ZA200610348B - Sintered metal parts and method for the manufacturing thereof - Google Patents
Sintered metal parts and method for the manufacturing thereof Download PDFInfo
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- ZA200610348B ZA200610348B ZA200610348A ZA200610348A ZA200610348B ZA 200610348 B ZA200610348 B ZA 200610348B ZA 200610348 A ZA200610348 A ZA 200610348A ZA 200610348 A ZA200610348 A ZA 200610348A ZA 200610348 B ZA200610348 B ZA 200610348B
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- ZA
- South Africa
- Prior art keywords
- powder
- sintered
- mpa
- powder metallurgical
- parts
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims description 16
- 229910052751 metal Inorganic materials 0.000 title claims description 4
- 239000002184 metal Substances 0.000 title claims description 4
- 238000004519 manufacturing process Methods 0.000 title claims description 3
- 239000000843 powder Substances 0.000 claims description 38
- 238000005480 shot peening Methods 0.000 claims description 19
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 16
- 238000005452 bending Methods 0.000 claims description 15
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 11
- 229910052804 chromium Inorganic materials 0.000 claims description 9
- 239000011651 chromium Substances 0.000 claims description 9
- 238000005245 sintering Methods 0.000 claims description 9
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 7
- 229910052750 molybdenum Inorganic materials 0.000 claims description 7
- 239000011733 molybdenum Substances 0.000 claims description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 6
- 229910000734 martensite Inorganic materials 0.000 claims description 6
- 229910002804 graphite Inorganic materials 0.000 claims description 5
- 239000010439 graphite Substances 0.000 claims description 5
- 239000000203 mixture Substances 0.000 claims description 5
- 229910052742 iron Inorganic materials 0.000 claims description 3
- 238000005496 tempering Methods 0.000 claims description 3
- 101000800807 Homo sapiens Tumor necrosis factor alpha-induced protein 8 Proteins 0.000 claims 1
- 102100033649 Tumor necrosis factor alpha-induced protein 8 Human genes 0.000 claims 1
- 239000000463 material Substances 0.000 description 20
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 15
- 229910052799 carbon Inorganic materials 0.000 description 14
- 229910052759 nickel Inorganic materials 0.000 description 8
- 238000005056 compaction Methods 0.000 description 7
- 238000001816 cooling Methods 0.000 description 7
- 239000011148 porous material Substances 0.000 description 6
- 229910001563 bainite Inorganic materials 0.000 description 5
- 229910000831 Steel Inorganic materials 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 238000009661 fatigue test Methods 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 150000001247 metal acetylides Chemical class 0.000 description 2
- 229910001562 pearlite Inorganic materials 0.000 description 2
- 238000004663 powder metallurgy Methods 0.000 description 2
- 239000000047 product Substances 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 206010020751 Hypersensitivity Diseases 0.000 description 1
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 1
- 230000002730 additional effect Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 229910001567 cementite Inorganic materials 0.000 description 1
- 229910052729 chemical element Inorganic materials 0.000 description 1
- 229940000425 combination drug Drugs 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 238000000280 densification Methods 0.000 description 1
- 238000010410 dusting Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- KSOKAHYVTMZFBJ-UHFFFAOYSA-N iron;methane Chemical compound C.[Fe].[Fe].[Fe] KSOKAHYVTMZFBJ-UHFFFAOYSA-N 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000011572 manganese Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 229910000859 α-Fe Inorganic materials 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C33/00—Making ferrous alloys
- C22C33/02—Making ferrous alloys by powder metallurgy
- C22C33/0257—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C33/00—Making ferrous alloys
- C22C33/02—Making ferrous alloys by powder metallurgy
- C22C33/0207—Using a mixture of prealloyed powders or a master alloy
- C22C33/0228—Using a mixture of prealloyed powders or a master alloy comprising other non-metallic compounds or more than 5% of graphite
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/16—Both compacting and sintering in successive or repeated steps
- B22F3/164—Partial deformation or calibration
- B22F2003/166—Surface calibration, blasting, burnishing, sizing, coining
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
Description
v WO 2005/120749 PCT/SE2005/000908
SINTERED METAL PARTS AND METHOD FOR THE MANUFACTURINS
THEREOF
The present invention refers to powder metallurgy and 5 more specifically to pre-alloyed chromium powder metal parts with improved fatigue properties.
In general, sintered products made by powder metallurgy are advantageous in cost over ingot steels obtained through forging and rolling steps and has wide utility as parts in e.g. motor vehicles. However, the sintered prod- uct has pores which are inevitably formed during the course of its fabrication. These remaining pores of the sintered powder-metallurgical materials impair the me- chanical properties of the materials, as compared with completely dense materials. This is a result of the pores acting as stress concentrations and also because the pores reduce the effective volume under stress. Thus, strength, ductility, fatigue strength, macro-hardness etc. in iron-based powder-metallurgical materials de- crease as the porosity increases.
Despite their comparatively low fatigue strength , iron- based powder-metallurgical materials are, to a certain . extent, used in components requiring high fatigue strength. Distaloy® HP, available from Hogands AB®, Swe- den, is a steel powder possible for use in high perform- ing purposes. In this Distaloy® powder the base-powder is alloyed with nickel, which is an expensive alloying ele- ment. This high performing material is therefore rather costly and there is a need for less expensive materials, which have at least as good fatigue strength.
NY
One route to improve the fatigue performance of powder metallurgical steels are secondary operations. Through hardening, case hardening or shot peening {or a combina- tion) are possible processes to get highest possible fa- tigue resistance of a component. Shot peening is normally performed in order to utilize the beneficial influence of compressive residual stresses in the surface. Pores open to the surface are weak points in powder metallurgical materials. These pores are at least partly neutralized by introduction of surface compression residual stresses.
Shot peening of compacted parts is disclosed in e.g. the
US patent 6 171 546. According to this patent the shot peening is followed by a final sintering step. An iron- based powder containing i. a. nickel is used as starting material. As indicated above there is an increasing de- mand for powders, which do not contain nickel, as nickel is expensive. Other disadvantages with nickel containing powders are dusting problems which may occur during the processing of the powder, and which may cause allergic reactions also in minor amounts. The use of nickel should thus be avoided. Also the US patent application 2004/0177719 relates to a method including shot peening.
More specifically, this application discloses a method, wherein a portion of the surface of a compacted part is subjected to shot peening after sintering. According to this application a densifying process involving powder forging or sizing is necessary in order improve the prop- erties of the final compacted part.
An object of the present invention is to provide a cost effective process for the preparation of powder metallur- gical components with high fatigue strength without any steps for achieving core densification. Another object is to provide a process involving powder materials, which are free from nickel.
I+ has unexpectedly been found that components having high fatigue strength can be obtained by shot peening of sintered components prepared from iron based powders dis- tinguished by low levels of chromium and molybdenum.
The powders used in the present invention are pre-alloyed iron-base powders comprising low amounts of chromium and molybdenum. A preferred amount is 1.3-3.5% by weight of chromium and 0.15-0.7% by weight of molybdenum. The pow- der may also contain small amounts, 0.09 to 0.3% by weight, of manganese and inevitable impurities. Such pow- ders are known from the US patent 6 348 080 and WO 03/106079. 70 The base powder is further mixed with graphite to obtain the desired strength in the material. The amount of graphite which is mixed with the iron-base powder is 0.1- 1.0%, preferably 0.15-0.85%. The powder mixture is com- pacted in a die to produce a green body. The compaction pressure is at least 600 MPa, preferably at least 700 MPa and more preferably 800 MPa. The compaction can be per- formed by cold compaction or warm compaction. After the compaction the obtained green part is sintered at a sin- tering temperature above 1100°c, preferably above 1220°C.
The sintering atmosphere is preferably a mix of nitrogen and hydrogen. A normal cooling rate in the sintering process is 0.8°C/s, a range between 0.5°C/s and 1.0°C/s is preferred. The sintered density is preferably above 7.15 g/cm’, more preferably above 7.3 g/cm®. The obtained microstructure in the as-sinterd material is mainly fine- pearlitic with a lower chromium and molybdenum content and martensitic or lower bainitic for slightly higher chromium and molybdenum content.
Tt has now unexpectedly been found that a remarkable in- crease in the bending fatigue limit can be obtained by shot peening the sintered low chromium powder materials.
Especially remarkable increase is obtained for notched parts, where an increase of more than 50% and even more than 70% can be obtained as can be seen from the follow- ing examples. The degree of shot peening as defined by
Almen A intensity, is preferably between 0.20 and 0.37 mm.
Secondary operations e.g. through hardening and case hardening, can be performed pefore the shot peering in order to improve the properties even more. Thus, after through hardening followed by tempering the material is mainly martensitic and the fatigue limit is raised by shotpeening. The martensite in the surface which is formed during case hardening is believed to form compres- sive stresses, which is beneficial for the fatigue limit.
Sinterhardening is an alternative process which is ap- plied in the sintering process. Sinterhardening uses forced cooling at the end of the sintering process of the components which results in a hardened structure.
The fatigue tests have been performed on notched specimen with a stress concentration factor, Ke, of 1.38 and on un-notched specimen. The tests show a greater increase in bending fatigue limit when shot peening notched specimen than when the shot peening is performed on un-notched specimen. The expression “notched” in this context refers to a specimen or component having a stress concentration factor above 1.3.
The invention is illustrated by the following non- limiting examples.
Example 1 5 Two pre-alloyed base-powders, Astaloy® Crl and Astaloy®
CrM, and one diffusion-alloyed base powder, Distaloy® HP, are included in the study. Distaloy® HP is diffusion- alloyed with Ni and Cu and pre-alloyed with Mo. The three materials included in this study are shown in Table 1.
Table 1 mstatoyorn| | loo = Tas hstaloy ce] | los [30 oistaloyaple.o Jz0 1s
Detailed information on process parameters, density and carbon levels will be given below. In table 2 plane bend- ing fatigue performance of un-notched specimen is shown for different alloys which are sintered 30 min in 90/10
N,/H, with cooling rate about 0.8C/sec. Fatigue tests on un-notched specimens are performed using 5 mm ISO03928 samples with chamfered edges. The tests are made in four- point plane bending at load ratio R=-1. The staircase method is used with 13 - 18 samples in the staircase and 2 million cycles as run-out limit. Evaluation of the staircase (50% probability fatigue limit and standard de- viation) is made according to the MPIF 56 standard. Test frequency is 27 - 30 Hz.
Table 2
Powder Density Carbon Oa, son | Std Dev | Oa, 0 ra eter | can [ome | tar
SIE EE
AotaloyCrM | 7.06 | 0.35 | 284 | 7.0 | 274 —50a | __ 0.56 | 316 | 8.4 | 300
Sistaloy BF [7.13 | 0.65 | 2905 | 22.5 | 261]
EST SF ww 5 CN 1 AM E XV
The microstructure of Astaloy CrL with sintered carbon below 0.6% and cooling rate about 0.8°C/s is upper bain- ite. Increased carbon above 0.74% changes the microstruc- ture to fine pearlite.
Microstructure analysis of 1120°C sintered Astaloy CrM materials and cooling rate 0.8°C/s and with sintered car- bon levels between 0.32% and 0.49% show a dense upper bainitic microstructure. Dense upper bainite has the same characteristics as regular upper bainite, i.e. an irrequ- lar mix of ferrite and cementite. The differences are the smaller distances between carbides and sizes of the car- bides. Increased sintered carbon shifts the microstruc- ture to a mix of martensite and lower bainite.
Table 3 shows influence of compaction pressure and carbon level for cold compacted Astaloy CrL. All materials were sintered at 1120°C for 30 min. in 90/10 Nz/Hz. In table 3 a summary of plane bending fatigue performance of Astaloy
CrL at two compaction pressures and two levels of addi- tional graphite. Std.dev. <5 indicates that the scatter is small and the MPIF standard 56 evaluation of standard deviation cannot be applied. The specimen in table 3 are un-notched.
Table 3
Material Graphite | Compacting Density | Carbon | Oa, sos std Oa, 50
C-UF4 Pressure As-sint As- Dev [%) [MPa] (g/cm?! | sint | [MPa] | [MPa] | [MPa] (%] sstaToyerc 06 | 600 | 6,94 | 0,56 | 2d [31.6 1 205
Ti20%, [58 600 | 6,03 | 0,75 | 233 | 9.5 1 218
Somin, gg | 800 | 7.13 | 0,565 | 236 | 8.5 [ 222
Gace
Influence of sintering temperature on the fatigue per- formance with un-notched specimen is shown in Table 4.
The microstructures of the materials in table 4 are char- acterized by mainly upper bainite (1120°C €.58%C) and fine pearlite (1120°C, 0.773%C and 1250°C, 0.74%C).
Table 4
Powder Sint. Density | Carbon Op, 50% Stdbev On, aos temp As-Sint | As-Sint | [MPal [MPa] [MPa] (g/cm’] [8]
AstaloyCrL] 1120°C 203 1120° 1250°C
Example 2 : :
Influence of shot peening and the combination of heat treatment and shot peening has been investigated on Asta- loy CrlL 3 mm edge-notched specimens. The notch is in- cluded in the press tool and no machining is performed.
The stress concentration factor in bending is obtained by
FEM to K=1.38. Test frequency is 27-30 Hz.
The materials are sintered at 1280°C for 30 min in Hz.
Cooling rate is 0.8°C/s.
The shot peening is performed to obtain an Almen A inten- sity of 0.32 mm.
Estimated plane bending fatigue performance of as sin- tered and as-sintered plus shot peened samples is shown in table 5.
Table 5
Powder Carbon | Density Secondary op- Bending Fa- Increase
As-Sint |As-Sint eration tigue Limit | after shot
AstaloyCrL| 0.70 | 7.30 wo | 235 notched ves | 420 | +79% |]
AstaloyCrL| 0.85 730 [we un-notched yes [aso | +32%
In table 6 an estimated plane bending fatigue performance of through hardened tempered and shot peened samples is shown. Through hardening is performed with an austeniti- zation temperature at 880°C. The cooling rate after aus- tenitization is made at 8°C/s. Finally the specimen are tempered at 250°C for 1 hour .
Table 6
Powder Carbon | Density Secondary operations Bending | Increase
As- |As-Sint Fatigue| after 1 : 3 Lp ! aro (g/en’] Through |Tempering| Shot prvi shot rardening | 250°C 1h |peening| [MFal | peening
EE Em notch [0.50 | 7.30 | wes | wes | wes | 450 [| +73%
EE EP 3 a un-notch
From the tables 5 and 6 it can be found that by shot peening the materials containing chromium and molybdenum a great increase of the bending fatigue limit is achieved.
Claims (12)
1. A method for producing powder metallurgical parts with improved fatigue strength comprising the steps of: - providing a pre-alloyed iron-based metal powder comprising at least 1.3-3.5% by weight of chromium, 0.15-0.7% by weight of molybdenum, - mixing said powder with 0.1-1.0% by weight of graphite, - compacting the obtained mixture at a pressure of at least 600 MPa, - sintering the compacted part in a single step at a temperature above 1100°C, and - shot-peening the part.
2. The method according to claim 1 wherein the increase of the fatigue strength is at least 50%.
3. The method according to claim 1 or 2, wherein the compacted and sintered part is subjected to hardening and tempering prior to shot peening.
4, The powder metallurgical part manufactured according to any one of the claims 1-3 having a mainly pearlitic microstructure.
5. The powder metallurgical part manufactured according to any one of the claims 1-3 having a mainly fine pearlitic microstructure.
6. The powder metallurgical part manufactured according to any one of the claims 1-3 having a martensitic and lower bainitic microstructure. .mcNDED SHEET 2008 0+ 23
7. The powder metallurgical part manufactured according to any one of the claim 1-3 having a mainly tempered martensitic microstructure.
8. The powder metallurgical part according to any one of the claims 4-7, having a bending fatigue limit of at least 340 MPa at a sintered density of 7.15 glcm?®.
9. The powder metallurgical part according to any one of the claims 4-7, having a bending fatigue limit of at least 400 MPa at a sintered density of 7.3 g/cm.
10. Use of a low chromium prealloyed powder for preparing notched sintered parts having a bending fatigue limit of at least 340 MPa at a sintered density of 7.15 g/lcm®, wherein said powder is compacted, sintered and optionally tempered and annealed and is subjected to shot peening.
11. Use of a low chromium prealloyed powder for preparing notched sintered parts according to claim 10 wherein said parts have a bending fatigue limit of at least 400 MPa at a sintered density of 7.3 g/cm’.
12. Use of the powder metallurgical part according to claim 10, wherein said parts have a stress concentration factor above 1.3. 2 « w+NDED SHEET 2008 -01- 23
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SE0401535A SE0401535D0 (en) | 2004-06-14 | 2004-06-14 | Sintered metal parts and method of manufacturing thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| ZA200610348B true ZA200610348B (en) | 2008-06-25 |
Family
ID=32710055
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| ZA200610348A ZA200610348B (en) | 2004-06-14 | 2005-06-13 | Sintered metal parts and method for the manufacturing thereof |
Country Status (13)
| Country | Link |
|---|---|
| EP (1) | EP1771268A1 (en) |
| JP (1) | JP4825200B2 (en) |
| CN (1) | CN100475389C (en) |
| AU (1) | AU2005252150B2 (en) |
| BR (1) | BRPI0512041A (en) |
| CA (1) | CA2570236A1 (en) |
| MX (1) | MXPA06014234A (en) |
| RU (1) | RU2345867C2 (en) |
| SE (1) | SE0401535D0 (en) |
| TW (1) | TWI290073B (en) |
| UA (1) | UA85245C2 (en) |
| WO (1) | WO2005120749A1 (en) |
| ZA (1) | ZA200610348B (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4789837B2 (en) | 2007-03-22 | 2011-10-12 | トヨタ自動車株式会社 | Iron-based sintered body and manufacturing method thereof |
| AT505699B1 (en) | 2007-09-03 | 2010-10-15 | Miba Sinter Austria Gmbh | METHOD FOR PRODUCING A SINTERED CERTAIN COMPONENT |
| RU2454473C1 (en) * | 2010-12-03 | 2012-06-27 | Общество с ограниченной ответственностью "Научно-производственное предприятие Вакууммаш" | Worn-out seal of turbomachine |
| RU2455116C1 (en) * | 2010-12-03 | 2012-07-10 | Общество с Ограниченной Ответственностью "Научно-производственное предприятие "Вакууммаш" | Abrasive turbine gland element |
| CA2823267C (en) * | 2010-12-30 | 2019-07-02 | Anna Larsson | Iron based powders for powder injection molding |
| CN104039484B (en) * | 2012-01-05 | 2016-12-07 | 霍加纳斯股份有限公司 | Metal dust and application thereof |
| JP5636605B2 (en) * | 2012-10-15 | 2014-12-10 | 住友電工焼結合金株式会社 | Method for manufacturing sintered parts |
| CN103008648B (en) * | 2012-12-28 | 2015-04-15 | 杭州东华链条集团有限公司 | Novel manufacturing method of maintenance-free chain |
| DE102013212528A1 (en) | 2013-06-27 | 2014-12-31 | Robert Bosch Gmbh | Process for producing a steel shaped body |
| RU2588979C1 (en) * | 2015-03-16 | 2016-07-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Кубанский государственный технологический университет" (ФГБОУ ВПО "КубГТУ") | Method of producing high-density powder chromium containing material based on iron |
| CA3017996C (en) * | 2016-03-23 | 2023-11-21 | Hoganas Ab (Publ) | Iron based powder |
| JP6431012B2 (en) * | 2016-09-16 | 2018-11-28 | トヨタ自動車株式会社 | Method for producing wear-resistant iron-based sintered alloy and wear-resistant iron-based sintered alloy |
| RU2703669C1 (en) * | 2018-10-16 | 2019-10-21 | Общество с ограниченной ответственностью Научно-технический центр "Уралавиаспецтехнология" | Abradable insert of turbine seal |
| US11668298B2 (en) | 2018-11-07 | 2023-06-06 | Hyundai Motor Company | Slide of variable oil pump for vehicle and method of manufacturing the same |
| BR112022006038A2 (en) | 2019-10-17 | 2022-07-12 | Nippon Sheet Glass Co Ltd | BODY OF GLASS |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03130349A (en) | 1989-06-24 | 1991-06-04 | Sumitomo Electric Ind Ltd | Ferrous sintered parts material excellent in fatigue strength and its production |
| US5512236A (en) * | 1992-12-21 | 1996-04-30 | Stackpole Limited | Sintered coining process |
| JPH07505679A (en) * | 1992-12-21 | 1995-06-22 | スタックポール リミテッド | Bearing manufacturing method |
| JP3346139B2 (en) * | 1995-12-28 | 2002-11-18 | 三菱マテリアル株式会社 | Iron-based sintered alloy connecting rod with a mechanically fractured surface between the rod and cap |
| SE9602376D0 (en) * | 1996-06-14 | 1996-06-14 | Hoeganaes Ab | Compact body |
| SE9800154D0 (en) * | 1998-01-21 | 1998-01-21 | Hoeganaes Ab | Steel powder for the preparation of sintered products |
| JP3736838B2 (en) * | 2000-11-30 | 2006-01-18 | 日立粉末冶金株式会社 | Mechanical fuse and manufacturing method thereof |
| SE0201824D0 (en) * | 2002-06-14 | 2002-06-14 | Hoeganaes Ab | Pre-alloyed iron based powder |
| JP2004115868A (en) * | 2002-09-26 | 2004-04-15 | Toyota Motor Corp | Method for manufacturing sintered member |
| US7416696B2 (en) | 2003-10-03 | 2008-08-26 | Keystone Investment Corporation | Powder metal materials and parts and methods of making the same |
-
2004
- 2004-06-14 SE SE0401535A patent/SE0401535D0/en unknown
-
2005
- 2005-06-13 RU RU2007101313/02A patent/RU2345867C2/en not_active IP Right Cessation
- 2005-06-13 ZA ZA200610348A patent/ZA200610348B/en unknown
- 2005-06-13 EP EP05752520A patent/EP1771268A1/en not_active Withdrawn
- 2005-06-13 CA CA002570236A patent/CA2570236A1/en not_active Abandoned
- 2005-06-13 MX MXPA06014234A patent/MXPA06014234A/en active IP Right Grant
- 2005-06-13 UA UAA200700314A patent/UA85245C2/en unknown
- 2005-06-13 BR BRPI0512041-1A patent/BRPI0512041A/en not_active Application Discontinuation
- 2005-06-13 CN CNB2005800193408A patent/CN100475389C/en not_active Expired - Fee Related
- 2005-06-13 WO PCT/SE2005/000908 patent/WO2005120749A1/en active Application Filing
- 2005-06-13 JP JP2007516433A patent/JP4825200B2/en not_active Expired - Fee Related
- 2005-06-13 AU AU2005252150A patent/AU2005252150B2/en not_active Ceased
- 2005-06-14 TW TW94119717A patent/TWI290073B/en not_active IP Right Cessation
Also Published As
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|---|---|
| BRPI0512041A (en) | 2008-02-06 |
| JP4825200B2 (en) | 2011-11-30 |
| AU2005252150B2 (en) | 2009-01-08 |
| JP2008502803A (en) | 2008-01-31 |
| MXPA06014234A (en) | 2007-02-14 |
| CA2570236A1 (en) | 2005-12-22 |
| CN1968775A (en) | 2007-05-23 |
| EP1771268A1 (en) | 2007-04-11 |
| RU2007101313A (en) | 2008-08-10 |
| CN100475389C (en) | 2009-04-08 |
| TWI290073B (en) | 2007-11-21 |
| TW200610599A (en) | 2006-04-01 |
| RU2345867C2 (en) | 2009-02-10 |
| SE0401535D0 (en) | 2004-06-14 |
| UA85245C2 (en) | 2009-01-12 |
| WO2005120749A1 (en) | 2005-12-22 |
| AU2005252150A1 (en) | 2005-12-22 |
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