WO2010028060A1 - Procédé pour améliorer la résistance à la fatigue par frottement d'alliages - Google Patents

Procédé pour améliorer la résistance à la fatigue par frottement d'alliages Download PDF

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Publication number
WO2010028060A1
WO2010028060A1 PCT/US2009/055753 US2009055753W WO2010028060A1 WO 2010028060 A1 WO2010028060 A1 WO 2010028060A1 US 2009055753 W US2009055753 W US 2009055753W WO 2010028060 A1 WO2010028060 A1 WO 2010028060A1
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WIPO (PCT)
Prior art keywords
component
alloy
fretting fatigue
nitriding
laser shock
Prior art date
Application number
PCT/US2009/055753
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English (en)
Inventor
Sushil K. Bhambri
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Zimmer, Inc.
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Filing date
Publication date
Application filed by Zimmer, Inc. filed Critical Zimmer, Inc.
Priority to EP09792182A priority Critical patent/EP2342364A1/fr
Publication of WO2010028060A1 publication Critical patent/WO2010028060A1/fr

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Classifications

    • 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
    • C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
    • C21D10/005—Modifying the physical properties by methods other than heat treatment or deformation by laser shock processing
    • 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
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/78—Combined heat-treatments not provided for above
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C8/06—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using gases
    • C23C8/08—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using gases only one element being applied
    • C23C8/24—Nitriding
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C8/06—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using gases
    • C23C8/36—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using gases using ionised gases, e.g. ionitriding
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C8/80—After-treatment

Definitions

  • the present invention relates to methods for enhancing the fretting fatigue resistance of alloys and, particularly, methods of enhancing the fretting fatigue of alloys by the laser shock peening of prehardened surfaces.
  • Orthopedic prostheses are used to replace and/or repair damaged or diseased bone in a patient's body.
  • titanium alloys such as Ti-6A1-4V
  • some prostheses are manufactured to be modular, i.e., a number of smaller pieces are individually manufactured and then connected together to form a complete prosthesis.
  • a femoral component of a hip prosthesis may be comprised of a separate diaphyseal portion, metaphyseal portion, and ball-shaped head portion that are connected together via Morse tapers.
  • connection between these independent components of the prosthesis allow for micromotion, i.e., extremely small relative surface displacement that occurs in the presence of loading, between the individual components.
  • fretting fatigue may occur within the titanium alloy which can shorten the useful life of the prosthesis.
  • alloys used in orthopedic components have been laser shock peened.
  • laser shock peening a laser beam is directed at the surface of the alloy to induce deep compressive residual stresses in the material.
  • the surfaces to be laser shock peened are first coated with a layer of paint or another ablation material. The surfaces are then positioned beneath a curtain of flowing water and subjected to the repetitive firing of a high energy laser beam.
  • the present invention provides a method for increasing the fretting fatigue resistance of an alloy by prehardening a surface of the alloy followed by laser shock peening the prehardened surface.
  • an orthopedic prosthesis is formed from a titanium alloy and subjected to surface nitriding followed by laser shock peening. By nitriding the titanium alloy, the hardness of the alloy is increased to a depth of as much as 0.02 ⁇ m below the surface. Then, by subjecting the nitrided surface of the alloy to laser shock peening, the fretting fatigue of the surface may be increased by more than 100%.
  • the resistance of the surface to fretting fatigue is substantially increased when compared to the increase in the resistance to fretting fatigue that would have been expected by a person of ordinary skill in the art with laser shock peening alone.
  • improvements in an alloy's fretting fatigue resistance is a direct result of an increase in the alloy's hardness.
  • laser shock peening the surface of a non-hardened alloy results in an increase in the alloy's hardness of approximately 50% and, correspondingly, the alloy exhibits an increased resistance to fretting fatigue of approximately 30%.
  • the improved fretting fatigue resistance of an alloy's surface is, as indicated above, believed by those of ordinary skill in the art to be a by-product of the increased hardness of the alloy's surface.
  • the alloy's hardness is increased by another 50%, while the alloy's resistance to fretting fatigue unexpectedly increases by as much as 150%.
  • the increase in the alloy's resistance to fretting fatigue cannot be directly correlated to the increase in the hardness of the nitrided alloy after laser shock peening, as it is only improved by approximately 50% as compared to the nitrided alloy.
  • the proportional relationship that those of ordinary skill in the art believe exists between the increase in the hardness of an alloy's surface and the increase in the fretting fatigue resistance of the alloy's surface has been disproved for a prehardened surface of an alloy that is subjected to laser shock peening.
  • this increase in the alloy's resistance to fretting fatigue is substantially greater than the 30% increase that results from laser shock peening alone.
  • improving by 100% or more the fretting fatigue resistance of the surface of an orthopedic implant allows the orthopedic implant to withstand loads in excess of twice of the anticipated loading requirements during use, which are typically three times the patient's body weight. As a result, the size of the orthopedic component may be decreased. Additionally, the design of the orthopedic components may also be altered, as less material may be needed in certain positions to bear the same loads as traditional implants. Furthermore, by laser shock peening a previously hardened, e.g., nitrided, surface, only selected sections of a prosthesis, as opposed to the entirety of a prosthesis, may be subjected to the desired surface modification. As a result, the prosthesis may be produced for a substantially lower cost than a prosthesis that is laser shock peened in its entirety.
  • the present invention provides a method of enhancing the fretting fatigue resistance of an alloy, including the steps of: forming an orthopedic component from an alloy, wherein the alloy has a melting point; nitriding at least a portion of the orthopedic component to form a nitrided surface, the nitrided surface having a first fretting fatigue strength; and laser shock peening at least a portion of the nitrided surface of the orthopedic component to form a laser shock peened surface, wherein the laser shock peened surface has a second fretting fatigue strength.
  • the present invention provides a method of enhancing the fretting fatigue resistance of an alloy, including the steps of: forming a modular orthopedic component from an alloy having a melting point, the modular orthopedic component including: a first component defining a male tapered surface; and a second component defining a female tapered surface, the male tapered surface of the first component configured to form a taper lock with the female tapered surface of the second component; nitriding at least one of the male tapered surface of the first component and the female tapered surface of the second component to form a nitrided surface, the nitrided surface having a first fretting fatigue; and laser shock peening at least a portion of the nitrided surface to form a laser shock peened surface, wherein the laser shock peened surface has a second fretting fatigued strength.
  • Fig. 1 is a flow chart depicting an exemplary method of performing the present invention.
  • FIG. 2 is a perspective view of an exemplary, modular orthopedic component in the form of a hip stem
  • FIG. 3 is a cross-sectional view of the hip stem of Fig. 2 further depicting a femoral head secured thereto.
  • the present invention provides a method for enhancing the fretting fatigue of an alloy by subjecting the alloy to surface hardening followed by laser shock peening.
  • the present invention is described in detail below and in the following Example with specific reference to Ti-6A1-4V, the present invention is more generally applicable to titanium alloys and the teachings of the present invention may be utilized in conjunction with alpha/beta or beta titanium alloys such as Ti-6A1-Nb alloy, Ti- 15Mo beta titanium alloy, and other biocompatible alloys, such as Co-Cr-Mo alloys, that can be surface hardened in a similar manner as Ti-6A1-4V.
  • Ti-6A1-4V is a titanium alloy used to manufacture orthopedic prosthesis and is readily available from numerous commercial sources.
  • Ti- 6A1-4V is received at Step 10 in mill annealed condition as stock material.
  • the Ti-6A1-4V has a fine grain alpha-beta microstructure in which the alpha phase has a hexagonal close packed crystal structure and the beta phase has a body centered cubic crystal structure.
  • the Ti-6A1-4V alloy is, in one exemplary embodiment, machined at Step 20 into a preform orthopedic component.
  • a preformed orthopedic component is an orthopedic component that has a shape that is dimensioned to be substantially similar to the desired dimensions of a final orthopedic component.
  • a preform orthopedic component may require machining or other modifications, however slight, before it is formed into a finished orthopedic component.
  • a final orthopedic component is formed at Step 20.
  • Modular hip stem 51 includes metaphyseal or neck portion 52, which forms a first component of modular hip stem 51, and diaphyseal or stem portion 54, which forms a second component of modular hip stem 51.
  • neck portion 52 includes female tapered surface 56 that cooperates with male tapered surface 58 of stem portion 54 to form a Morse taper and secure the components together.
  • neck portion 52 and stem portion 54 While described and depicted herein with specific reference to neck portion 52 and stem portion 54 being joined by cooperation of female tapered surface 56 of neck portion 52 and male tapered surface 58 of stem portion 54, the tapered surfaces may be reversed, such that neck portion 52 and stem portion 54 are joined by cooperation of a male tapered surface of neck portion 52 and a female tapered surface of stem portion 54.
  • neck portion also includes male tapered surface 60.
  • Male tapered surface 60 is configured to form a taper lock with a corresponding femoral head 62, as shown in Fig. 3.
  • Nitriding is a surface hardening heat treatment that introduces nitrogen into the surface of the Ti-6A1-4V alloy of the orthopedic component at a temperature substantially below both the melting point and beta-transus temperature of mill annealed Ti-6A1-4V.
  • nitriding processes introduce nitrogen into the surface of the Ti-6A1-4V orthopedic component by heating the component in either a liquid salt bath including nitrogen bearing salts or in a gas stream containing cracked ammonia.
  • the orthopedic component is nitrided utilizing a gas method, such as known methods that use a box furnace or fluidized bed, for example.
  • the nitriding process may be a liquid or plasma nitriding process.
  • any other known methods of nitriding, such as ion implantation, may be used.
  • nitriding is performed at a temperature below both the melting point and the beta-transus temperature of mill annealed Ti-6A1-4V. Specifically, the melting point for mill annealed Ti-6A1-4V is approximately between 2420 0 F and 3020 0 F and the beta- transus temperature is approximately between 1777°F and 1813°F.
  • the nitriding is performed by heating the components in a vacuum oven to approximately 1100 0 F in a nitrogen gas environment and holding the components at approximately HOO 0 F for 8 hours. In another exemplary embodiment, the nitriding is performed by heating the components in a vacuum oven to approximately 1050 0 F ⁇ 50 0 F in a nitrogen gas environment and holding the components at approximately 1050 0 F ⁇ 50 0 F for 8 hours. Additionally, the nitriding treatment may be conducted utilizing a Ti-Nidium® nitriding process. "Ti-Nidium" is a registered trademark of Zimmer, Inc, of Warsaw, Indiana.
  • Exemplary methods of performing nitriding processes are disclosed in U.S. Patent No. 5,192,323 to Shetty et al, entitled METHOD OF SURFACE HARDENING ORTHOPEDIC IMPLANT DEVICES, issued on March 9, 1993, the entire disclosure of which is expressly incorporated by reference herein.
  • hip stem 51 may be nitrided
  • only portions of the surfaces of hip stem 51 may be nitrided.
  • one or both of tapered surfaces 56, 58 of neck portion 52 and stem portion 54, respectively, may be nitrided.
  • the orthopedic component is laser shock peened at Step 40.
  • at least a portion of the surface that was previously nitrided at Step 30 is subjected to laser shock peening.
  • the entirety of the surfaces nitrided at Step 30 is subjected to laser shock peening.
  • only a portion of the surfaces subjected to nitriding at Step 30 are subjected to laser shock peening at Step 40.
  • all of the surfaces of hip stem 51 are nitrided, only one or both of tapered surfaces 56, 58 of neck portion 52 and stem portion 54, respectively, may be subjected to laser shock peening.
  • a laser beam is directed at the surface of the alloy to induce deep compressive residual stresses in the material.
  • the surfaces to be laser shock peened are coated with a layer of paint or another ablation material.
  • the surfaces are then positioned beneath a curtain of flowing water and subjected to the repetitive firing of a high energy laser beam.
  • the laser beam passes through the water, it contacts the paint or other ablation material coating the surfaces of the alloy.
  • the material is ablated and is transformed into plasma.
  • This transformation results in the generation of Shockwaves radiating from the surfaces of the alloy.
  • These Shockwaves are redirected toward the alloy's surfaces by the curtain of flowing water, which also washes away the ablated surface material.
  • compressive stress is introduced into the alloy.
  • a nitrided and laser shock peened alloy may exhibit an improvement in fretting fatigue resistance that exceeds 100% when compared to an alloy that is only nitrided.
  • the improvement in fretting fatigue resistance of a nitrided and laser shock peened alloy may be as great as 100%, 110%, 120%, 130%, 140%, or 150% as compared to an alloy that is only nitrided.
  • the laser shock peening induces greater compressive residual stress to a larger depth below the surface of the orthopedic component than is achieved without the prior surface hardening treatment.
  • This increased residual stress may delay crack nucleation and early crack propagation, while offering a resistance to abrasion.
  • this increase in the residual stresses may enhance the crack tolerance capacity, i.e., the ability of a material to accept crack formation without failure, increase the alloy's resistance to crack initiation, and increase the alloy's ability to arrest crack growth, all of which are indicative of the alloy's overall resistance to fretting fatigue failure.
  • the orthopedic component may be formed into a finished orthopedic component at Step 50.
  • the orthopedic component may be subjected to additional machining and/or milling steps using a computer numerical control machine, i.e., a CNC machine, for example.
  • additional work such as additional surface treatments and/or sterilization procedures, may be performed on the orthopedic component at Step 50 to render the orthopedic component suitable for implantation.
  • Wrought mill annealed Ti-6A1-4V ELI titanium alloy (ASTM F- 136-02A) bar stock was obtained from Supra Alloys, Inc., of Camarillo, California.
  • the alloy bar stock was formed into ten complete, modular hip stems each having a mid-stem Morse taper.
  • the modular hip stems that were formed were similar to hip stems available in the ZMR® Hip System, commercially available from Zimmer, Inc., of Warsaw, Indiana.
  • ZMR is a registered trademark of Zimmer, Inc., of Warsaw, Indiana.
  • Each of the modular components that form the Morse taper i.e., diaphyseal or stem components and metaphyseal or neck components, were subjected to thermal nitrogen diffusion surface hardening treatment, i.e., nitriding.
  • thermal nitrogen diffusion surface hardening treatment i.e., nitriding.
  • the individual modular components were placed in a Model H 26 vacuum furnace, manufactured by Vacuum Furnace Systems Corporation of Souderton, Pennsylvania, and heated to approximately 1100 0 F in a nitrogen gas environment. The components were held at approximately 1100° F for 8 hours. The components were then allowed to cool and were removed from the vacuum furnace.
  • the resulting nitrided surfaces of the male tapered modular orthopedic component experienced an increase in hardness of approximately 400 KHNlOg on the Knoop Hardness Scale.
  • the nitriding technique used in the present testing has an insignificant effect on the fatigue strength of the alloy. Specifically, as disclosed in U.S. Pat. No. 5,192,323 to Shetty et al., which is expressly incorporated by reference herein above, a component nitrided using this technique experiences a 5%-10% decrease in fatigue strength as compared to a non-nitrided component.
  • the fretting fatigue behavior of nitrided titanium alloy tapers has been reported to be slightly better than non-nitrided tapers when used in modular orthopedic components.
  • the nitrided modular components that included the male tapered sections were then sent to Lawrence Livermore National Laboratory in Livermore, California, to be subjected to laser shock peening.
  • the male tapers of the modular components were laser shock peened twice with 10 GW/cm of laser energy.
  • an intense beam of laser light is generated using a Nd: glass slab laser system and is impinged onto a sacrificial ablating material layer, such as paint or adhesive backed aluminum tape.
  • the laser light rapidly vaporizes a thin portion of the ablative layer and produces plasma confined by a thin laminar layer of water flowing over the surface of the ablating material.
  • Expanding plasma generates Shockwaves having a pressure of approximately 100 kbar that is directed toward the component by the flowing water. These Shockwaves create a plastic strain in the material resulting in the formation of a compressive residual stress field.
  • Laser peening parameters are optimized by varying the laser pulse irradiance, the laser energy, the duration of the laser pulse, and the number of treatment layers.
  • the male tapered modular components having the nitrided and laser shock peened male Morse taper section were taper locked to the female tapered modular components having only the nitrided female Morse taper section to form a mid-stem junction between the two components.
  • the resulting hip stem assemblies were then subjected to fatigue testing.
  • the male modular components, i.e., the diaphyseal components, of the hip stem assemblies were potted in bone cement 0.25 inch below the mid-stem modular junction of the assemblies.
  • the fatigue tests were conducted on specimens mounted in an anatomical orientation (15° medial/lateral, 10° anterior/posterior, and 12° antiversion) and in ambient conditions at a frequency of 10 Hz.
  • load was applied vertically to the hip stem assemblies using a MTS servohydraulic test machine, commercially available from MTS Systems Corporation, of Minneapolis, Minnesota.
  • the specimens were cyclically loaded in a sinusoidal waveform to 10,000,000 cycles or until fracture, whichever occurred first.
  • the next specimen was tested at higher or lower load depending upon whether the previous specimen had fractured or survived 10,000,000 cycles.
  • the next specimen was tested at a higher load.
  • the next specimen was tested at a lower load.
  • fretting fatigue i.e., fretting fatigue strength
  • fretting fatigue strength was determined for each of the modular components having a nitrided and laser shock peened male taper by plotting a load vs. number of cycles curve on a semi-log scale. Additional fatigue tests were repeated on three more groups of specimens at varying loads that were laser shock peened at different times. The results of these tests are set forth in Tables 2-5 below.
  • the mill annealed modular components having the male tapered sections that were hardened by nitriding and then laser shock peened had an average fretting fatigue strength of 7562 N. Specifically, of 17 samples that were tested at 7562.3 N, 3 of the samples failed before reaching the conclusion of the testing at 10,000,000 cycles for a failure rate of 18%.
  • the fretting fatigue strength of modular components having male tapered sections that were only hardened by nitriding averaged 3113 N. Specifically, of the 10 nitrided-only samples tested at 3113 N, 2 of samples fractured before reaching the conclusion of the testing at 10,000,000 cycles for a failure rate of 20%.

Abstract

La présente invention porte sur un procédé permettant d’accroître la résistance à la fatigue par frottement d'un alliage par prédurcissement d'une surface de l'alliage, suivi d’un martelage par choc laser de la surface prédurcie. Dans un exemple de mode de réalisation, une prothèse orthopédique est formée à partir d’un alliage de titane, et soumise à une nitruration de surface, suivie d’un martelage à choc laser. Grâce à la nitruration de l'alliage de titane, la dureté de la surface de l'alliage est accrue. Ensuite, grâce à l’exposition de la surface nitrurée de l'alliage à un martelage par choc laser, la fatigue par frottement de la surface nitrurée peut être améliorée de plus de 100 %.
PCT/US2009/055753 2008-09-02 2009-09-02 Procédé pour améliorer la résistance à la fatigue par frottement d'alliages WO2010028060A1 (fr)

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US9359508P 2008-09-02 2008-09-02
US61/093,595 2008-09-02

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109777977A (zh) * 2017-06-10 2019-05-21 黄国新 一种冲床冲棒的制造方法

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8968411B2 (en) * 2009-12-17 2015-03-03 Zimmer, Inc. Modular elbow prosthesis
US8936647B2 (en) 2012-06-22 2015-01-20 Zimmer, Inc. Elbow prosthesis
US10201374B2 (en) 2012-06-22 2019-02-12 Zimmer, Inc. Assembly tool for a prosthesis
EP2903776B8 (fr) 2012-10-01 2021-04-07 Raytheon Technologies Corporation Procédés d'essai de martelage par choc laser
FR3023851A1 (fr) * 2014-07-21 2016-01-22 Hydromecanique & Frottement Procede de traitement d'une piece nitruree/ nitrocarburee
CN104726688B (zh) * 2015-02-10 2017-07-18 江苏大学 一种考虑激光冲击效应的法兰内球笼挤压模具设计方法
US10619222B2 (en) 2015-04-08 2020-04-14 Metal Improvement Company, Llc High fatigue strength components requiring areas of high hardness
US11584969B2 (en) 2015-04-08 2023-02-21 Metal Improvement Company, Llc High fatigue strength components requiring areas of high hardness
EP3777776A1 (fr) * 2019-08-13 2021-02-17 Alessandro Melozzi Tête de prothèse de la hanche
CN110904404B (zh) * 2019-12-25 2023-07-11 浙江工业大学 基于钛合金表面激光氮化和喷丸同步复合技术的工艺方法与装置

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5192323A (en) * 1990-11-05 1993-03-09 Zimmer, Inc. Method of surface hardening orthopedic implant devices
US5308412A (en) * 1993-03-15 1994-05-03 Zimmer, Inc. Method of surface hardening cobalt-chromium based alloys for orthopedic implant devices
EP0985384A1 (fr) * 1998-09-10 2000-03-15 Buechel-Pappas Trust Méthode pour améliorer la résistance d'un composant prothétique
JP2004052997A (ja) * 2002-05-30 2004-02-19 Nsk Ltd 転動装置及びその製造方法
US20040236433A1 (en) * 2003-05-23 2004-11-25 Kennedy Richard L. Cobalt alloys, methods of making cobalt alloys, and implants and articles of manufacture made therefrom
US6911100B1 (en) * 2002-08-30 2005-06-28 Biomet, Inc. Method for controlling residual stress in prosthetics
US7338529B1 (en) * 2004-03-30 2008-03-04 Biomet Manufacturing Corp. Methods and apparatuses for enhancing prosthetic implant durability
JP2008195994A (ja) * 2007-02-09 2008-08-28 Kyoto Institute Of Technology チタン製品の表面改質方法及び表面改質チタン製品

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59406283D1 (de) * 1994-08-17 1998-07-23 Asea Brown Boveri Verfahren zur Herstellung einer Turbinenschaufel aus einer (alpha-Beta)-Titan-Basislegierung
US20060009857A1 (en) * 2004-07-08 2006-01-12 Gibbs Phillip M Method and apparatus for surface hardening implants
US9005306B2 (en) * 2006-11-07 2015-04-14 Biomedflex, Llc Medical Implants With Compliant Wear-Resistant Surfaces
KR20100112586A (ko) * 2008-01-04 2010-10-19 스미스 앤드 네퓨, 인크. 표면 합금 의료용 이식물

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5192323A (en) * 1990-11-05 1993-03-09 Zimmer, Inc. Method of surface hardening orthopedic implant devices
US5308412A (en) * 1993-03-15 1994-05-03 Zimmer, Inc. Method of surface hardening cobalt-chromium based alloys for orthopedic implant devices
EP0985384A1 (fr) * 1998-09-10 2000-03-15 Buechel-Pappas Trust Méthode pour améliorer la résistance d'un composant prothétique
JP2004052997A (ja) * 2002-05-30 2004-02-19 Nsk Ltd 転動装置及びその製造方法
US6911100B1 (en) * 2002-08-30 2005-06-28 Biomet, Inc. Method for controlling residual stress in prosthetics
US20040236433A1 (en) * 2003-05-23 2004-11-25 Kennedy Richard L. Cobalt alloys, methods of making cobalt alloys, and implants and articles of manufacture made therefrom
US7338529B1 (en) * 2004-03-30 2008-03-04 Biomet Manufacturing Corp. Methods and apparatuses for enhancing prosthetic implant durability
JP2008195994A (ja) * 2007-02-09 2008-08-28 Kyoto Institute Of Technology チタン製品の表面改質方法及び表面改質チタン製品

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
KING A ET AL: "Effects of fatigue and fretting on residual stresses introduced by laser shock peening", MATERIALS SCIENCE AND ENGINEERING A: STRUCTURAL MATERIALS:PROPERTIES, MICROSTRUCTURE & PROCESSING, LAUSANNE, CH, vol. 435-436, 5 November 2006 (2006-11-05), pages 12 - 18, XP025099155, ISSN: 0921-5093, [retrieved on 20061105] *
LIU D ET AL: "Fretting fatigue improvement of Ti6Al4V by coating and shot peening", JOURNAL OF MATERIALS SCIENCE AND TECHNOLOGY, SHENYANG, CN, vol. 21, no. 2, 1 March 2005 (2005-03-01), pages 246 - 250, XP009125992, ISSN: 1005-0302 *
LIU DAOXIN ET AL: "Effect of plasma nitriding and shot peening on the fretting damage resistance of Ti alloy", CAILIAO RECHULI XUEBAO = TRANSACTIONS OF MATERIALS AND HEATTREATMENT, CAILIAO RECHULI XUEBAO, CN, vol. 22, no. 3, 1 September 2001 (2001-09-01), pages 49 - 54, XP009126117, ISSN: 1009-6264 *
See also references of EP2342364A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109777977A (zh) * 2017-06-10 2019-05-21 黄国新 一种冲床冲棒的制造方法

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