an engine core ⁇ 5 flows, in turn, in a conventional manner with a compressor device 6, a burner 7 and a turbine device 8 is executed.
  • FIG. 2 is an enlarged detail view of a ⁇ lumpy rotor portion 9 of the compressor means 6 of an annular base body 10 and a plurality is shown on comprises the circumference distributed vane elements 11, which extend substantially radially from the base body 10.
  • the integral rotor section 9 constitutes a so-called blisk, which is an integrally bladed rotor construction.
  • the term blisk is composed of the English words "blade” for shovel and "disk” for disc.
  • the disc or the annular base body 10 and the sight ⁇ feletti 11 are made of one piece, whereby provided at more ⁇ lumpy areas running rotor blade roots and disk grooves omitted.
  • the one-piece rotor region 9 is characterized by a significantly smaller number of parts compared to conventionally bladed compressor rotors and the disk shape of the annular base body 10 is designed for a lower edge load.
  • the surface 13 or the annulus of the main body 10 between the blade elements 11 is preferably also firmly rolled by means of a single-finger rolling tool.
  • Each upper ⁇ surface near areas of the one-piece rotor portion 9 are solidified by increasing the dislocation density through the fixed rollers of the surfaces of the longitudinal sides and the edges of the blade members 11, the transition areas 12 and the surface 13 of the base body 10 and cured, the surface layer of the rotor region. 9
  • the hardening of the surface layer reduces the risk of cracks resulting from foreign body damage as well as vibration loads.
  • the introduced into the material by the deep rolling compressive stresses result in the region of the rotor portion 9 to counteract that this a crack propagation ⁇ step after formation of a crack and thus have a positive effect as regards the fatigue strength and thus with respect to the life of the jet engine. 1
  • FIGS. 3 and 4 each show a side view of a rolling tool 14 for deep rolling the longitudinal sides or the entire surface of the blade elements 11 of the rotor region 9.
  • the rolling tool 14 comprises a tool carrier 15 which is connectable to a carrier spindle 16 of a machine tool in dar ⁇ braem extent.
  • Two pliers body 17, 18 of the rolling tool 14 in the region of a pivot bearing 19 are rotatably connected to the tool carrier 15, wherein the pliers body 17, 18 are coupled via a presently acting as a single-acting piston-cylinder unit drive means 20 and a distance between Wälz Schemeen 21, 22 is reduced as a function of a drive device-side rotational movement of the tong body 17 and 18 about the pivot bearing 19.
  • the hydraulic pressure is applied to the drive device 20 and a piston element 23 moves out of a cylinder element 24 of the drive device 20 due to the applied hydraulic pressure, whereby a distance between the ends 25 facing away from the rolling regions 21 and 22 results from such a change in operating state of the drive device 20 and 26 the pliers body 17 and 18 is increased, while the distance between the Wälz Schemeen 21 and 22 is reduced in accordance with the geometric conditions in dependence of the rotational movement of the pliers body 17 and 18 to the pivot bearing 19 around.
  • the pliers body 17 and 18 are each rotatably connected to the drive device 20 in the region of their ends 25 and 26.
  • a distance between the Wälz Schemeen 21 and 22 remains the same.
  • the pliers body 17 and 18 are connected via piston elements 28 and 29 with the tool carrier 15 in operative connection, wherein the pliers body 17 and 18 of the piston elements 28 and 29 relative to the tool carrier 15 about the pivot bearing 19 in a relation to the tool carrier 15 and in FIG. Defined zero position shown 3 are reset when a Zan ⁇ gen Sciences 17 and 18 together about the pivot bearing 19 twisting rotational force is substantially equal to zero.
  • the forceps bodies 17 and 18, a presently two spring means 30 and 31 comprehensive rear part ⁇ device 32 assigned, via a distance between the rolling areas 21 and 22 by reset device-side turning the tong body 17 and 18 in the direction of a maximum value is variable.
  • the Wälz Symposiume 21 and 22 comprise present each a ball element 33, 34 which are respectively in support portions placed ⁇ accepted and can be acted upon in a known manner with hydrau ⁇ lischem pressure to the blade elements 11 with the required Wälzkraft via the ball members To act on 33 and 34.
  • the holding portions 35 and 36 are present in the clamped bodies 17 and 18 fixedly connected via screw connections and at least approximately finger-like executed Adapterele ⁇ elements 37 and 38 and preferably screwed via set screws with them.
  • the adapter elements 37 and 38 are each interchangeable, whereby over the rolling tool 14 different Eingriffstie ⁇ fen in the radial direction between the blade elements 11 can be realized.
  • designed adapter elements 37 and 38 are connected to the tong bodies 17 and 18 also in respect of the portable pressure or Wälzkraft, wherein thinner adapter elements are insertable into narrower areas between the cast ⁇ fel instituten.
  • an axis 39 of the support spindle 16 is connected to the tool carrier 15 operating state between the Wälz Schemeen 21 and 22nd by a contact point between the rolling areas 21 and 22 which is equal to zero at a distance between the rolling areas 21 and 22.
  • the axis or the spindle support axis 29 and an axis through the contact point between the Wälz Schemeen 21 and 22 congruent, whereby the programming of the rolling process is substantially simplified.
  • a distance between the rolling regions 21 and 22 can only be reduced by the drive device 20 to a defined limit value.
  • the two ball elements 33 and 34 are by corresponding rotation or pivoting of the pliers body 17 and 18 and thus the adapter elements 37 and 38 are not brought into contact with each other, whereby damage to the rolling tool 14 are excluded in a simple manner.
  • the rolling tool 14 By means of the rolling tool 14 are integrally bladed disks and rotors of jet engines at low cost festwalzbar. Due to the quick and easy replacement of the adapter elements 37 and 38, the rolling tool 14 is low Set-up times for different geometrically executed rotor areas can be used, wherein in addition to different depths of engagement between blade elements and different processing ⁇ forces during the rolling process on differently designed components with high security and process capability are darstell ⁇ bar.
  • the rolling tool 14 By means of the pliers design of the rolling tool 14 is a treatment of blade elements or of Aerofoils of integral rotor sections from Tip to Fillet possible, with a simultaneous deep rolling of the pressure and suction sides of blade elements to avoid an inherent tension delay is provided.
  • the surface of the base body between the blade elements or the annulus by means of a single tool is festwalzbar.
  • the rolling tool 14 can be integrated into any known machining center. In contrast to a post-consolidation by means of shot peening, there are no expensive systems to procure.
  • the Nachverfest Trent Runaway can be, for example, in conventional milling by means of the rolling die 14 ⁇ leads.
  • the milling centers are equipped with the rolling tool 14 and the surfaces of one-piece rotor sections are processed analogously to milling with the deep rolling tool 14 Be ⁇ rich their surface.
  • the turbine apparatus The turbine apparatus

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Procédé de fabrication d'une partie de rotor (9) monobloc, de préférence d'un réacteur (1). Cette partie de rotor (9) comprend un corps de base (10) annulaire et plusieurs éléments aubes (11) répartis sur la périphérie, ces éléments aubes s'étendant sensiblement dans le sens radial à partir du corps de base (10). Un outil de laminage pénétrant entre les éléments aubes (11) permet d'introduire des contraintes propres dans lesdits éléments aubes (11) par galetage de renforcement dans des zones proches de la surface. Lors du galetage de renforcement, une zone respective de l'élément aube (11) est disposée entre des zones de l'outil de laminage et les faces longitudinales de l'élément aube (11) sont galetées simultanément. Selon l'invention, l'outil de laminage est introduit radialement entre les éléments aubes (11) et les surfaces des éléments aubes sont galetées. Ainsi, au moins les éléments aubes (11) présentent une surface usinée par galetage de renforcement.
EP12715668.5A 2011-04-12 2012-04-12 Procédé de fabrication d'une partie de rotor monobloc et partie de rotor monobloc Withdrawn EP2697014A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011007224A DE102011007224A1 (de) 2011-04-12 2011-04-12 Verfahren und Herstellung eines einstückigen Rotorbereiches und einstückiger Rotorbereich
PCT/EP2012/056612 WO2012140103A1 (fr) 2011-04-12 2012-04-12 Procédé de fabrication d'une partie de rotor monobloc et partie de rotor monobloc

Publications (1)

Publication Number Publication Date
EP2697014A1 true EP2697014A1 (fr) 2014-02-19

Family

ID=45992234

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12715668.5A Withdrawn EP2697014A1 (fr) 2011-04-12 2012-04-12 Procédé de fabrication d'une partie de rotor monobloc et partie de rotor monobloc

Country Status (4)

Country Link
US (1) US20130216391A1 (fr)
EP (1) EP2697014A1 (fr)
DE (1) DE102011007224A1 (fr)
WO (1) WO2012140103A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012018604A1 (de) 2012-09-20 2014-03-20 Rolls-Royce Deutschland Ltd & Co Kg Walzwerkzeugvorrichtung
DE102012018605A1 (de) * 2012-09-20 2014-03-20 Rolls-Royce Deutschland Ltd & Co Kg Walzwerkzeugvorrichtung
DE102012111347B4 (de) * 2012-11-23 2016-08-18 WOMA GmbH Verfahren zum Bearbeiten eines fluiddruckbeaufschlagten Bauteils einer Pumpe und fluiddruckbeaufschlagtes Bauteil
CN113369799B (zh) * 2021-07-07 2022-07-26 哈尔滨电气动力装备有限公司 核电站轴封核主泵导叶过流面的制造工艺

Family Cites Families (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE496732C (de) * 1927-12-20 1930-04-25 Aeg Zum Schutz gegen Auswaschungen durch stroemenden Dampf gehaertete Turbinenschaufel
US3290915A (en) * 1964-04-30 1966-12-13 United Aircraft Corp Machine for cold-rolling a nonuniform surface
DE4309176C2 (de) * 1993-03-22 1995-10-19 Siemens Ag Verfahren zum Festwalzen eines Bauteils
DE19511882B4 (de) * 1995-03-31 2005-01-05 Audi Ag Verfahren zum Verfestigen von Werkstückoberflächen
DE19516834A1 (de) * 1995-05-08 1996-11-14 Siemens Ag Walzvorrichtung zur Erzeugung von Druckeigenspannungen in einem Bauteil sowie Verwendung der Walzvorrichtung
US5826453A (en) * 1996-12-05 1998-10-27 Lambda Research, Inc. Burnishing method and apparatus for providing a layer of compressive residual stress in the surface of a workpiece
US6415486B1 (en) * 2000-03-01 2002-07-09 Surface Technology Holdings, Ltd. Method and apparatus for providing a residual stress distribution in the surface of a part
US6622570B1 (en) * 2000-03-01 2003-09-23 Surface Technology Holdings Ltd. Method for reducing tensile stress zones in the surface of a part
US6568077B1 (en) * 2000-05-11 2003-05-27 General Electric Company Blisk weld repair
GB2367028B (en) * 2000-09-22 2004-06-09 Rolls Royce Plc Gas turbine engine rotor blades
DE10245396A1 (de) * 2002-09-28 2004-04-15 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zur Oberflächenbearbeitung von Werkstücken
FR2871399B1 (fr) * 2004-06-15 2006-09-22 Snecma Moteurs Sa Procede de reparation d'un element d'aube
US7229253B2 (en) * 2004-11-30 2007-06-12 General Electric Company Fatigue-resistant components and method therefor
US7185521B2 (en) * 2005-05-13 2007-03-06 General Electric Company Method and apparatus for process control of burnishing
US7805972B2 (en) * 2005-10-12 2010-10-05 Surface Technology Holdings Ltd. Integrally bladed rotating turbo machinery and method and apparatus for achieving the same
US8024846B2 (en) * 2006-01-27 2011-09-27 General Electric Company Preparation of an article surface having a surface compressive texture
US7600404B2 (en) * 2006-04-07 2009-10-13 Surface Technology Holdings, Ltd. Surface treatment apparatus and method
US20070281088A1 (en) * 2006-06-02 2007-12-06 United Technologies Corporation Low plasticity burnishing of coated titanium parts
US7530792B2 (en) * 2006-06-30 2009-05-12 General Electric Company Component of variable thickness having residual compressive stresses therein, and method therefor
KR20080012744A (ko) * 2006-08-03 2008-02-12 유나이티드 테크놀로지스 코포레이션 부식 코팅되는 부품의 코팅전 버니싱
US8079120B2 (en) * 2006-12-30 2011-12-20 General Electric Company Method for determining initial burnishing parameters
US8051565B2 (en) * 2006-12-30 2011-11-08 General Electric Company Method for increasing fatigue notch capability of airfoils
US7526965B2 (en) * 2006-12-30 2009-05-05 General Electric Company Method for evaluating burnishing element condition
FR2950547B1 (fr) * 2009-09-29 2012-08-24 Snecma Reparation d'aubes de compresseur en titane par compression a froid
DE102010001287A1 (de) * 2010-01-27 2011-07-28 Rolls-Royce Deutschland Ltd & Co KG, 15827 Verfahren und Vorrichtung zur Oberflächenverfestigung von Bliskschaufeln
US9139897B2 (en) * 2010-12-30 2015-09-22 United Technologies Corporation Thermal barrier coatings and methods of application
US9737965B2 (en) * 2012-01-23 2017-08-22 United Technologies Corporation Roll peening tooling and process

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2012140103A1 *

Also Published As

Publication number Publication date
US20130216391A1 (en) 2013-08-22
WO2012140103A1 (fr) 2012-10-18
DE102011007224A1 (de) 2012-10-18

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