US3762881A - Composite high strength machine element and method of making the same - Google Patents

Composite high strength machine element and method of making the same Download PDF

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US3762881A
US3762881A US00152862A US3762881DA US3762881A US 3762881 A US3762881 A US 3762881A US 00152862 A US00152862 A US 00152862A US 3762881D A US3762881D A US 3762881DA US 3762881 A US3762881 A US 3762881A
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sleeve
metals
interface
sintered
sleeves
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W Dunn
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Federal Mogul LLC
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Federal Mogul LLC
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/14—Special methods of manufacture; Running-in
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/12—Structural composition; Use of special materials or surface treatments, e.g. for rust-proofing
    • F16C33/121—Use of special materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/12—Structural composition; Use of special materials or surface treatments, e.g. for rust-proofing
    • F16C33/122—Multilayer structures of sleeves, washers or liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/30—Parts of ball or roller bearings
    • F16C33/58—Raceways; Race rings
    • F16C33/62—Selection of substances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/30—Parts of ball or roller bearings
    • F16C33/58—Raceways; Race rings
    • F16C33/64—Special methods of manufacture
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/02—Sliding-contact bearings for exclusively rotary movement for radial load only
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/22—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings
    • F16C19/24—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly
    • F16C19/26—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly with a single row of rollers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2204/00—Metallic materials; Alloys
    • F16C2204/60—Ferrous alloys, e.g. steel alloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2220/00—Shaping
    • F16C2220/20—Shaping by sintering pulverised material, e.g. powder metallurgy
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2220/00—Shaping
    • F16C2220/40—Shaping by deformation without removing material
    • F16C2220/46—Shaping by deformation without removing material by forging
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2223/00—Surface treatments; Hardening; Coating
    • F16C2223/10—Hardening, e.g. carburizing, carbo-nitriding
    • F16C2223/12—Hardening, e.g. carburizing, carbo-nitriding with carburizing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2226/00—Joining parts; Fastening; Assembling or mounting parts
    • F16C2226/10—Force connections, e.g. clamping
    • F16C2226/16—Force connections, e.g. clamping by wedge action, e.g. by tapered or conical parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2226/00—Joining parts; Fastening; Assembling or mounting parts
    • F16C2226/50—Positive connections
    • F16C2226/70—Positive connections with complementary interlocking parts
    • 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
    • Y10T29/49826—Assembling or joining
    • Y10T29/49861—Sizing mating parts during final positional association
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12451—Macroscopically anomalous interface between layers
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12778—Alternative base metals from diverse categories
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12986—Adjacent functionally defined components

Definitions

  • ABSTRACT This composite high-strength bushing consists of a heavy-load-bearing sleeve of sintered powdered high performance alloy and a lesser-load-bearing support sleeve of sintered base metal such as sintered powdered iron.
  • the outer sleeve has an internal taper while the inner sleeve has a matching external taper, both sleeves being separately formed from their respective powdered metals by suitable dies in conventional briquetting presses and thereafter sintered and forged by forcing them together in a hot-forging press at a high temperature.
  • the outer and inner sleeves are thereby firmly and inseparably joined by high heat and pressure and interlocked by the migration of minute portions'of one of the metals past minute portions of the other metal across the tapered interface therebetween, thereby forming an intermediate zone of the intermingled metals encircling the interface.
  • a modification employs tapers of slightly different convergence between the outer and inner sleeves but also results in a similarly-inseparable interlocking connection by a similar migration of the metals into an intermediate zone encircling the interface.
  • FIG. 1 is a longitudinal section through the outer powdered metal sleeve, after briquetting and sintering, according to one form of the invention
  • FIG. 2 is a longitudinal section through the inner powdered metal sleeve, after briquetting and sintering, according to the same form of the invention
  • FIG. 3 is a longitudinal section through a hot-forging die in a hot-forging press, showing the outer and inner sleeves of FIGS. 1 and 2 at the start of the hot-forging operation of uniting them into a composite bushing;
  • FIG. 4 is a longitudinal section through the composite bushing, after forging
  • FIG. 5 is a flow diagram of the steps involved in the method of making the composite bushing of FIG. 4;
  • FIG. 6 is a longitudinal section through a modification of the invention shown in FIGS. 1 to 5 inclusive, wherein the outer and inner sleeves possess slightly different converging tapers, with the components assembled immediately prior to hot forging as in FIG. 3;
  • FIG. 7 is a photomicrograph of a longitudinal section of the composite bushing of FIG. 4 showing the interlocking of the different metals at the interface;
  • FIGS. 8 and 9 are reproductions of graphical test charts produced by tension tests made upon specimens cut from the composite bushings, as shown in FIG. 4;
  • FIG. 10 is a photomicrograph similar to FIG. 7 but showing the interlocking of the metals of the different metals at the interface of a longitudinal section of the modification involving the differently-tapered sleeves shown in FIG. 6, after hot-forging;
  • FIG. 11 is a longitudinal section through the composite bushing, after forging, with the positions of the com ponents of FIG. 4 reversed.
  • FIG. 4 shows a composite high-strength bushing, generally designated 10, according to one form of the invention, as composed of a high-performance alloy outer sleeve 12 joined at an approximately conical or tapered interface 11 to a plain iron inner sleeve 14 with opposite flat annular end surfaces 13 and 15.
  • the sleeves l2 and 14 are formed from sintered powdered metal outer and inner components 16 and 18 respectively (FIG. 3) according to the procedure shown in the flow chart or diagram in FIG. 5.
  • the outer and inner components 16 and 18 (FIGS.
  • the dies for briquetting the outer components 16 are so formed as to impart to the outer component 16 an outer cylindrical surface 20, upper and lower annular surfaces 22 and 24, a relatively short upper inner cylindrical bore surface 26, and a lower tapered or conical bore surface 28, with the surfaces 26 and 28 collectively forming a partially tapered and partially cylindrical inner surface 30.
  • the dies for briquetting the inner component 18, are so formed as to provide an outer surface 32 consisting of a relatively short lower cylindrical surface 34 and an upper conical or tapered surface 36, the surface 36 having the same taper as the surface 28 of the outer component 16.
  • the short cylindrical surfaces 26 and 34 provide clearances with the adjacent tapered surfaces 36 and 28 respectively. These clearances receive the sidewise flow of metal during forging and thereby prevent folding over" at the opposite ends 13 and 15.
  • the inner component 18 has upper and lower flat annular surfaces 38 and 49 respectively and an inner cylindrical surface 42.
  • the outer component 16 is formed by briquetting a powder of a suitable high performance metal or metal alloy, the particular alloy being used as exemplary in the present invention being the so-called S.A.E. 4600 alloy powder.
  • the inner component 18, which does not require the load-bearing characteristics of the outer portion 12 of the composite sleeve 10, is formed from plain iron powder.
  • the tapered surfaces 28 and 36 are both formed with matching tapers of 3. Briquetting is carried out to produce a density of approximately percent in the finished briquettes I6 and 18. Separate sintering is then carried out at a temperature between 2,100 and 2,150 F., individually for each piece.
  • the sintered powdered metal outer and inner sleeves l2 and 14 are then placed in telescoped relationship, the temperatures of both components are then brought to a predetermined forging temperature within the range of l,500 to 2,100" F. and then placed in the cylindrical die bore 42 of a forging press 44.
  • the latter is provided with a hot-forging die set 45 including a die plate 46 containing the cylindrical die bore 42, a lower tubular punch 48 and an upper tubular punch 50 adapted to telescope with the die bore 42 and having flat annular facing surfaces 52 and 54 respectively adapted to produce the flat annular end surfaces 13 and 15 respectively in the composite high strength sleeve or machine element 10 (FIG. 4).
  • the lower tubular punch 48 (FIG.
  • a cylindrical core rod 64 with an outer cylindrical surface 66 is adapted to telescope with the lower and upper punch bores 56 and 58 and with the die bore 62 to define a die cavity 68.
  • the outer high performance alloy component 16 and the inner low performance component 18 are separately briquetted to densities of approximately 75 percent in separate briquetting dies to produce the configurations described above.
  • the briquettes 16 and 18 (FIGS. 1 and 2) are then separately sintered at temper atures preferably between 2,l00 and 2,150 F. with the upper tubular punch 50 retracted upward so as to leave the mouth of the die cavity 68 open.
  • the sintered outer and inner sleeves 12 and 14 are then removed from the sintering oven and transferred to the die cavity 68 of the forging die set 45 of the forging press 44 at a predetermined temperature between l,800 and 2,l0O F.
  • the sintered sleeves l2 and 14 may be more convenient to reheat the sintered sleeves l2 and 14 prior to placing them in the forging die cavity 68, due to loss of heat sustained in making the transfer from the sintering oven to the forging press 44.
  • the thus heated sintered outer and inner sleeves 12 and 14 are placed in the forging die cavity 68 in telescoping relationship (FIG. 3).
  • the upper punch 50 is moved downward with the cylindrical surface 42 of the die plate 46 preventing lateral metal flow and the top surface 52 of the lower punch 48 acting as an anvil to effect axial motion of the outer sleeve 12 relatively to the inner sleeve 14.
  • This hot forging operation is carried out with sufficient force to drive the outer sleeve 12 with the internal tapered surface 28 of the outer component 16 axially downward upon the outer tapered surface 36 of the inner sleeve 14 and to raise the density of the composite element to about 98 percent, or substantially solid metal.
  • This action causes the end surfaces 22 and 24 of the outer sleeve 12 to move into substantially co-planar relationship with the end surfaces 38 and 410 respectively of the inner sleeve 14 (FIG. 4).
  • Torsion tests (FIGS. 8 and 9) of standard specimens cut longitudinally from the composite bushing 10 at the interface 11 therebetween confirm the exceptional interlocking obtained at the interface 11. These specimens comprised rectangular blocks one inch in length and 0.312 inches square with the interface 11 disposed midway between the longitudinal side surfaces. The tests were performed in the torsion testing machine disclosed and claimed in the l-laller US. Pat. No. 3,122,915 of Mar. 3, 1964 for Torsion Testing Machine. In these two graphic charts, the abscissae represent the applied twist to the specimen in degrees whereas the ordinates indicate the applied torque in inch pounds. The curves obtained were drawn by a pen moving transversely to the motion of the chart.
  • the peaks of the curves A, B, C, D and E represent the peak torque measured in inch pounds obtained when the test specimen began to fracture or fail, and the rotation or twist of the test specimen in degrees at which such failure occurred is indicated by the reading of the horizontal scale designated by the words twist (degrees)".
  • twist degrees
  • specimen D a tensile strength of 79,286 p.s.i. with 20 percent elongation; and for specimen E a tensile strength of 71,430 p.s.i. with 17 percent elongation.
  • a composite high-strength bushing 71 which is substantially identical in appearance to the composite high strength bushing 10 shown in FIG. 4, hence is not separately illustrated in its finished form.
  • the sole difference in the construction is that the composite bushing, generally designated 70, consisting of the outer sleeve 72 of high performance alloy with the inner sleeve 74 of base metal, such as plain iron, brings together differently tapered internal and external conical surfaces 76 and 78 of the outer and inner sleeves 72 and 74 respectively.
  • the internal conical surface 76 of the outer sleeve 72 is provided with an approximately three-degree taper
  • the outer conical surface 78 of the inner sleeve 74 is provided with a two-degree taper.
  • the briquett ing, reheating, sintering and forging procedures, includingthe temperatures and pressures involved, remain substantially the same as those set forth above in connection with the production of the composite high performance bushing 10 of FIG. 4 and achieve similar results.
  • a similar interlocking at the interface corre sponding to the interface 11 is also produced, with a similar migration of the two metals into one another at that interface, as shown by the photomicrograph in FIG. 10. Torsion tests of the modified construction of FIG.
  • the above-mentioned nickel-content S.A.E. 4600 iron alloy powder has the following composition:
  • the nickel-free high-performance iron alloy powder also mentioned above has the following composition:
  • Heat treatment of the composite bushing 10 or is carried out in the usual and customary manner.
  • iron as used herein includes iron having carbon therein for controlling the hardness desired,'as achieved by such heat treatment. It also includes carburization for providing a hardened external surface, such as by case hardening.
  • FIG. 11 shows a composite high-strength bushing, generally designated III), as consisting of a reversal of the components shown in FIG. 4, namely as composed of an iron outer sleeve I12 joined at an approximately conical or tapered interface 114 to a high performance alloy inner sleeve 1116 with opposite flat annular end surfaces 118 and 120.
  • the sleeves 112 and 116 are formed from sintered powdered iron and high perfor mance alloy outer and inner components shaped like the components 16 and 18 (FIG. 3) according to the procedure described above for producing the composite high-strength bushing of FIGS. 1 to 4 inclusive shown in the flow chart or diagram of FIG. 5. Accordingly, it is believed that no further explanation is needed.
  • the composite bushing 10 of FIG. 4 is suitable for the inner race ofa roller bearing, whereas the composite bushing 110 is suitable for the outer race thereof, with conventional cylindrical rollers disposed in the annular space therebetween.
  • the modified composite bushing 110 is suitable for use as a high performance plain sleeve bearing for rotatably supporting a shaft (not shown) in its bore 122 while its outer cylindrical surface 124 is mounted in the usual counterbore or seat in the machine frame or other supporting structure (not shown).
  • a composite high-strength bushing comprising an inner sleeve of a base sintered powdered metallic material having a tapered external surface thereon. and an outer sleeve of a high-strength powdered metallic material having an internal bore tapered correspondingly to said tapered external surface and fusibly joined thereto in snugly-fitting telescoped mating engagement with said tapered external surface at a substantially frusto-conical interface therebetween, minute portions of one of said metallic materials extending irregularly past minute portions of the other of said metallic materials across said interface into interlocking engagement with one another in anintermediate zone encircling said. in terface and containing the thus intermingled metallic materials, said base material being iron and said high-strength material being a manganese'molybdenum iron alloy.
  • a composite high-strength bushing according to claim 1, wherein said high-strength material is a nickelcontent manganese-molybdenum iron alloy.
  • a composite high-strength bushing according to claim ll, wherein said high-strength material is a nickel free manganese-molybdenum iron alloy.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Forging (AREA)
  • Powder Metallurgy (AREA)
US00152862A 1971-06-14 1971-06-14 Composite high strength machine element and method of making the same Expired - Lifetime US3762881A (en)

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US (1) US3762881A (de)
AU (1) AU470940B2 (de)
BE (1) BE784780A (de)
BR (1) BR7203817D0 (de)
CA (1) CA967211A (de)
DE (1) DE2228795A1 (de)
ES (1) ES403093A1 (de)
FR (1) FR2142409A5 (de)
GB (1) GB1364780A (de)
IT (1) IT966729B (de)
SE (1) SE388376B (de)

Cited By (17)

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FR2253942A1 (de) * 1973-12-10 1975-07-04 Skf Ind Trading & Dev
US4168862A (en) * 1978-01-05 1979-09-25 Langfield Edward R Wear or thrust plates for hydraulic rock splitting apparatus
US4249993A (en) * 1978-06-23 1981-02-10 Dominion Engineering Works Limited Adjustable bearing system for paper machine
US4654951A (en) * 1980-04-04 1987-04-07 Hughes Aircraft Company Method of assembling extreme pressure belted structures
US4721598A (en) * 1987-02-06 1988-01-26 The Timken Company Powder metal composite and method of its manufacture
US4939827A (en) * 1987-10-20 1990-07-10 Diado Metal Company Ltd. Method of manufacturing a bearing device including a housing with a flange at one end thereof and a bearing bush press-fitted thereinto
US5941651A (en) * 1994-06-10 1999-08-24 Di Serio; Thomas Process for the fabrication of parts made of cast alloys with reinforcement zones
US6148685A (en) * 1995-12-15 2000-11-21 Zenith Sintered Products, Inc. Duplex sprocket/gear construction and method of making same
US6238806B1 (en) * 2000-05-09 2001-05-29 The Japan Steel Works, Ltd. Clad steel pipe
US6266183B1 (en) * 2000-09-18 2001-07-24 Veeco Instruments Inc. Self-centering crash protection mechanism for interference microscope objective
US6626576B1 (en) 2000-02-02 2003-09-30 Gkn Sinter Metals, Inc. Duplex powder metal bearing caps and method of making them
US20070261514A1 (en) * 2006-04-13 2007-11-15 Geiman Timothy E Multi-material connecting rod
US20080212911A1 (en) * 2005-05-18 2008-09-04 Schaeffler Kg Antifriction Bearing Rage, Particularly For Highly Stressed Antifriction Bearings in Aircraft Power Units and Methods For the Production Thereof
US20100026107A1 (en) * 2008-07-30 2010-02-04 Hitachi Kodki Co., Ltd. Power tool
CN102979813A (zh) * 2012-11-22 2013-03-20 上海斐赛轴承科技有限公司 带有绝缘套圈的绝缘轴承及制作方法
US10563695B2 (en) 2017-04-14 2020-02-18 Tenneco Inc. Multi-layered sintered bushings and bearings
CN111964856A (zh) * 2020-07-16 2020-11-20 芜湖天航装备技术有限公司 一种用于航空发射装置振动试验的专用销轴及其使用方法

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3116424A1 (de) * 1981-04-24 1982-11-11 Hilti AG, 9494 Schaan Duebel
DE3539447A1 (de) * 1985-11-07 1987-05-21 Uni Cardan Ag Kraftuebertragungswelle
DE102007025239B4 (de) * 2007-05-31 2011-08-25 S.O.B. Co., Ltd. Verfahren zur Herstellung eines Gleitlagers

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2253942A1 (de) * 1973-12-10 1975-07-04 Skf Ind Trading & Dev
US4168862A (en) * 1978-01-05 1979-09-25 Langfield Edward R Wear or thrust plates for hydraulic rock splitting apparatus
US4249993A (en) * 1978-06-23 1981-02-10 Dominion Engineering Works Limited Adjustable bearing system for paper machine
US4654951A (en) * 1980-04-04 1987-04-07 Hughes Aircraft Company Method of assembling extreme pressure belted structures
US4721598A (en) * 1987-02-06 1988-01-26 The Timken Company Powder metal composite and method of its manufacture
US4939827A (en) * 1987-10-20 1990-07-10 Diado Metal Company Ltd. Method of manufacturing a bearing device including a housing with a flange at one end thereof and a bearing bush press-fitted thereinto
US5941651A (en) * 1994-06-10 1999-08-24 Di Serio; Thomas Process for the fabrication of parts made of cast alloys with reinforcement zones
US6148685A (en) * 1995-12-15 2000-11-21 Zenith Sintered Products, Inc. Duplex sprocket/gear construction and method of making same
US6626576B1 (en) 2000-02-02 2003-09-30 Gkn Sinter Metals, Inc. Duplex powder metal bearing caps and method of making them
US6238806B1 (en) * 2000-05-09 2001-05-29 The Japan Steel Works, Ltd. Clad steel pipe
US6266183B1 (en) * 2000-09-18 2001-07-24 Veeco Instruments Inc. Self-centering crash protection mechanism for interference microscope objective
US20080212911A1 (en) * 2005-05-18 2008-09-04 Schaeffler Kg Antifriction Bearing Rage, Particularly For Highly Stressed Antifriction Bearings in Aircraft Power Units and Methods For the Production Thereof
US7857518B2 (en) * 2005-05-18 2010-12-28 Schaeffler Kg Antifriction bearing race, particularly for highly stressed antifriction bearings in aircraft power units
US20070261514A1 (en) * 2006-04-13 2007-11-15 Geiman Timothy E Multi-material connecting rod
US20100026107A1 (en) * 2008-07-30 2010-02-04 Hitachi Kodki Co., Ltd. Power tool
US8381835B2 (en) * 2008-07-30 2013-02-26 Hitachi Koki Co., Ltd. Power tool
CN102979813A (zh) * 2012-11-22 2013-03-20 上海斐赛轴承科技有限公司 带有绝缘套圈的绝缘轴承及制作方法
US10563695B2 (en) 2017-04-14 2020-02-18 Tenneco Inc. Multi-layered sintered bushings and bearings
CN111964856A (zh) * 2020-07-16 2020-11-20 芜湖天航装备技术有限公司 一种用于航空发射装置振动试验的专用销轴及其使用方法

Also Published As

Publication number Publication date
AU470940B2 (en) 1976-04-01
ES403093A1 (es) 1975-04-16
SE388376B (sv) 1976-10-04
CA967211A (en) 1975-05-06
FR2142409A5 (de) 1973-01-26
IT966729B (it) 1974-02-20
DE2228795A1 (de) 1972-12-21
GB1364780A (en) 1974-08-29
BE784780A (fr) 1972-10-02
AU4211472A (en) 1973-11-15
BR7203817D0 (pt) 1973-07-17

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