US3708353A - Processing for iron-base alloy - Google Patents
Processing for iron-base alloy Download PDFInfo
- Publication number
- US3708353A US3708353A US00169534A US3708353DA US3708353A US 3708353 A US3708353 A US 3708353A US 00169534 A US00169534 A US 00169534A US 3708353D A US3708353D A US 3708353DA US 3708353 A US3708353 A US 3708353A
- Authority
- US
- United States
- Prior art keywords
- percent
- iron
- alloy
- base alloy
- nickel
- 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
- 239000000956 alloy Substances 0.000 title claims abstract description 33
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 33
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 18
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 16
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 9
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 9
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 9
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 9
- 239000011651 chromium Substances 0.000 claims abstract description 9
- 239000000203 mixture Substances 0.000 claims abstract description 9
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 9
- 239000011733 molybdenum Substances 0.000 claims abstract description 9
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 9
- 239000010936 titanium Substances 0.000 claims abstract description 9
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 9
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 9
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims abstract description 9
- 229910052742 iron Inorganic materials 0.000 claims abstract description 8
- 238000005096 rolling process Methods 0.000 claims description 7
- 230000032683 aging Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 2
- 230000002459 sustained effect Effects 0.000 claims description 2
- 238000010438 heat treatment Methods 0.000 description 4
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 229910052796 boron Inorganic materials 0.000 description 2
- 230000000052 comparative effect Effects 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 230000000704 physical effect Effects 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 229910001339 C alloy Inorganic materials 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 description 1
- 239000011825 aerospace material Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 230000003466 anti-cipated effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005097 cold rolling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- BHEPBYXIRTUNPN-UHFFFAOYSA-N hydridophosphorus(.) (triplet) Chemical compound [PH] BHEPBYXIRTUNPN-UHFFFAOYSA-N 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000011572 manganese Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 229910052717 sulfur Inorganic materials 0.000 description 1
- 239000011593 sulfur Substances 0.000 description 1
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
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/50—Ferrous alloys, e.g. steel alloys containing chromium with nickel with titanium or zirconium
-
- 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
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/54—Ferrous alloys, e.g. steel alloys containing chromium with nickel with boron
Definitions
- percent vanadium, balance iron is provided to provide a grain size of ASTM 5 or finer when measured at 1,000X magnification (normal ASTM grain size readings are at lOOX magnification) with an ultimate tensile strength at room temperature of about 175,000
- the present invention relates, in general, to the ironbase alloys and, more particularly, to novel processing therefor providing a significant increase in mechanical properties.
- Aerospace Materials Specification AMS 5525 C describes an alloy of the nominal composition, by weight, of percent chromium, 26 percent nickel, 1.3 percent molybdenum, 2.1 percent titanium, 0.3 percent vanadium, balance substantially iron. As specified in AMS 5525 C, this alloy as currently processed has a maximum tensile strength of 105,000 p.s.i. after solutioning and a minimum tensile strength after full heat treatment of 140,000 p.s.i.
- the present invention provides an iron-base alloy having physical properties equivalent to the AMS 5597 nickel-base alloy, particularly a minimum tensile strength at room temperature, in the fully heat treated condition, approaching 180,000 p.s.i.
- processing is conducted at a temperature not exceeding 1,550F., preferably in the range of 1350F.-1,450F.
- a low temperature stabilization thus replaces the high temperature solution heat treatment.
- the alloy is then aged to provide maximum yield strength.
- step 1 Present AMS 5525 AMS 5597 Invention Tensile Strength p.s.i., max. 120,000 105,000 140,000 Elongflw in 20 25 30 2 in. min. Rockwell Hardness (0.030 in.) B B90 TABLE III
- step 3 Present AMS 5525 AMS 5597 Invention Tensile Strength p.s.i., min. 175,000 140,000 180,000 0.2% Strength 160,000 95,000 150,000 p.s.i., min. Elong.% in 2 in. min. 18 15 15
- the following tables summarize the effect of the processing on a material of the appropriate chemistry.
- Iron-base alloy sheet at a nominal composition, by weight, of about 15 percent chromium, 26 percent nickel, 1.3 percent molybdenum, 2.1 percent titanium and 0.3 percent vanadium, having at room temperature an ultimate tensile strength of about 175,000 p.s.i. or higher and an 0.2 percent yield strength of about 160,000 p.s.i. or higher.
- the alloy after rolling being exposed to no sustained temperature in excess of about 1 ,5 50F.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Heat Treatment Of Steel (AREA)
Abstract
An iron-base alloy of the nominal composition, by weight, of 15 percent chromium, 26 percent nickel, 1.3 percent molybdenum, 2.1 percent titanium, 0.3 percent vanadium, balance iron, is provided to provide a grain size of ASTM 5 or finer when measured at 1,000X magnification (normal ASTM grain size readings are at 100X magnification) with an ultimate tensile strength at room temperature of about 175,000 p.s.i.
Description
United States Patent [191 Athey Jan.2,1973
[54] PROCESSING FOR IRON-BASE ALLOY [75] Inventor: Roy L. Athey, North Palm Beach,
Fla.
[73] Assignee: United Aircraft Corporation, East Hartford, Conn.
[22] Filed: Aug. 5, 1971 [2]] Appl. No.: 169,534
[52] US. Cl. ..148/l2.3, 148/37, 148/38 [51] Int. Cl. ..C22c 39/20, C22c 41/02, C21d 7/14 A [58] Field of Search ..l48/l2.3, 38, 37; 75/128 W, 75/128 T, 128 B [56] References Cited UNITED STATES PATENTS 2,909,426 10/1959 Richmond et al ..75/128 F 3,065,067 11/1962 Aggen ..75/128F Primary Examiner-W. W. Stallard AttorneyRichard N. James [5 7 ABSTRACT An iron-base alloy of the nominal composition, by weight, of 15 percent chromium, 26 percent nickel, 1.3 percent molybdenum, 2.1 percent titanium, 0.3
percent vanadium, balance iron, is provided to provide a grain size of ASTM 5 or finer when measured at 1,000X magnification (normal ASTM grain size readings are at lOOX magnification) with an ultimate tensile strength at room temperature of about 175,000
p.s.i.
3 Claims, No Drawings PROCESSING FOR IRON-BASE ALLOY BACKGROUND OF THE INVENTION The present invention relates, in general, to the ironbase alloys and, more particularly, to novel processing therefor providing a significant increase in mechanical properties.
Aerospace Materials Specification AMS 5525 C describes an alloy of the nominal composition, by weight, of percent chromium, 26 percent nickel, 1.3 percent molybdenum, 2.1 percent titanium, 0.3 percent vanadium, balance substantially iron. As specified in AMS 5525 C, this alloy as currently processed has a maximum tensile strength of 105,000 p.s.i. after solutioning and a minimum tensile strength after full heat treatment of 140,000 p.s.i.
There is an urgent demand in certain applications for a structural alloy having a strength of about 180,000 p.s.i. These strength requirements are satisfied by the nickel-base alloy specified in AMS 5597. However, for the particular application in mind, an iron-base alloy would be preferred to a nickel-base alloy because of an anticipated exposure of the alloy to a high pressure hydrogen environment. In such an environment hydrogen embrittlement is much more severe in the nickel-base alloys than those having basis in iron. Thus, it is extremely important, if not essential, to have available an iron-base alloy whose physical properties approach that of the AMS 5597 nickel-base alloy.
SUMMARY OF THE INVENTION The present invention provides an iron-base alloy having physical properties equivalent to the AMS 5597 nickel-base alloy, particularly a minimum tensile strength at room temperature, in the fully heat treated condition, approaching 180,000 p.s.i.
The detailed specification chemistry for this alloy, as compared to the AMS 5525 C alloy is set forth in the following table:
TABLE I Composition (percent by weight) This invention AMS 5525 C Min. Max. Min. Max. Carbon 0.08 0.08 Manganese 0.10 2 Silicon 0.25 1 Phosphorous 0.015 0.025 Sulfur 0.015 0.025 Chromium 13.5 16 13.5 16 Nickel 24 27 24 27 Molybdenum 1 1.5 l 1.5 Titanium 1.9 2.3 1.9 2.3 Boron 0.003 0.01 0.003 0.01 Vanadium 0.1 0.5 0.1 0.5 Aluminum 0.35 0.35 Iron Balance Balance Rolling into sheet or strip conducted at a starting temperature of about 1,800 F. with working down to about 1,550 F. produces a grain size too small to rate by ASTM charts at 100X magnification. Cold rolling with low temperature annealing may also be utilized to produce similar microstructures. Subsequent to the rolling operation, processing is conducted at a temperature not exceeding 1,550F., preferably in the range of 1350F.-1,450F. A low temperature stabilization thus replaces the high temperature solution heat treatment. The alloy is then aged to provide maximum yield strength.
DESCRIPTION OF THE PREFERRED EMBODIMENTS The conventional processing for the AMS 5525 alloy is as follows:
1. rolling between 2,000F. down to 1,800F.;
2. solution heat treatment at 1,800F.;
3. and precipitation heat treatment at 1,325F. for 16 hours.
The processing according to the comparative embodiment of the present invention involves the following parameters and sequence:
1. rolling at 1,800F. down to 1,550F.;
2. stabilization at about 1,400F.;
3. and aging at about 1,300F. for 16 hours. (optional) The comparative results of the respective processing are summarized in the following tables and compared, where appropriate, to the AMS 5597 nickel-base alloy goal:
TABLE 1] After step 1 Present AMS 5525 AMS 5597 Invention Tensile Strength p.s.i., max. 120,000 105,000 140,000 Elongflw in 20 25 30 2 in. min. Rockwell Hardness (0.030 in.) B B90 TABLE III After step 3 Present AMS 5525 AMS 5597 Invention Tensile Strength p.s.i., min. 175,000 140,000 180,000 0.2% Strength 160,000 95,000 150,000 p.s.i., min. Elong.% in 2 in. min. 18 15 15 The following tables summarize the effect of the processing on a material of the appropriate chemistry.
TABLE IV Heat No. 8461 Rolled at 2,000F.
Subsequent H.T. Yield Ultimate F./hr./cool k.s.i. k.s.i. EL R/A 1800/ l/0Q+ l300/l6/AC 98.4 158.2 27 44.7 (AMS 5525) 96.8 165.0 28 49.3 1700/l/OQ+ 100.8 168.3 28 47.1 1300/ 16/AC 1500/ I/OQ-l- 1300/16/AC 137.1 176.2 22 31.3 AC 138.8 176.3 20 36.5
TABLE V Heat No. 8461 Rolled at 1,800F.
Subsequent H.T. Yield Ultimate F.lhr./cool k.s.i. k.s.i. EL R/A Thus, it will be seen that the improved processing of the present invention provides an iron-base alloy having strength approaching that of the AMS 5597'nickelbase alloy, as desired.
Although the invention has been specifically described in detail in connection with specific examples and preferred embodiments, the invention in its broader aspects is not limited thereto, but departures may be made therefrom within the scope of the accompanying claims without departure from the principles of the invention and without sacrificing its chief advantages.
What is claimed is:
1. Alloy sheet at a composition of about, by weight, 13-16 percent chromium, 24-27 percent nickel, l-2 percent molybdenum, 1.5-2.5 percent titanium, 0.0030.0l percent boron, 0.1-0.5 percent vanadium, balance substantially iron, having at room temperature an ultimate tensile strength in excess of about 170,000 p.s.i. and an 0.2 percent yield strength in excess of about 150,000 p.s.i.
2. Iron-base alloy sheet at a nominal composition, by weight, of about 15 percent chromium, 26 percent nickel, 1.3 percent molybdenum, 2.1 percent titanium and 0.3 percent vanadium, having at room temperature an ultimate tensile strength of about 175,000 p.s.i. or higher and an 0.2 percent yield strength of about 160,000 p.s.i. or higher.
3. The method of producing sheet from an alloy of the nominal composition of about, by weight, 15 percent chromium, 26 percent nickel, 1.3 percent molybdenum, 2.1 percent titanium, 0.3 percent vanadium, balance substantially iron, which comprises:
rolling at a temperature not exceeding about and subsequently aging the alloy at a temperature of about 1,300F.,
the alloy after rolling being exposed to no sustained temperature in excess of about 1 ,5 50F.
4 I1! l I i
Claims (2)
- 2. Iron-base alloy sheet at a nominal composition, by weight, of about 15 percent chromium, 26 percent nickel, 1.3 percent molybdenum, 2.1 percent titanium and 0.3 percent vanadium, having at room temperature an ultimate tensile strength of about 175,000 p.s.i. or higher and an 0.2 percent yield strength of about 160, 000 p.s.i. or higher.
- 3. The method of producing sheet from an alloy of the nominal composition of about, by weight, 15 percent chromium, 26 percent nickel, 1.3 percent molybdenum, 2.1 percent titanium, 0.3 percent vanadium, balance substantially iron, which comprises: rolling at a temperature not exceeding about 1,800* F., and subsequently aging the alloy at a temperature of about 1, 300* F., the alloy after rolling being exposed to no sustained temperature in excess of about 1,550* F.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US16953471A | 1971-08-05 | 1971-08-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3708353A true US3708353A (en) | 1973-01-02 |
Family
ID=22616103
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US00169534A Expired - Lifetime US3708353A (en) | 1971-08-05 | 1971-08-05 | Processing for iron-base alloy |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3708353A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5223053A (en) * | 1992-01-27 | 1993-06-29 | United Technologies Corporation | Warm work processing for iron base alloy |
| FR2727982A1 (en) * | 1994-12-13 | 1996-06-14 | Imphy Sa | AUSTENITIC STAINLESS STEEL FOR HOT EMPLOYMENT |
| EP1262157A1 (en) * | 2001-05-29 | 2002-12-04 | Anton Meyer & Co.AG | Scalpel for ophtalmology surgery |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2909426A (en) * | 1958-03-27 | 1959-10-20 | Universal Cyclops Steel Corp | Ferrous base alloys |
| US3065067A (en) * | 1959-01-21 | 1962-11-20 | Allegheny Ludlum Steel | Austenitic alloy |
| CA698600A (en) * | 1964-11-24 | The Carpenter Steel Company | Age hardenable austenitic chromium-nickel-titanium steel | |
| US3199978A (en) * | 1963-01-31 | 1965-08-10 | Westinghouse Electric Corp | High-strength, precipitation hardening austenitic alloys |
| US3212884A (en) * | 1963-07-03 | 1965-10-19 | Marjorie O Soler | Ferrous base alloys containing boron |
-
1971
- 1971-08-05 US US00169534A patent/US3708353A/en not_active Expired - Lifetime
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA698600A (en) * | 1964-11-24 | The Carpenter Steel Company | Age hardenable austenitic chromium-nickel-titanium steel | |
| US2909426A (en) * | 1958-03-27 | 1959-10-20 | Universal Cyclops Steel Corp | Ferrous base alloys |
| US3065067A (en) * | 1959-01-21 | 1962-11-20 | Allegheny Ludlum Steel | Austenitic alloy |
| US3199978A (en) * | 1963-01-31 | 1965-08-10 | Westinghouse Electric Corp | High-strength, precipitation hardening austenitic alloys |
| US3212884A (en) * | 1963-07-03 | 1965-10-19 | Marjorie O Soler | Ferrous base alloys containing boron |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5223053A (en) * | 1992-01-27 | 1993-06-29 | United Technologies Corporation | Warm work processing for iron base alloy |
| FR2727982A1 (en) * | 1994-12-13 | 1996-06-14 | Imphy Sa | AUSTENITIC STAINLESS STEEL FOR HOT EMPLOYMENT |
| WO1996018750A1 (en) * | 1994-12-13 | 1996-06-20 | Imphy S.A. | Austenitic stainless steel to be used hot |
| EP1262157A1 (en) * | 2001-05-29 | 2002-12-04 | Anton Meyer & Co.AG | Scalpel for ophtalmology surgery |
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