EP0207697A1 - Acier moulé inoxydable et procédé pour sa fabrication - Google Patents
Acier moulé inoxydable et procédé pour sa fabrication Download PDFInfo
- Publication number
- EP0207697A1 EP0207697A1 EP86304758A EP86304758A EP0207697A1 EP 0207697 A1 EP0207697 A1 EP 0207697A1 EP 86304758 A EP86304758 A EP 86304758A EP 86304758 A EP86304758 A EP 86304758A EP 0207697 A1 EP0207697 A1 EP 0207697A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- article
- cast
- stainless steel
- balance
- nitrogen
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims description 15
- 238000004519 manufacturing process Methods 0.000 title claims description 4
- 229910001256 stainless steel alloy Inorganic materials 0.000 title description 8
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 42
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 29
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 25
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 22
- 229910001220 stainless steel Inorganic materials 0.000 claims description 26
- 239000010935 stainless steel Substances 0.000 claims description 23
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 14
- 239000000203 mixture Substances 0.000 claims description 14
- 239000011651 chromium Substances 0.000 claims description 13
- 239000010955 niobium Substances 0.000 claims description 13
- 229910052804 chromium Inorganic materials 0.000 claims description 12
- 229910000859 α-Fe Inorganic materials 0.000 claims description 12
- 229910000831 Steel Inorganic materials 0.000 claims description 11
- 229910001566 austenite Inorganic materials 0.000 claims description 11
- 239000010959 steel Substances 0.000 claims description 11
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 10
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 10
- 229910052799 carbon Inorganic materials 0.000 claims description 9
- 238000005728 strengthening Methods 0.000 claims description 9
- 229910052748 manganese Inorganic materials 0.000 claims description 8
- 239000011572 manganese Substances 0.000 claims description 8
- 229910052750 molybdenum Inorganic materials 0.000 claims description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 7
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 7
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 claims description 7
- 239000005864 Sulphur Substances 0.000 claims description 7
- 229910052742 iron Inorganic materials 0.000 claims description 7
- 239000011733 molybdenum Substances 0.000 claims description 7
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 5
- 229910052710 silicon Inorganic materials 0.000 claims description 4
- 239000010703 silicon Substances 0.000 claims description 3
- 229910000851 Alloy steel Inorganic materials 0.000 claims description 2
- UCKMPCXJQFINFW-UHFFFAOYSA-N Sulphide Chemical compound [S-2] UCKMPCXJQFINFW-UHFFFAOYSA-N 0.000 claims description 2
- 239000012535 impurity Substances 0.000 claims description 2
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 claims description 2
- 239000000155 melt Substances 0.000 claims description 2
- 238000002844 melting Methods 0.000 claims description 2
- 230000008018 melting Effects 0.000 claims description 2
- 238000005266 casting Methods 0.000 abstract description 27
- 238000004227 thermal cracking Methods 0.000 abstract description 9
- 229910052751 metal Inorganic materials 0.000 abstract description 6
- 239000002184 metal Substances 0.000 abstract description 6
- 229910001141 Ductile iron Inorganic materials 0.000 abstract description 3
- 229910001060 Gray iron Inorganic materials 0.000 abstract description 3
- 125000004122 cyclic group Chemical group 0.000 abstract description 2
- 229910001039 duplex stainless steel Inorganic materials 0.000 abstract description 2
- 229910045601 alloy Inorganic materials 0.000 description 39
- 239000000956 alloy Substances 0.000 description 39
- 239000000243 solution Substances 0.000 description 14
- 238000012360 testing method Methods 0.000 description 14
- 239000000463 material Substances 0.000 description 7
- 239000000470 constituent Substances 0.000 description 5
- 239000007789 gas Substances 0.000 description 5
- 238000007792 addition Methods 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000011960 computer-aided design Methods 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 230000004580 weight loss Effects 0.000 description 2
- 229910000967 As alloy Inorganic materials 0.000 description 1
- 229910001208 Crucible steel Inorganic materials 0.000 description 1
- RZJQYRCNDBMIAG-UHFFFAOYSA-N [Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Zn].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn] Chemical class [Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Cu].[Zn].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Ag].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn].[Sn] RZJQYRCNDBMIAG-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- BIJOYKCOMBZXAE-UHFFFAOYSA-N chromium iron nickel Chemical compound [Cr].[Fe].[Ni] BIJOYKCOMBZXAE-UHFFFAOYSA-N 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000001351 cycling effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000007572 expansion measurement Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 229910017464 nitrogen compound Inorganic materials 0.000 description 1
- 150000002830 nitrogen compounds Chemical class 0.000 description 1
- QJGQUHMNIGDVPM-UHFFFAOYSA-N nitrogen group Chemical group [N] QJGQUHMNIGDVPM-UHFFFAOYSA-N 0.000 description 1
- 229910052698 phosphorus Inorganic materials 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 229910052715 tantalum Inorganic materials 0.000 description 1
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000005382 thermal cycling Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/60—Ferrous alloys, e.g. steel alloys containing lead, selenium, tellurium, or antimony, or more than 0.04% by weight of sulfur
Definitions
- the present invention relates to relatively low-cost stainless steel alloys used for casting applications, e.g. turbine and turbocharger housings, exhaust manifolds, combustion chambers, etc. having satisfactory corrosion resistance and other properties at room and elevated temperatures in the operating range up to 2000°F (1093°C).
- Cast articles of this type in particular, automotive or aircraft turbocharger housings, are subject to elevated operating temperatures up to about 2000 °F (1093°C), and must be able to contain a turbine wheel generating very high rotational speeds.
- the temperature reaches 1300-1400°F (704-760°C) resulting in housing metal temperatures of 1200-1300°F (649-74°C).
- the operating temperatures extend up to the 1750-2000°F (954-1909 0 C) range, which results in metal temperatures of 1550-1950°F (843-1066°C) at the gas inlet or tongue section of the turbocharger housing since this inlet area is within a few degrees of the turbine exhaust temperature and is insulated so that heat is not dissipated rapidly. It is in metal sections such as this gas inlet area of an automotive turbocharger where the exhaust gas initially contacts the turbocharger, that thermal cracking is encountered, unless relatively expensive stainless steel casting alloys are employed.
- the commercially available HD alloy which is inherently a duplex material contains about 26-30% chromium and 4-7% nickel, however, because of the relatively low nickel content, it is subject to sigma phase formation, which becomes very brittle and gives rise to thermal cracking when used at elevated temperatures, particularly when the cast material is subjected to thermal cycling.
- a stainless steel casting alloy of higher nickel content such as commercially available high nickel ductile iron casting alloys. Examples of these are NiResist (Trade Mark) developed by International Nickel Company, or HK30, a chromium-nickel-iron stainless steel alloy containing approximately 30% chromium and 20% nickel, balance essentially iron.
- the HK series stainless steel alloys in general have about 18-22% nickel and are fully austenitic.
- the HK stainless steel alloys are some of the strongest stainless steel casting alloys, in terms of creep strength, however, while meeting the high temperature property requirements for turbocharger housings, they are quite expensive and present casting difficulties because of their high nickel content.
- a cast stainless steel article having a duplex metallurgical structure of about 20 - 80% ferrite, the balance being austenite and being substantially devoid of sigma phase, the article comprising essentially in weight percent about 27-31% Chromium, 4-6% Nickel, 0.2-0.5% Nitrogen, 0.2-0.4% Carbon, 0.5-1.5% Columbium, up to 1% Manganese and/or Molybdenum as a sulphide former 0.2-0.4% Sulphur, the balance being Iron, with incidental impurities.
- Such an article may have good resistance to thermal cracking when subjected to cycling between room temperature and a service temperature of 1500-1950°F (816-1066°C) and which, in the solution treated condition, may be resistant to oxidation corrosion, may have a room temperature tensile strength of at least 75.000psi and at least about 7% elongation.
- a duplex stainless steel alloy that is, a two phase alloy having both ferritic and austenitic structure, can be used for cast metal parts subject to high operating temperatures, such as automobile turbocharger housings, gasoline engine exhaust manifolds, and cast furnace or combustion chamber components, thereby combining the high temperature properties of the austenitic phase with the castability and low thermal expansion characteristic of the ferritic phase.
- the article has a Nitrogen content of 0.3-0.4 weight percent.
- the article has a composition including by weight: 27 - 31% Cr, 4 - 6% Ni, 0.2 - 0.4%C, 0.5 - 1.0% Mn, up to 1.0% Mo, 1 - 2% Si, 0.5 - 1.5% Cb (Columbium), 0.3 - 0.4% N up to 0.03 %P, 0.2 - 0.4 %S, up to 0.50% Cu, up to 0.20% A1, the balance being iron.
- the article has a duplex structure of 40 - 60% ferrite, the balance being austenite.
- a preferred composition for the article, by weight may be 31% Chromium, 5% Nickel, 0.24% Carbon, 0.65% Manganese, 1% Silicon, 0.35% Molybdenum, 0.3% Sulphur, 0.9 % Columbium, 0.32% Nitrogen, the balance being Iron.
- a method for producing a cast stainless steel article having a duplex metallurgical structure of about 20 - 80% ferrite, the balance being austenite comprising the steps of: melting a commercial steel mixture to a target chemistry of about 27 - 31% Chromium, 4 - 6% Nickel, 0.2 - 0.4% Carbon, up to 1% Manganese and/or Molybdenum, 0.5 - 1.5% Columbium 0.2 - 0.5% Nitrogen, 0.2 - 0.4% Sulphur; heating the steel alloy mixture to a temperature of about 2850 - 2900°F (1566 - 1593°C) for a time sufficient to homogenise the melt; pouring the steel at a tap temperature of about 2850°F (1566°C) into moulds employing gates designed to minimise porosity; and allowing the article to solidify.
- the method includes subjecting the cast article to a solution treatment at about 2000 - 2200°F (1093 - 1204°C) for 1 - 4 hours or longer to redistribute M 23 c 6 carbide (where "M" is essentially Chromium).
- the method includes the step of removing the gates by snap breaking after the cast article has cooled to room temperature and before the solution treatment.
- the solution treated article is air cooled following the solution treatment and is preferably also subjected to a strengthening treatment at about 1400 - 1600°F (760 - 871°C) for up to 24 hours.
- a preferred stainless steel casting alloy composition for turbine housings is an H-series stainless steel with a relatively low nickel content which is modified with nitrogen to obtain a ferrite/austenite duplex structure having ferrite in the range of 20 - 80%, preferably 40 - 60% ferrite, having improved resistance to thermal cracking.
- the amount of ferrite present in the alloy microstructure is determined by the chemistry of the alloy, the fabrication technique, and the heat treatment employed. It is not believed that the ferritic phase contributes to the high temperature properties of the cast alloy.
- stainless steel castings according to the invention may be brittle and hence some form of solution treatment is preferable.
- the brittleness prior to heat treatment has been found to enhance the steel casting method of the present invention, since the cast steel gating can be designed for gate removal by snapping rather than machine cutting.
- the preferred solution treatment is conducted at 2000 - 2200°F (1093 - 1204°C) for 1 to 4 hours followed by air cooling.
- the alloy may be subjected to a strengthening treatment of 1400 - 1600 °F (760 - 871°C) for up to 24 hours, but since the cast articles encounter temperatures in this temperature range during service, the strengthening treatment may be effected in situ during testing or initial service of the cast articles.
- the primary strengthening mechanism of the stainless steel casting of the present invention is believed to be by carbide dispersion in a solid solution strengthened matrix.
- carbide dispersion in a solid solution strengthened matrix.
- MC carbide where "M” is essentially Cb
- M 23 C 6 carbide constituent is relatively unaffected by solution treatment and hence remains as a strengthening constituent after solution treatment.
- the brittle M 23 C 6 carbide constituent (where "M” is essentially Cr)is spheroidized or partially dissolved during solution treatment.
- This dissolved carbide reprecipitates at the lower temperatures encountered during normal operating conditions and thus enhances the strength of the alloy in service.
- the solution treatment redistributes, i.e. dissolves or spherioidizes the M 23 C 6 carbide, the spheroidized or droplet from of the carbide being more ductile than the original angular form.
- Sulphur is added to the stainless steel casting alloy of the present invention, in an amount of 0.2 - 0.4% to enhance machinability, and is combined with manganese or molybdenum as MnS or MoS.
- Silicon which adds to the fluidity of the cast alloys, is normally present in commercial steels in an amount up to 2%, and 2.5 - 1.5% columbium is added for strengthening since columbium produces the very stable MC carbide. Tantalum may be similarly beneficial for strengthening but is more expensive than columbium.
- Turbine housings were prepared for testing in accordance with the present invention made of the DMS016 alloys shown in Table 1 and the resulting castings had the properties shown in Table II.
- Table I also shows the compositions of the closely related HC, HD and HK series alloys.
- the pouring temperature varied from 2733 - 2770°F (1500 - 1521°C) for twelve (12) ladles poured in connection with the above examples.
- the charge material was a commercial mixture approximating the desired chemistry of the DMS016 alloys in accordance with the invention.
- Figure 1 is a 400X photomicrograph, showing the microstructure of alloy DMS016 modified with 0.16%N, at 400X showing approximately 10% austenite, which is the lighter phase, the darker phase being ferrite.
- the microstructure shown in Figure 2 (0.20%N) contains about 20% austenite
- the microstructure shown in Figure 3 (0.32%N) contains about 40 - 50 % Austenite
- the microstructure shown in Figure 4 having 0.35% N contains about 50 - 55% austenite.
- a particular requirement for a turbocharger housing is that it must contain a wheel burst.
- the containment test is performed to determine whether the turbine housing of the particular alloy will contain a wheel which bursts as the rotating speed is increased in accordance with a particular containment requirement policy.
- Turbocharger manufacturers typically have several burst containment tests, i.e. for auto (gasoline), diesel and aircraft turbochargers. The first two tests are generally similar, while the latter (aircraft) may differ primarily in the use of a mechanically weakened wheel.
- a test of the alloy designated DMS016 2 was run on a containment burst test stand.
- the shaft-wheel was modified to facilitate bursting, in accordance with standard aircraft test procedures, by drilling an axial hole in the hub and three holes in the back disc to obtain a three piece hub burst.
- the turbine inlet temperature was controlled to 1750°F (954°C) at the turbine inlet flange and the turbocharger was stabilised for 10 minutes at 97,500 rpm at 1750°F (954°C) turbine inlet temperature.
- the turbocharger was then rapidly accelerated until the weakened wheel burst at approximately 159,000rpm.
- the housing was found to contain the wheel burst.
- a conventional aircraft turbine housing 10, as shown in Figure 5 was cast from the alloy of the present invention designated DMS016 2 and completed 600 hours of gas stand cyclic durability testing at an inlet temperature of 1750°F (954°C). Visual examination of the unit after completion of 600 hours of testing showed no cracks either at the tongue section 12, shown in Figure 5, or at the top of the volute (gas passage) surface. Hence, the cast housing made of alloy DMS016 2 was found to have excellent resistance to thermal cracking.
- Oxidation testing at 1500°F (816°C) showed a weight loss of 0.03% after 100 hours.
- the sulphidation test at 1700°F (927 o C) showed a weight loss of approximately 0.4% in one hour.
- the turbocharger housing finite element thermal stress model shown in Figure 5 compared the standard NiResist material (D-5S) with a similar housing model constructed of the alloy DMS016 2 , and the results shown in table III, show that while DMS016 2 developed greater stress, it had a greater fatigue life.
- the temperature at the tongue 12 was 1520°F (827°C) and in the waste gate port region 16 was 1480°F (804°C). While these results were based on very limited creep data, the values for which may vary significantly, the data as shown in Table III indicates greater durability in the alloy of the present invention, DMS016 2 .
- the finite element stress analysis identified two distinct critical areas where fatigue cracks are expected to occur, namely the tongue 12 and the waste gate port region 16. Thus, it was found that D MS016 2 has higher strength at elevated temperatures than D5S ( N iResist) and also has a higher modulus of elasticity and a slightly lower co-efficient of thermal expansion. The result is a casting able to withstand higher thermal stress.
- the DMS016 alloy appears to meet the development guidelines that were established in that it has castability, machinability and service properties equal to or superior to D5S NiResist and in many areas approaches the properties of HK30 stainless steel, a more expensive high nickel material.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Heat Treatment Of Articles (AREA)
- Treatment Of Steel In Its Molten State (AREA)
- Supercharger (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
- Heat Treatment Of Sheet Steel (AREA)
- Heat Treatment Of Steel (AREA)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AT86304758T ATE46194T1 (de) | 1985-06-26 | 1986-06-20 | Rostfreie gussstahllegierung und verfahren zu ihrer herstellung. |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US74915385A | 1985-06-26 | 1985-06-26 | |
| US749153 | 1985-06-26 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0207697A1 true EP0207697A1 (fr) | 1987-01-07 |
| EP0207697B1 EP0207697B1 (fr) | 1989-09-06 |
Family
ID=25012500
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP86304758A Expired EP0207697B1 (fr) | 1985-06-26 | 1986-06-20 | Acier moulé inoxydable et procédé pour sa fabrication |
Country Status (6)
| Country | Link |
|---|---|
| EP (1) | EP0207697B1 (fr) |
| JP (1) | JPH0672294B2 (fr) |
| AT (1) | ATE46194T1 (fr) |
| BR (1) | BR8505304A (fr) |
| DE (1) | DE3665488D1 (fr) |
| ES (1) | ES8707569A1 (fr) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2193726B (en) * | 1986-07-23 | 1991-05-22 | Jgc Corp | Carbon containing compound treating apparatus with resistance to carbon deposition |
| US6165288A (en) * | 1994-05-17 | 2000-12-26 | Ksb Aktienegsellschaft | Highly corrosion and wear resistant chilled casting |
| EP1472382A4 (fr) * | 2002-01-09 | 2005-03-30 | Roman Radon | Alliage coulable pour coussinet a contenu eleve de chrome et d'azote |
| US20140099196A1 (en) * | 2011-06-06 | 2014-04-10 | Borgwarner Inc. | Exhaust-gas turbocharger |
| EP2980253A1 (fr) * | 2014-07-31 | 2016-02-03 | Honeywell International Inc. | Alliages d'acier inoxydable et carters de turbine de turbocompresseur formés à partir d'alliages d'acier inoxydable |
| WO2017194282A1 (fr) * | 2016-05-13 | 2017-11-16 | Continental Automotive Gmbh | Acier pour applications à haute température et carter de turbine constitué de cet acier |
| CN109766634A (zh) * | 2019-01-11 | 2019-05-17 | 徐州徐工矿业机械有限公司 | 一种矿用大型铸钢件数字化正向研发方法 |
| US10975718B2 (en) | 2013-02-12 | 2021-04-13 | Garrett Transportation I Inc | Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same |
| CN113881883A (zh) * | 2020-07-01 | 2022-01-04 | 盖瑞特交通一公司 | 铁素体不锈钢合金和由不锈钢合金形成的涡轮增压器运动部件 |
| DE102020128884A1 (de) | 2020-11-03 | 2022-05-05 | BMTS Technology GmbH & Co. KG | Austenitische Stahllegierung und Turbinengehäuse oder Turbinengehäusebauteil für einen Abgasturbolader |
| CN116812000A (zh) * | 2023-05-26 | 2023-09-29 | 安徽合力股份有限公司合肥铸锻厂 | 球墨铸铁转向节及其制备工艺 |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9534281B2 (en) | 2014-07-31 | 2017-01-03 | Honeywell International Inc. | Turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same |
| US10316694B2 (en) | 2014-07-31 | 2019-06-11 | Garrett Transportation I Inc. | Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same |
| CN109487174A (zh) * | 2018-11-30 | 2019-03-19 | 山西太钢不锈钢股份有限公司 | 一种兼顾高温强度与低温韧性的双相不锈钢板材制造方法 |
| US20220205511A1 (en) * | 2019-04-25 | 2022-06-30 | Volvo Truck Corporation | A flywheel arrangement, a vehicle and a method of manufacturing a flywheel arrangement |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3563729A (en) * | 1968-04-16 | 1971-02-16 | Crucible Inc | Free-machining corrosion-resistant stainless steel |
| US3969109A (en) * | 1974-08-12 | 1976-07-13 | Armco Steel Corporation | Oxidation and sulfidation resistant austenitic stainless steel |
| US4405389A (en) * | 1982-10-21 | 1983-09-20 | Ingersoll-Rand Company | Austenitic stainless steel casting alloy for corrosive applications |
-
1985
- 1985-10-15 JP JP60229768A patent/JPH0672294B2/ja not_active Expired - Lifetime
- 1985-10-23 BR BR8505304A patent/BR8505304A/pt unknown
-
1986
- 1986-06-20 EP EP86304758A patent/EP0207697B1/fr not_active Expired
- 1986-06-20 DE DE8686304758T patent/DE3665488D1/de not_active Expired
- 1986-06-20 AT AT86304758T patent/ATE46194T1/de active
- 1986-06-25 ES ES556779A patent/ES8707569A1/es not_active Expired
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3563729A (en) * | 1968-04-16 | 1971-02-16 | Crucible Inc | Free-machining corrosion-resistant stainless steel |
| US3969109A (en) * | 1974-08-12 | 1976-07-13 | Armco Steel Corporation | Oxidation and sulfidation resistant austenitic stainless steel |
| US4405389A (en) * | 1982-10-21 | 1983-09-20 | Ingersoll-Rand Company | Austenitic stainless steel casting alloy for corrosive applications |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2193726B (en) * | 1986-07-23 | 1991-05-22 | Jgc Corp | Carbon containing compound treating apparatus with resistance to carbon deposition |
| US6165288A (en) * | 1994-05-17 | 2000-12-26 | Ksb Aktienegsellschaft | Highly corrosion and wear resistant chilled casting |
| EP1472382A4 (fr) * | 2002-01-09 | 2005-03-30 | Roman Radon | Alliage coulable pour coussinet a contenu eleve de chrome et d'azote |
| US10309415B2 (en) * | 2011-06-06 | 2019-06-04 | Borgwarner Inc. | Exhaust-gas turbocharger |
| US20140099196A1 (en) * | 2011-06-06 | 2014-04-10 | Borgwarner Inc. | Exhaust-gas turbocharger |
| US10975718B2 (en) | 2013-02-12 | 2021-04-13 | Garrett Transportation I Inc | Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same |
| EP3168318A1 (fr) * | 2014-07-31 | 2017-05-17 | Honeywell International Inc. | Alliages d'acier inoxydable et carters de turbine de turbocompresseur formés à partir d'alliages d'acier inoxydable |
| EP2980253A1 (fr) * | 2014-07-31 | 2016-02-03 | Honeywell International Inc. | Alliages d'acier inoxydable et carters de turbine de turbocompresseur formés à partir d'alliages d'acier inoxydable |
| WO2017194282A1 (fr) * | 2016-05-13 | 2017-11-16 | Continental Automotive Gmbh | Acier pour applications à haute température et carter de turbine constitué de cet acier |
| CN109766634A (zh) * | 2019-01-11 | 2019-05-17 | 徐州徐工矿业机械有限公司 | 一种矿用大型铸钢件数字化正向研发方法 |
| CN113881883A (zh) * | 2020-07-01 | 2022-01-04 | 盖瑞特交通一公司 | 铁素体不锈钢合金和由不锈钢合金形成的涡轮增压器运动部件 |
| DE102020128884A1 (de) | 2020-11-03 | 2022-05-05 | BMTS Technology GmbH & Co. KG | Austenitische Stahllegierung und Turbinengehäuse oder Turbinengehäusebauteil für einen Abgasturbolader |
| CN116812000A (zh) * | 2023-05-26 | 2023-09-29 | 安徽合力股份有限公司合肥铸锻厂 | 球墨铸铁转向节及其制备工艺 |
Also Published As
| Publication number | Publication date |
|---|---|
| ES556779A0 (es) | 1987-08-01 |
| DE3665488D1 (en) | 1989-10-12 |
| EP0207697B1 (fr) | 1989-09-06 |
| ATE46194T1 (de) | 1989-09-15 |
| JPH0672294B2 (ja) | 1994-09-14 |
| ES8707569A1 (es) | 1987-08-01 |
| BR8505304A (pt) | 1987-02-17 |
| JPS624855A (ja) | 1987-01-10 |
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