US2860968A - Wrought high temperature alloy - Google Patents
Wrought high temperature alloy Download PDFInfo
- Publication number
- US2860968A US2860968A US571377A US57137756A US2860968A US 2860968 A US2860968 A US 2860968A US 571377 A US571377 A US 571377A US 57137756 A US57137756 A US 57137756A US 2860968 A US2860968 A US 2860968A
- Authority
- US
- United States
- Prior art keywords
- titanium
- aluminum
- boron
- iron
- molybdenum
- 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
- 229910045601 alloy Inorganic materials 0.000 title description 5
- 239000000956 alloy Substances 0.000 title description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 20
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 18
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 14
- 239000010936 titanium Substances 0.000 claims description 14
- 229910052719 titanium Inorganic materials 0.000 claims description 14
- 229910052782 aluminium Inorganic materials 0.000 claims description 13
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 13
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 12
- 229910052796 boron Inorganic materials 0.000 claims description 12
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 10
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 10
- 229910052799 carbon Inorganic materials 0.000 claims description 10
- 229910052742 iron Inorganic materials 0.000 claims description 10
- 229910052750 molybdenum Inorganic materials 0.000 claims description 10
- 239000011733 molybdenum Substances 0.000 claims description 10
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 9
- 229910052804 chromium Inorganic materials 0.000 claims description 9
- 239000011651 chromium Substances 0.000 claims description 9
- 229910052759 nickel Inorganic materials 0.000 claims description 9
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 7
- 230000002035 prolonged effect Effects 0.000 claims description 7
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims description 6
- 229910052748 manganese Inorganic materials 0.000 claims description 6
- 239000011572 manganese Substances 0.000 claims description 6
- 229910052710 silicon Inorganic materials 0.000 claims description 6
- 239000010703 silicon Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 description 11
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 239000000203 mixture Substances 0.000 description 2
- 229910000640 Fe alloy Inorganic materials 0.000 description 1
- 241000124008 Mammalia Species 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
-
- 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
- the 350% aluminum material of this invention has numerous applications in 5 250% titanium gas turbines and jet engine components; some of 5.00- 6.00% aluminum and titanium combined uses for which this material is particularly useful are: 0 08% boron fabricated nozzle guide vanes, afterburner flame gutters,' I i' m nickel turbine shrouds, etc.
- the material of this invention in i sheet metal form has better high-temperature properties.
- oaluminum 40 Th h ht kd 3 00% titanium e wroug t or o wor e ma mas 0 1s 1nven- 020% boron tlon may be subsequently solutlon treated and aged.
- the material also may contain silicon ranging up to about typical treatment this purpose iljcludes hheatingf for one hour at 2075"v water quenc ing, re eating our ig g iigzii ig 3 2 f g ifi 3 25 222: hours at 1 100 F., and thereaf ter air cooling.
- a wrought-metal product capable of withstanding high and prolonged stress at elevated temperature consisting essentially as follows:
- a sheet metal product capable of withstanding high and prolonged stress at elevated temperature consisting 1o essentially as follows:
- a hot rolled sheet metal capable of withstanding high and prolonged stress at elevated temperature consisting essentially as follows:
- a wrought-metal product capable of withstanding high and prolonged stress at elevated temperature consisting essentially as follows:
- a wrought-metal product capable of withstanding high and prolonged stress at elevated temperature consisting essentially as follows:
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
- Catalysts (AREA)
- Heat Treatment Of Steel (AREA)
Description
ICC
Patented Nov. 18,1958
Usually, the preferred materials will fall within ;a range 1 of composition as follows:
2,860,968 I v WROUGHT HIGH TE PERATURE- nnoy 0.0% 930% carbon Alfred L. Boegehold, Pontiac, Mich., Dean K. Hanink, chromlum Indianapolis, 11111., and Fred J. Webbere, Pontiac, Mich., 4.00.- 6.00% molybdenum assignors to General Motors Corporation, 'Detroit, 14.00-30.00% 11'011 Mich., acorporation of Delaware v 1.50- 5.00% aluminum 1.50- 2.50% titanium No Drawing. Applicahon March 14 1956 0 Serial No. 571,377
Balance n1ckel 8 Claims. -(Cl. 75122) The following is atypical example of a highly satis- This invention has to do with an improved high-temac ory alloy in accordance with the invention; perature alloy which is capable of being hot worked into any desired shape and is capable 'of withstanding pro- 5 carbon longed stress at elevated temperature. 0 10% (max) manganese The alloy of this invention is especially useful for 0 (mm) Silicon parts which have to withstand high stresses under elevated 72 14 00 17 0% chromium temperature conditions such as 1500 F. or higher and" 600% molybdenum at the same time be resistant to oxidation. The 240046007] iron alloy uses a minimum of strategic materials. The 350% aluminum material of this invention has numerous applications in 5 250% titanium gas turbines and jet engine components; some of 5.00- 6.00% aluminum and titanium combined uses for which this material is particularly useful are: 0 08% boron fabricated nozzle guide vanes, afterburner flame gutters,' I i' m nickel turbine shrouds, etc. The material of this invention in i sheet metal form has better high-temperature properties. I and much lower strategic rating than materials current- All composltlons P f mventlon have good 1 available commercially in sheet form WOIk-abllltyo at temperatures ln the range of about 1750 The composition of the material of the present invento 21 25 Th ls 15 p r c lar advantage of the tion in its broader aspects consists essentially as follows: Pmsmt mvemlon f fl mammals can b6 readfly O 03 0307 b processed from-cast ingots into wrought products such g; as bar StuCll, sheets, etc., using conventional rolling mill 6 f gi equipment. The materials have been successfully re- 4 15 p enum duced into sheets having thicknesses as low as 0.03 inch. 3 :35; The sheet materials of this invention may be hot or cold pressed or otherwise formed into desired shapes.
oaluminum 40 Th h ht kd 3 00% titanium e wroug t or o wor e ma mas 0 1s 1nven- 020% boron tlon may be subsequently solutlon treated and aged. A The material also may contain silicon ranging up to about typical treatment this purpose iljcludes hheatingf for one hour at 2075"v water quenc ing, re eating our ig g iigzii ig 3 2 f g ifi 3 25 222: hours at 1 100 F., and thereaf ter air cooling. Another rfnges between 0 05 and 030 Percent and the s ilicon t1:eatmen-t mcludas heatmg at 2000-0 for 20 minutes rangesbetween afid 0 60 percent. Best results also an coolmg, and thereafter reheatlng for 20 hours at are obtained when the iron content, is not more than 1500 about 30 percent and when the material has a boron Table A below glves the results of typical tests on test content of at least .04 percent and preferably at least bars made fro]? Wrought barstfick from dlflgrenfi heats Q06 percgnta This amount of boron substantially The Table A gives thecompositlon of the mater1als,.the proves elongation rupture and with increase in heat treat ng cond1t1ons, t1me to rupture. 1n hours, perrupture life. Amounts of iron above 30 percent cause cent elongatlon at rupture, and the test condit1ons includa decrease in high-temperature strength g temperature and $1655 mp y l F S Table A wnouon'r BAasTo'oK Heat c a v ..H0l1lS. .Percent.. No. 0 Mn Si Ni v Cr Mo Fe Al' Ti B: Condition to Eltsgnga- Test Conditions V ggigg z 2.1 1,500 F./35,000 p. s. 1. 1 .19 .05 .11 Bal. 14.7 4.35 23.9 3.57 2.23 ND gg;. a1 1,500F. a 5,0o 0 1.3.1. iiit fiiti a v 4. new F./35,000p. .1. 1 h .,'2,075 F. o 2 .19 .05 1 .11 Bal. 14.6 4.17 23.5 3.39 2.31 .041 {4-hi's., ,500F 13.8 1,500 F./35,000p. s,i. v 1 1hr., 2,07 F. 11.6 1,500 F./35,000p. a.1.. 3 .05 .14 Bel. 14.8' 4.24 26.0 2.80 2.4a .05 1m-.,2,075 F. 11.1 1,500" F./25,000p. s. 1.-
0.03-0.30% carbon 0.00-1.00% silicon 0.00-1.00% manganese 13.00-17.00% chromium 4.00-6.00% molybdenum 24.00-55.00% nickel 14.00-55.00% iron 1.50-5.00% aluminum LSD-3.00% titanium 0.01-0.20% boron 2. A wrought-metal product capable of withstanding high and prolonged stress at elevated temperature consisting essentially as follows:
6 24.00-26.0% iron 2.753.50% aluminum 1.75-2.50% titanium 5.00-6.00% aluminum and titanium combined 0.04-0.08% boron Balance nickel 6. A sheet metal product capable of withstanding high and prolonged stress at elevated temperature consisting 1o essentially as follows:
0.05-0.20% carbon 0.10% (max.) manganese 0.60% (max.) silicon 14.00-17.00% chromium 4.006.00% molybdenum 24.00-26.00% iron 2.753.50% aluminum 1.75-2.50% titanium 5.00-6.00% aluminum and titanium combined 0.04-0.08% boron Balance nickel 0.03-0.30% carbon 0.00-1.00% silicon 0.00-1.00% manganese 7. A hot rolled sheet metal capable of withstanding high and prolonged stress at elevated temperature consisting essentially as follows:
13.0017.00%chromium 4.00-6.00% molybdenum 24.0055.00% nickel l4.0055.00% iron LSD-5.00% aluminum 1.50-3.00% titanium 0.0l0.20% boron 3. The product of claim 2 which has been solution treated and aged.
4. A wrought-metal product capable of withstanding high and prolonged stress at elevated temperature consisting essentially as follows:
0.03-0.30% carbon 13.00-17.00% chromium 4.00-6.00% .molybdenum 14.00-30.00% iron 1.50-5.00% aluminum LSD-3.00% titanium 0.04-0.20% boron Balance nickel 5. An alloy capable of being hot worked and withstanding high and prolonged stress at elevated tempera tureconsisting essentially as follows:
0.05-0.20% carbon 0.10% (max.) manganese 0.60% (max.) silicon 14.00l7.00% chromium 4.00-6.00% molybdenum ODS-0.30% carbon 13.00-17.00% chromium 4.006.00% molybdenum 14.0030.00% iron LSD-5.00% aluminum 1.50-2.50% titanium 0.04-0.20% boron Balance nickel 35 8. A wrought-metal product capable of withstanding high and prolonged stress at elevated temperature consisting essentially as follows:
0.03-O.30% carbon 13.00-17.00% chromium ADO-6.00% molybdenum 14.0030.00% iron LSD-5.00% aluminum 1.50-2.50% titanium 0.06-0.08% boron Balance nickel References Cited in the file of this patent UNITED STATES PATENTS 2,343,040 Allen et al. Feb. 29, 1944 2,661,284 Nisbet Dec. 1, 1953 2,668,536 Callaway et al. Sept. 7, 1954 FOREIGN PATENTS 632,712 Great Britain Dec. 5, 1949
Claims (2)
- 0.03-0.30% CARBON 0.00-1.00% SILICON 0.00-1.00% MANGANESE 13.00-17.00% CHROMIUM 4.00-6.00% MOLYBDENUM 24.00-55.00% NICKEL 14.00-55.00% IRON 1.50-5.00% ALUMINUM 1.50-3.00% TITANIUM 0.01-0.20% BORON
- 1. AN ALLOY CAPABLE OF BEING HOT WORKED AND WITHSTANDING HIGH AND PROLONGED STRESS AT ELEVATED TEMPERATURE CONSISTING ESSENTIALLY AS FOLLOWS:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US571377A US2860968A (en) | 1956-03-14 | 1956-03-14 | Wrought high temperature alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US571377A US2860968A (en) | 1956-03-14 | 1956-03-14 | Wrought high temperature alloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2860968A true US2860968A (en) | 1958-11-18 |
Family
ID=24283443
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US571377A Expired - Lifetime US2860968A (en) | 1956-03-14 | 1956-03-14 | Wrought high temperature alloy |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2860968A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3046108A (en) * | 1958-11-13 | 1962-07-24 | Int Nickel Co | Age-hardenable nickel alloy |
| US3051565A (en) * | 1960-04-29 | 1962-08-28 | Allegheny Ludlum Steel | Austenitic alloys |
| US3243287A (en) * | 1962-09-14 | 1966-03-29 | Crucible Steel Co America | Hot strength iron base alloys |
| US3457066A (en) * | 1959-04-10 | 1969-07-22 | Gen Electric | Nickel base alloy |
| US3844774A (en) * | 1973-09-24 | 1974-10-29 | Carondelet Foundry Co | Corrosion-resistant alloys |
| US3993475A (en) * | 1974-04-20 | 1976-11-23 | Duraloy Blaw-Knox, Inc. | Heat resisting alloys |
| EP0066365A3 (en) * | 1981-04-20 | 1983-01-19 | Howmet Turbine Components Corporation | Nickel-chromium-iron alloy and castings thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2343040A (en) * | 1942-12-18 | 1944-02-29 | Driver Co Wilbur B | Electrical resistance alloy |
| GB632712A (en) * | 1947-01-17 | 1949-12-05 | Int Nickel Co | Improvements relating to heat-resisting alloys and to articles made from them |
| US2661284A (en) * | 1951-06-27 | 1953-12-01 | Gen Electric | Precipitation hardenable iron base alloy |
| US2668536A (en) * | 1952-11-14 | 1954-02-09 | John R Farries | Instrument for operating on mitral valves |
-
1956
- 1956-03-14 US US571377A patent/US2860968A/en not_active Expired - Lifetime
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2343040A (en) * | 1942-12-18 | 1944-02-29 | Driver Co Wilbur B | Electrical resistance alloy |
| GB632712A (en) * | 1947-01-17 | 1949-12-05 | Int Nickel Co | Improvements relating to heat-resisting alloys and to articles made from them |
| US2661284A (en) * | 1951-06-27 | 1953-12-01 | Gen Electric | Precipitation hardenable iron base alloy |
| US2668536A (en) * | 1952-11-14 | 1954-02-09 | John R Farries | Instrument for operating on mitral valves |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3046108A (en) * | 1958-11-13 | 1962-07-24 | Int Nickel Co | Age-hardenable nickel alloy |
| US3457066A (en) * | 1959-04-10 | 1969-07-22 | Gen Electric | Nickel base alloy |
| US3051565A (en) * | 1960-04-29 | 1962-08-28 | Allegheny Ludlum Steel | Austenitic alloys |
| US3243287A (en) * | 1962-09-14 | 1966-03-29 | Crucible Steel Co America | Hot strength iron base alloys |
| US3844774A (en) * | 1973-09-24 | 1974-10-29 | Carondelet Foundry Co | Corrosion-resistant alloys |
| US3993475A (en) * | 1974-04-20 | 1976-11-23 | Duraloy Blaw-Knox, Inc. | Heat resisting alloys |
| EP0066365A3 (en) * | 1981-04-20 | 1983-01-19 | Howmet Turbine Components Corporation | Nickel-chromium-iron alloy and castings thereof |
| US4401622A (en) * | 1981-04-20 | 1983-08-30 | The International Nickel Co., Inc. | Nickel-chromium-iron alloy |
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