US3758295A - Nickel chromium iron alloys - Google Patents
Nickel chromium iron alloys Download PDFInfo
- Publication number
- US3758295A US3758295A US00108171A US3758295DA US3758295A US 3758295 A US3758295 A US 3758295A US 00108171 A US00108171 A US 00108171A US 3758295D A US3758295D A US 3758295DA US 3758295 A US3758295 A US 3758295A
- Authority
- US
- United States
- Prior art keywords
- alloys
- nickel
- alloy
- titanium
- stress
- 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.)
- Expired - Lifetime
Links
- 229910000640 Fe alloy Inorganic materials 0.000 title abstract description 7
- BIJOYKCOMBZXAE-UHFFFAOYSA-N chromium iron nickel Chemical compound [Cr].[Fe].[Ni] BIJOYKCOMBZXAE-UHFFFAOYSA-N 0.000 title abstract description 7
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 abstract description 20
- 239000010936 titanium Substances 0.000 abstract description 20
- 229910052719 titanium Inorganic materials 0.000 abstract description 20
- 229910052782 aluminium Inorganic materials 0.000 abstract description 18
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract description 18
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract description 16
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 abstract description 16
- 229910052799 carbon Inorganic materials 0.000 abstract description 16
- 229910052750 molybdenum Inorganic materials 0.000 abstract description 16
- 239000011733 molybdenum Substances 0.000 abstract description 16
- 239000000203 mixture Substances 0.000 abstract description 7
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 abstract 1
- 229910045601 alloy Inorganic materials 0.000 description 54
- 239000000956 alloy Substances 0.000 description 54
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 42
- 230000035882 stress Effects 0.000 description 27
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 22
- 229910052759 nickel Inorganic materials 0.000 description 21
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 11
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 11
- 229910052796 boron Inorganic materials 0.000 description 11
- 229910052804 chromium Inorganic materials 0.000 description 11
- 239000011651 chromium Substances 0.000 description 11
- 238000010438 heat treatment Methods 0.000 description 11
- 229910052742 iron Inorganic materials 0.000 description 11
- 230000032683 aging Effects 0.000 description 7
- 239000012535 impurity Substances 0.000 description 6
- 239000010955 niobium Substances 0.000 description 6
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 6
- 238000001816 cooling Methods 0.000 description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 4
- 229910052758 niobium Inorganic materials 0.000 description 4
- 239000010703 silicon Substances 0.000 description 4
- 229910052710 silicon Inorganic materials 0.000 description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 3
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 3
- 239000010941 cobalt Substances 0.000 description 3
- 229910017052 cobalt Inorganic materials 0.000 description 3
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 3
- 229910052802 copper Inorganic materials 0.000 description 3
- 239000010949 copper Substances 0.000 description 3
- 229910052748 manganese Inorganic materials 0.000 description 3
- 239000011572 manganese Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000010791 quenching Methods 0.000 description 3
- 229910052715 tantalum Inorganic materials 0.000 description 3
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 3
- 238000011282 treatment Methods 0.000 description 3
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 2
- 230000002411 adverse Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000000470 constituent Substances 0.000 description 2
- 230000002596 correlated effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000000171 quenching effect Effects 0.000 description 2
- 238000007670 refining Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 229910052726 zirconium Inorganic materials 0.000 description 2
- 240000002129 Malva sylvestris Species 0.000 description 1
- 235000006770 Malva sylvestris Nutrition 0.000 description 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 235000013351 cheese Nutrition 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000000875 corresponding effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- NRUQNUIWEUZVLI-UHFFFAOYSA-O diethanolammonium nitrate Chemical compound [O-][N+]([O-])=O.OCC[NH2+]CCO NRUQNUIWEUZVLI-UHFFFAOYSA-O 0.000 description 1
- 235000012438 extruded product Nutrition 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 229910001068 laves phase Inorganic materials 0.000 description 1
- 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 description 1
- 238000002844 melting Methods 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 229910052717 sulfur Inorganic materials 0.000 description 1
- 239000011593 sulfur Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
Definitions
- rotor discs With regard to rotor discs, the different properties required are indeed manifold and complex. Contributing to this and of particular significance is the large variation of temperature occurring radially between the center or hub and the periphery or rim of the disc. This temperature gradient is accompanied by a stress gradient in the opposite sense so that the highest stress occurs in the lowtemperature region near the hub and vice versa.
- a rotor disc material must therefore not only have a high creep strength up to the highest temperatures to which it is exposed to ensure freedom from distortion by creep in service, particularly at the rim, but also a high proof stress and ultimate tensile strength at more moderate temperatures to ensure that the high hub stresses do not lead to distortion or fracture on loading.
- nickel alloys have found extensive use in the production of rotor discs as well as a host of other diverse high temperature products.
- Typical of the relatively lower-cost alloys hitherto used for rotor discs is the nickel-chromium-iron alloy (herein designated Alloy A) having the following approximate nominal composi- 3,758,295 Patented Sept. 11, 1973 ICC tion: carbon 0.05%, chromium 12.5%, nickel 42.5%, molybdenum 5.7%, titanium 2.8%, aluminum 0.2%, boron 0.015%, balance iron and impurities. While this alloy has a very satisfactory combination of properties, the progressive increase in the designed operating temperatures and stresses of gas-turbine engines calls for a material having a substantially higher proof stress.
- This desideratum can be obtained by the use of nickelchromium-base alloys containing high contents of such alloying elements as molybdenum and niobium, but such alloys have the serious disadvantages of being very difficult to hot-work and extremely difficult to machine.
- the present invention contemplates providing alloys containing (in weight percent) about 0.02% to about 0.1% carbon, about 10% to about 15% chromium, about 5% to about 7% molybdenum, about 3.3% to about 4.5% titanium, about 0.2% to about 1.1% aluminum, about 45% to about 55% nickel, about 0.003% to 0.02% boron, the balance being essentially iron. It is particularly advantageous in seeking an optimum combination of properties that the total percentage of titanium plus aluminum is (a) greater than 0.06 times the percentage of nickel plus 1.0 and (b) less than 0.24 times the percentage of nickel minum 6.0.
- the content of each of the constituents of the alloys responds to the ranges above set forth.
- percentages of carbon significantly less than 0.02% the alloys are notch-sensitive, their life in stress-rupture tests being greatly reduced by the presence of notches. Too much carbon, on the other hand, leads to the formation of excessive amounts of carbides which tend to segregate and give rise to directionality effects in the tensile and stress-rupture properties of the wrought material.
- the carbon content should not exceed about 0.1% and beneficially is not more than 0.08%. It is most advantageous that the carbon be at least 0.03% but not more than 0.06%.
- At least about 10% chromium is required for adequate resistance to oxidation at operating temperature, but more than about 15% renders the alloys liable to embrittlement on prolonged heating.
- Molybdenum contributes to the stress-rupture strength of the alloys, and at least 5% is required for this purpose. Raising the molybdenum content much above 7%, however, makes the alloy very difficult to work and also susceptible to embrittlement, and preferably the molybdenum content is from 5.4% to 6.7%.
- the titanium be less than about 3.3%, it can be expected that one or more of proof stress, hardness or stress-rupture strength will be inadequate. However, increasing the titanium content above 4.5% undesirably reduces the ductility. It is much preferred that the titanium be at least 3.5% and not more than 4.25%.
- Aluminum in an amount of about 0.2% or more is required to avoid the risk of embrittlement. Surprisingly, however, increasing the aluminum content, while increasing the tensile ductility of the alloys, is found to lower their proof stress. For this reason it should not exceed about 1.1%.
- An aluminum range of 0.3% to 0.9% is deemed quite satisfactory but in striving for the best combination of proof stress and ductility it is advantageously from 0.5% to 0.7%.
- the alloys should contain at least 45% of nickel to avoid instability and embrittlement through the formation of Laves phase on prolonged heating. Too much nickel, however, tends to reduce the proof stress and unduly raise the cost of the alloy, and the nickel content must therefore not exceed 55%. Moreover, as above indicated, it is to considerable advantage that the percentage of nickel, titanium and aluminum be correlated to satisfy the relationships designated as (a) and (b) above. By observing these relationships an exceptionally good combination of desired mechanical characteristics is more consistently attained.
- alloys 0.03% to 0.08% preferably 0.03% to 0.06%, carbon, 11% to 14% chromium, 5.4% to 6.7% molybdenum, 3.75% to 4.1% titanium, 0.5% to 0.7% aluminum, 47% to 52% nickel, 0.01% to 0.02% boron, the balance essentially iron.
- solution heating comprises heating at 1040 C. to 1100 C. for 1 to 8, preferably for 2 to 4 hours.
- the alloys may be aged in two stages, the first consisting of heating at 740 C. to 780 C. for more than 1 hour followed by aging at 675 C. to 720 C. for at least 8 hours.
- One suitable aging treatment of this kind comprises heating at 775 C. for 20 hours and then at 700 C. for 16 hours. Cooling after the solution heating is preferably rapid, e.g., a water quench, but cooling between aging treatments may be conducted in air.
- the present alloys after solution heating for 2 hours at 1095 C., water quenching, aging for 20 hours at 775 C., air cooling, aging at 700 C. for 16 hours and air cooling, are generally characterized by a proof stress (0.1% offset) at 600 C. of at least about 62 t.s.i. (long tons per square inch), a tensile ductility of at least about 14% elongation and a stress-rupture life of over 100 hours under a stress of 47 t.s.i. at 650 C. They have excellent hot workability, can be deformed hot by rolling, forging, swaging and extrusion and can be deformed cold by rolling, drawing and swaging.
- Three alloys A, B and 1 were prepared by air-melting and vacuum-refining followed, in the case of Alloys A and B, by electroslag refining. Ingots cast from the alloys were forged to cheeses and then to rotor disc blanks 14 inches in diameter having a central punched-out bore 3 inches in diameter. After heat treatment to develop the optimum tensile properties, the disc blanks were sectioned and test pieces were machined from similar positions adjacent and tangential to the central bore.
- Alloy B was a preferred alloy of our above-mentioned specification No. 1,132,724 having the following nominal composition, in percent by weight: carbon 0.04%, chromium 12.5%, nickel 42.5%, molybdenum 5.75%, titanium 3.0%, aluminum 0.4%, niobium 0.55% and boron 0.015%, the balance, apart from impurities which included silicon 0.2% and manganese 0.1%, being iron. Alloy No.
- iron in referring to iron as constituting the balance or essentially the balance of the subject alloys, the presence of other elements, as will be appreciated by those skilled in the art, is not excluded such as those commonly present as incidental elements, e.g., deoxidizing and cleansing constituents, and impurities ordinarily associated therewith in amounts that do not adversely affect the basic characteristic of the alloys.
- silicon and manganese common impurities in such alloys, it is not necessary that either should exceed 0.5 each and, in fact, they should be held to low levels. Not more than traces or very little lead and sulfur should be present but the alloys can contain up to at least 0.5% copper, 1% cobalt and 0.1% zirconium. However, it is important that they be free or substantially free of niobium or tantalum, the combined percentage of which should be held to less than about 0.3%, e.g., less than 0.2%.
- a nickel-chromium-iron alloy characterized by (a) a proof stress of at least about 62 t.s.i. at a temperature of about 600 C., (b) a tensile ductility of at least 14% at 650 C., (c) a stress rupture-life of at least 100 hours under a stress of 47 t.s.i. at a temperature of about 650 C.
- said alloy consisting of about 0.02% to about 0.1% carbon, about to about chromium, about 5% to about 7% molybdenum, about 3.3% to about 4.5 titanium, about 0.2% to 1.1% aluminum, the total percentage of the titanium plus aluminum being greater than 0.06 time the percentage of nickel plus 1.0 and less than 0.24 time the percentage of nickel minus 6.0, about 45% to about 55% nickel, about 0.003% to about 0.02% boron, up to about 0.5% each of silicon, manganese and copper, up to 1% cobalt, up to less than 0.3% of columbium plus tantalum, and the balance essentially iron.
- a wrought rotor disc produced from an alloy composition as set forth in claim 1.
- a nickel-chromium-iron alloy characterized by (a) a proof stress of at least about 62 t.s.i. at a temperature of about 600 C., (b) a tensile ductility of at least 14% at 65 0 C., (c) a stress rupture life of at least about 100 hours under a stress of about 47 t.s.i. at a temperature of about 650 C.
- said alloy consisting of about 0.02% to about 0.1% carbon, about 10% to about 15% chromium, about 5% to about 7% molybdenum, about 3.5% to about 4.5% titanium, about 0.3% to about 0.9% aluminum, about to about nickel, about 0.003% to about 0.02% boron, up to about 0.5% each of silicon, manganese and copper, up to 1% cobalt, up to less than 0.3% of columbium plus tantalum, and the balance essentially iron.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB364373A GB1325595A (en) | 1969-07-28 | 1970-01-26 | Steering network |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3758295A true US3758295A (en) | 1973-09-11 |
Family
ID=9762199
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US00108171A Expired - Lifetime US3758295A (en) | 1970-01-26 | 1971-01-20 | Nickel chromium iron alloys |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US3758295A (enrdf_load_stackoverflow) |
| AT (1) | AT312950B (enrdf_load_stackoverflow) |
| CA (1) | CA947120A (enrdf_load_stackoverflow) |
| DE (1) | DE2102749A1 (enrdf_load_stackoverflow) |
| FR (1) | FR2076968A5 (enrdf_load_stackoverflow) |
| GB (1) | GB1302293A (enrdf_load_stackoverflow) |
| SE (1) | SE360389B (enrdf_load_stackoverflow) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4174213A (en) * | 1977-03-04 | 1979-11-13 | Hitachi, Ltd. | Highly ductile alloys of iron-nickel-chromium-molybdenum system for gas turbine combustor liner and filler metals |
| US4401622A (en) * | 1981-04-20 | 1983-08-30 | The International Nickel Co., Inc. | Nickel-chromium-iron alloy |
| EP0234172A2 (en) | 1985-12-30 | 1987-09-02 | United Technologies Corporation | High-strength nickel-base superalloy for castings, treated by means of hot isostatic pressing |
| CN115233071A (zh) * | 2022-06-23 | 2022-10-25 | 西北工业大学 | 一种Ni-Fe基高温中熵合金及其制备方法 |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4750944A (en) * | 1985-12-30 | 1988-06-14 | United Technologies Corporation | Laves free cast+hip nickel base superalloy |
-
1970
- 1970-01-26 GB GB364370A patent/GB1302293A/en not_active Expired
-
1971
- 1971-01-20 US US00108171A patent/US3758295A/en not_active Expired - Lifetime
- 1971-01-21 DE DE19712102749 patent/DE2102749A1/de active Pending
- 1971-01-22 AT AT51271A patent/AT312950B/de not_active IP Right Cessation
- 1971-01-22 CA CA103,425A patent/CA947120A/en not_active Expired
- 1971-01-25 SE SE00802/71A patent/SE360389B/xx unknown
- 1971-01-25 FR FR7102381A patent/FR2076968A5/fr not_active Expired
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4174213A (en) * | 1977-03-04 | 1979-11-13 | Hitachi, Ltd. | Highly ductile alloys of iron-nickel-chromium-molybdenum system for gas turbine combustor liner and filler metals |
| US4401622A (en) * | 1981-04-20 | 1983-08-30 | The International Nickel Co., Inc. | Nickel-chromium-iron alloy |
| EP0234172A2 (en) | 1985-12-30 | 1987-09-02 | United Technologies Corporation | High-strength nickel-base superalloy for castings, treated by means of hot isostatic pressing |
| US4888253A (en) * | 1985-12-30 | 1989-12-19 | United Technologies Corporation | High strength cast+HIP nickel base superalloy |
| CN115233071A (zh) * | 2022-06-23 | 2022-10-25 | 西北工业大学 | 一种Ni-Fe基高温中熵合金及其制备方法 |
| CN115233071B (zh) * | 2022-06-23 | 2024-05-24 | 西北工业大学 | 一种Ni-Fe基高温中熵合金及其制备方法 |
Also Published As
| Publication number | Publication date |
|---|---|
| DE2102749A1 (de) | 1971-07-29 |
| AT312950B (de) | 1974-01-25 |
| SE360389B (enrdf_load_stackoverflow) | 1973-09-24 |
| CA947120A (en) | 1974-05-14 |
| GB1302293A (enrdf_load_stackoverflow) | 1973-01-04 |
| FR2076968A5 (enrdf_load_stackoverflow) | 1971-10-15 |
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