US3833363A - Titanium-base alloy and method of improving creep properties - Google Patents

Titanium-base alloy and method of improving creep properties Download PDF

Info

Publication number
US3833363A
US3833363A US00241286A US24128672A US3833363A US 3833363 A US3833363 A US 3833363A US 00241286 A US00241286 A US 00241286A US 24128672 A US24128672 A US 24128672A US 3833363 A US3833363 A US 3833363A
Authority
US
United States
Prior art keywords
alloy
silicon
titanium
silicon content
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
Application number
US00241286A
Inventor
H Bomberger
S Seagle
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RMI Co
Original Assignee
RMI Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by RMI Co filed Critical RMI Co
Priority to US00241286A priority Critical patent/US3833363A/en
Priority to CA166,903A priority patent/CA966334A/en
Priority to GB1573573A priority patent/GB1433371A/en
Priority to FR7311971A priority patent/FR2179055B1/fr
Priority to DE2316891A priority patent/DE2316891C2/en
Application granted granted Critical
Publication of US3833363A publication Critical patent/US3833363A/en
Priority to US05/812,881 priority patent/USRE29946E/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material
    • Y10T29/49988—Metal casting

Definitions

  • the most common such alloy contains normally 6% aluminum, 2% tin, 4% zirconium and 2% molybdenum, and is known in the trade as the 6242 alloy.
  • Harris et a1 disclose a number of alloys of composition approaching the 6242 alloy, except that the alloys preferably contain about 0.1 to 2.0% silicon. Most of the alloys listed in the examples in the patent have a silicon content of 0.5%.
  • the apparent purpose of the patentees is to provide alloys which have improved creep properties; the patent does not discuss notch toughness.
  • An object of our invention is to provide a novel titanium-base alloy which contains alloying elements in a range similar to that described in the Peebles patent, but to which we add silicon in an amount to produce a silicon content in a narrow critical range above the residual level, whereby our alloy exhibits marked improvement over the 6242 alloy in tests for creep properties and stress rupture strength at elevated temperatures, without appreciable detriment to its other properties such as tensile strength, ductility or notch toughness.
  • a further object is to provide a method of improving the creep properties of an alloy otherwise similar to the Peebles alloy by adding silicon to the alloy in an amount to produce a silicon content in a narrow critical range above the residual level but below the range used in the prior art.
  • FIG. 1 is a graph showing the effect of silicon additions on the notch toughness of an alloy otherwise similar to the 6242 alloy.
  • FIG. 2 is a graph showing the effect of silicon additions on the creep and stress rupture strengths of an alloy otherwise similar to the 6242 alloy.
  • FIG. 3 is a graph showing the effect of silicon additions on the creep deformation of an alloy otherwise similar to the 6242 alloy.
  • the remainder of the alloy consists by weight of about 5.5 to aluminum, 1.7 to 2.3% tin, 0.7 to 5.0% zirconium, and 0.7 to 3.0% molybdenum, balance titanium and unavoidable impurities.
  • the preferred nominal analysis apart from silicon is similar to the commercial 6242 alloy, to wit 6% aluminum, 2% tin, 4% zirconium and 2% molybdenum, balance titanium.
  • the creep properties of the alloy fall off significantly as the silicon content is lowered nearer the residual level of 0.03%.
  • the upper limit of silicon in our alloy is defined by the level at which various properties, particularly notch toughness but surprisingly also creep, start to be affected detrimentally to an unacceptable degree.
  • Our tests show that the creep strength is maximum at a silicon content just below our upper limit, but the optimum silicon content of our alloy for a good combination of properties is about 0.08 to 0.09%. To demonstrate these phenomena, we performed a series of tests hereinafter described.
  • FIG. 1 shows graphically the effect of silicon on notch toughness. As long as the silicon content of the alloy does not exceed our upper limit of about 0.13%, the Charpy impact energy is not likely to drop below the generally acceptable minimum of 10 ft.-1bs.
  • FIG. 2 shows graphically results listed in Tables [11 and IV.
  • curve X we plot the average time to reach 0.1% deformation against silicon content. This curve shows a well-defined peak in the creep strength when the alloy has a silicon content of about 0.10%, but we prefer a slightly lower silicon content because other properties commence to be affected adversely at 0. silicon. Each point on the curve represents the average of at least two tests. The minimum acceptable time for 0.1% deformation under one current specification is 35 hours. The 6242 alloy, with only its residual silicon content, did not meet this specification, as indicated by point A on curve X. The alloy with a silicon content of 0.2% barely met this specification, as indicated by point B on the curve, but was deficient in other respects, as shown by the results of our notch toughness tests.
  • Curve Y in which we plot the time for rupture at l,000 F against silicon content, rises above the scale of the graph at our optimum silicon content, but thereafter drops precipitously.
  • FIG. 3 shows graphically additional information from Table III on the effect of silicon on creep deformation. This curve, in which we plot the permanent deformation at 100 hours against the silicon content, shows a minimum again near our optimum silicon content.
  • the points A and B in FIG. 3 correspond with the same points in FIG. 2.
  • a titanium-base alloy consisting by weight of about 5.5 to 6.5% aluminum, 1.7 to 2.3% tin, 0.7 to 5.0% zirconium, 0.7 to 3.0% molybdenum, silicon in an amount of at least 0.04% but less than 0.10%, and the balance titanium and unavoidable impurities, said alloy having a minimum Charpy V-notch impact energy of 10 ft.- lbs., and requiring a minimum time of 35 hours to reach 0.1% deformation when exposed to a stress of 35 Ksi at 950 F.
  • a method of improving the creep properties of a titanium base alloy which otherwise consists by weight of about 5.5 to 6.5% aluminum, 1.7 to 2.3% tin, 0.7 to 5.0% zirconium, 0.7 to 3.0% molybdenum, balance titanium and unavoidable impurities, and which has a residual silicon content of about 0.02 to 0.03%, said method comprising adding silicon to said alloy in an amount to produce a silicon content therein of at least 0.04% but less than 0.10% including the residual, whereby the alloy attains sufficient creep strength that specimens thereof require a minimum time of 35 hours to reach 0.1% deformation when exposed to a stress of 35 Ksi at 950 F, yet retain sufficient notch toughness to have a minimum Charpy V-notch impact energy of 10 ft.-lbs.-
  • a method as defined in claim 4 in which silicon is added to the alloy in an amount to produce a silicon content therein of 0.08 to 0.09%.

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)
  • Forging (AREA)
  • Manufacture And Refinement Of Metals (AREA)

Abstract

A titanium-base alloy consisting by weight of about 5.5 to 6.5% aluminum, 1.7 to 2.3% tin, 0.7 to 5.0% zirconium, 0.7 to 3.0% molybdenum, 0.04 to 0.13% silicon, and the balance titanium. The addition of silicon to the otherwise known alloy produces a marked improvement in creep properties without significant detrimental effect to other properties.

Description

United States Patent [1 1 Bomberger, Jr. et al. Sept. 3, 1974 [54] TITANIUM-BASE ALLOY AND METHOD OF 3,482,968 12/1969 Hunter 75/175.5 IMPROVING CREEP PROPERTIES 3,619,184 1 1/1971 Bomberger et a1. 75/175.5 3,756,810 9/1973 Parris et a1 75/1755 [75] Inventors: Howard B. Bomberger, Jr.,
Canfield; Stanley R. Seagle, Warren, OTHER UBLICATIONS both of 01119 AFML-TR-70-l25, Development of a 900 F. Tita- 73 Assignee: RMI Company, Niles, Ohio 22 g Alloy, Russo et y 1970. PP- & [22] Filed: Apr. 5, 1972 I [21] Appl. No.: 241,286 Primary ExaminerCharles N. Lovell Attorney, Agent, or FirmWalter P. Wood [52] US. Cl 75/l75.5, 148/325, 148/133 [51] Int. Cl. C22c /00 [57] ABSTRACT [58] Field of Search 75/ 175.5; 148/312i832553, A titaniunkbase alloy consisting by weight of about 5.5 to 6.5% aluminum, 1.7 to 2.3% tin, 0.7 to 5.0% 56 R f Ct d zirconium, 0.7 to 3.0% molybdenum, 0.04 to 0.13% 1 e erences I e silicon, and the balance titanium. The addition of sili- UNITED STATES PATENTS con to the otherwise known alloy produces a marked 2,893,864 7/1959 Harris et al. 75/1755 improvement in creep properties without significant 3,049,425 8/1962 Fentiman et al... 75/1755 d t i ntal ffect to other properties, 3,343,951 9/1967 Peebles 75/l75.5 3,378,368 4/1968 Minton et al. 75/1755 6 Claims, 3 Drawing Figures EFFECT OF SILICON CONTENT ON THE CREEP PROPERTIES I O I AVERAGE r/ue', Irours m 3 o OF Ti- 6242 MODIFICATIONS TIME FOR 0.! DEFORM4T/0N\ A7 oF 3 5 1129/ A MINIMUM ACCEPTAELE rm: SPECIFIED 40 FOR 9501- 35 KS/ AND 0./ OEFORAMT/OM 0B 30 I I RANGE OF PRESENT 20 I INVENTION I A I /0 I I I I I 1 l l I SILICON CONTENT, "/4
PATENIED ow .3 E 3 9 & iamkauu 52 R m9 Q 1 w l 3 on 539 t wmamak m Mai m IWP TITANIUM-BASE ALLOY AND METHOD OF IMPROVING CREEP PROPERTIES -which consists by weight of 5.5 to 6.5% aluminum, 1.7
to 2.3% tin, 0.7 to 5.0% zirconium, and 0.7 3.03.0 molybdenum, balance titanium and unavoidable impurities. The only other elements discussed in the patent specification as being present in the alloy are oxygen, nitrogen and carbon, the last two as interstitial impurities. Silicon is not discussed, but information available in the file history establishes that the patentee believed he should exclude silicon altogether from the alloy for the reason that as little as 0.15% silicon has a highly detrimental effect on notch toughness. In fact the patentee pointedly says silicon or equivalent compoundforming elements must be omitted from his alloys. Alloys of compositions within the range described in the Peebles patent have many useful properties and have achieved commercial success. The most common such alloy contains normally 6% aluminum, 2% tin, 4% zirconium and 2% molybdenum, and is known in the trade as the 6242 alloy. Harris et a1 disclose a number of alloys of composition approaching the 6242 alloy, except that the alloys preferably contain about 0.1 to 2.0% silicon. Most of the alloys listed in the examples in the patent have a silicon content of 0.5%. The apparent purpose of the patentees is to provide alloys which have improved creep properties; the patent does not discuss notch toughness.
I-leretofore there have been available (a) 6242 alloy to which no silicon is added intentionally, and (b) an alloy otherwise similar to 6242 to which silicon is added in an amount to produce a silicon content of 0.2%. Only the former is presently used commercially, since the latter showed unfavorable notch toughness properties. We have observed that the commercial 6242 alloy usually has a residual silicon content in the range of about 0.02 to 0.03%, even though no silicon is added intentionally. Some of the residual silicon comes from the sponge titanium, but more is likely to come from the master alloy used to introduce molybdenum to the sponge. Modern spectrographic techniques can determine silicon contents in this range in the titanium-base alloys to an accuracy of about i parts per million.
An object of our invention is to provide a novel titanium-base alloy which contains alloying elements in a range similar to that described in the Peebles patent, but to which we add silicon in an amount to produce a silicon content in a narrow critical range above the residual level, whereby our alloy exhibits marked improvement over the 6242 alloy in tests for creep properties and stress rupture strength at elevated temperatures, without appreciable detriment to its other properties such as tensile strength, ductility or notch toughness.
A further object is to provide a method of improving the creep properties of an alloy otherwise similar to the Peebles alloy by adding silicon to the alloy in an amount to produce a silicon content in a narrow critical range above the residual level but below the range used in the prior art.
In the drawing:
FIG. 1 is a graph showing the effect of silicon additions on the notch toughness of an alloy otherwise similar to the 6242 alloy.
FIG. 2 is a graph showing the effect of silicon additions on the creep and stress rupture strengths of an alloy otherwise similar to the 6242 alloy; and
FIG. 3 is a graph showing the effect of silicon additions on the creep deformation of an alloy otherwise similar to the 6242 alloy.
According to our invention, we formulate alloys of a composition within the range of the Peebles patent and we can employ similar techniques, except that we add silicon to the alloy in an amount sufficient to produce a silicon content therein in a critical range of about 0.04 to 0.13% by weight, including the residual. Like Peebles, the remainder of the alloy consists by weight of about 5.5 to aluminum, 1.7 to 2.3% tin, 0.7 to 5.0% zirconium, and 0.7 to 3.0% molybdenum, balance titanium and unavoidable impurities. The preferred nominal analysis apart from silicon is similar to the commercial 6242 alloy, to wit 6% aluminum, 2% tin, 4% zirconium and 2% molybdenum, balance titanium.
The creep properties of the alloy fall off significantly as the silicon content is lowered nearer the residual level of 0.03%. The upper limit of silicon in our alloy is defined by the level at which various properties, particularly notch toughness but surprisingly also creep, start to be affected detrimentally to an unacceptable degree. Our tests show that the creep strength is maximum at a silicon content just below our upper limit, but the optimum silicon content of our alloy for a good combination of properties is about 0.08 to 0.09%. To demonstrate these phenomena, we performed a series of tests hereinafter described.
COMPOSITION AND PREPARATION OF SPECIMENS To conduct these tests, we formulated several 25- pound ingots of a composition within the range of the Peebles patent, except that we added silicon in varying amounts. Table I, which follows, lists the analyses of these ingots. Heat No. 20039 is actually the commercial 6242 alloy with its residual silicon content of 0.03% and is outside the lower limit of our invention. The constituents other than silicon fall within current commercial specifications for the 6242 alloy in all the Heats except No. 21006, which is low in molybdenum.
Table I CHEMICAL COMPOSITION OF Ti-6242 MODIFICATIONS Composition, '/1
Heat No. Al Sn Zr Mn Fe I O N C Si Table I Continued CHEMICAL COMPOSITION OF Ti-6242 MODIFICATIONS Com position,
Heat No. A1 Sn Zr Mn Fe O N C Si Spec 1" Max 6.5 2.25 4.5 2.20 25 .15 .04 .04 (3) Min 5.5 1.75 3.5 1.80
Spec 2 Max 6.5 2.20 4.4 2.20 25 .15 .05 .05 (3) Min 5.5 1.80 3.6 1.80
"'Pralt 6: Whitney Specification 1209D (February 15. 1971) 'Gencru1 Electric Specification C50TF39-1T (March 18. I971) (31None Specified TENSILE AND NOTCH TOUGHNESS TESTS We conducted tensile tests on 0.250-inch gauge diameter machined specimens obtained from the bars described, both at room temperature and 900 F. We tested each specimen at 0.005 in./in./min. through the yield strength and thereafter at a crosshead speed of 0.2 in./mi n. until failure. We conducted notch toughness tests using the standard ASTM V-notch Charpy test at F. Values of 10 ft.-lbs. or greater in the V- notch Charpy test are generally considered acceptable for titanium-base alloys. Table II, which follows, lists the results of the tensile and notch toughness tests.
Table II As Table II shows, addition of silicon produces a modest increase in the yield strength of the alloy and a correspondingly small but acceptable loss in ductility. The notch toughness, as measured by impact energy, decreases as more silicon is added, but does not decrease below an acceptable value as long as the silicon content remains within the critical limits of our invention. While our invention results in a minor loss in notch toughness, it achieves a major gain in needed creep strength, as hereinafter demonstrated.
FIG. 1 shows graphically the effect of silicon on notch toughness. As long as the silicon content of the alloy does not exceed our upper limit of about 0.13%, the Charpy impact energy is not likely to drop below the generally acceptable minimum of 10 ft.-1bs.
CREEP AND STRESS RUPTURE TESTS We conducted creep tests on the specimens by exposing them to a stress of 35 Ksi at 950 F. We recorded both the time at which each specimen reached 0.1% deformation and the extent of deformation after 100 hours. We used an optical extensometer system to measure the deformation. We also conducted tensile tests on the specimens following creep exposure. Table 111, which follows, lists the results.
TENSILE AND NOTCH TOUGHNESS PROPERTIES OF Ti-6242 MODIFICATIONS impact 72F 900F Heat" Si energy UTS YS El RA UTS YS E1 RA No. ft-lbs Ksi Ksi "/1 Ksi Ksi "/1 71 k-inch bar. Heat treatment: (Beta transus 25F)l hr-AC; 1 F-8 hrAC 'Standard ASTM Charpy V-Notch test I Low Molybdenum (1.5%)
l wflm I TW'VWW' 7 Table III CREEP PROPERTIES OF ROLLED /ii-1NCH BAR OF Ti6242 MODIFICATIONS Creep Results Tensile Properties I Total Time Total Def at at 72F Heafl Si Time for def 100 hr. UTS YS El RA No. 71 hr. 0.154 "/1 Ksi Ksi 11 27 20039 .030 No Exposure 162 150 16.5 45.0 114 18 .21 .19 I63 148 17.0 40.3 14 .19 .18 163 148 17.0 42.9
Table 111- Continued CREEP PROPERTIES OF ROLLED "Ya-INCH BAR OF Ti-6242 MODIFICATIONS Creep Results Tensile Properties Total Time Total Def at at 72F Heat Si Time for def 100 hr. UTS YS El RA No. /1 hr. 0.17! /1 Ksi Ksi 7! 21004 .056 No Exposure 164 151 15.0 40.3
99 25 .16 .16 166 151 16.0 36.1 98 I40 .08 .08 171 155 16.5 35.0 91 37 .12 .12 162 146 15.0 34.8 20043 .080 No Exposure 167 152 14.0 35.5 98 60 .12 .12 170 155 16.5 34.3 91 120 .09 .09 172 152 15.0 32.9 21005 .090 No Exposure 163 147 16.0 40.1 100 44 .13 .13 164 151 17.5 39.1 103 200 .06 .05 161 141 10.0 15.5 27277 .200 No Exposure 167 154 12.5 33.9 107 43 .15 .14 170 159 15.0 24.6 108 35 .13 .13 168 156 15.0 30.8
at 1,000 F using stresses of 70 Ksi and 75 Ksi. Table IV, which follows, lists the results.
Table IV I EFFECT OF SILICON ADDITIONS ON STRESS-RUPTURE 22 Ti-6242 MODIFICATIONS 'loud increased to 75 Ksi at 281 hrs and failure occurred after a combined time of 387 hrs.
loud increased to 75 Ksi at 282 hours and failure occurred after a combined time of 342 hrs WlFrig'ar {emailing Brie stfess rupture machine.
hr-AC.
FIG. 2 shows graphically results listed in Tables [11 and IV. In curve X we plot the average time to reach 0.1% deformation against silicon content. This curve shows a well-defined peak in the creep strength when the alloy has a silicon content of about 0.10%, but we prefer a slightly lower silicon content because other properties commence to be affected adversely at 0. silicon. Each point on the curve represents the average of at least two tests. The minimum acceptable time for 0.1% deformation under one current specification is 35 hours. The 6242 alloy, with only its residual silicon content, did not meet this specification, as indicated by point A on curve X. The alloy with a silicon content of 0.2% barely met this specification, as indicated by point B on the curve, but was deficient in other respects, as shown by the results of our notch toughness tests. Curve Y, in which we plot the time for rupture at l,000 F against silicon content, rises above the scale of the graph at our optimum silicon content, but thereafter drops precipitously. FIG. 3 shows graphically additional information from Table III on the effect of silicon on creep deformation. This curve, in which we plot the permanent deformation at 100 hours against the silicon content, shows a minimum again near our optimum silicon content. The points A and B in FIG. 3 correspond with the same points in FIG. 2.
The foregoing results were altogether unexpected to us. Our expectation had been that the relation between LII the time to reach 0.1% defonnation and the silicon content would follow approximately a straight line between points A and B of FIG. 2 instead of reaching an intermediate peak. Thus our invention provides an alloy of dramatically improved creep strength compared with either the 6242 al1oy or an otherwise similar alloy containing 0.2 percent silicon known previously. We maintain an acceptable level of notch toughness, but we trade a little in this respect for a much needed increase in creep strength.
We claim:
1. A titanium-base alloy consisting by weight of about 5.5 to 6.5% aluminum, 1.7 to 2.3% tin, 0.7 to 5.0% zirconium, 0.7 to 3.0% molybdenum, silicon in an amount of at least 0.04% but less than 0.10%, and the balance titanium and unavoidable impurities, said alloy having a minimum Charpy V-notch impact energy of 10 ft.- lbs., and requiring a minimum time of 35 hours to reach 0.1% deformation when exposed to a stress of 35 Ksi at 950 F.
2. An alloy as defined in claim 1 in which the silicon content is within the range of 0.08 to 0.09% by weight.
3. An alloy as defined in claim 1 of a weight composition approximately 6% aluminum, 2% tin, 4% zirconium, 2% molybdenum, 0.08 to 0.09% silicon, balance titanium and unavoidable impurities.
4. A method of improving the creep properties of a titanium base alloy which otherwise consists by weight of about 5.5 to 6.5% aluminum, 1.7 to 2.3% tin, 0.7 to 5.0% zirconium, 0.7 to 3.0% molybdenum, balance titanium and unavoidable impurities, and which has a residual silicon content of about 0.02 to 0.03%, said method comprising adding silicon to said alloy in an amount to produce a silicon content therein of at least 0.04% but less than 0.10% including the residual, whereby the alloy attains sufficient creep strength that specimens thereof require a minimum time of 35 hours to reach 0.1% deformation when exposed to a stress of 35 Ksi at 950 F, yet retain sufficient notch toughness to have a minimum Charpy V-notch impact energy of 10 ft.-lbs.-
5. A method as defined in claim 4 in which silicon is added to the alloy in an amount to produce a silicon content therein of 0.08 to 0.09%.
6. A method as defined in claim 4 in which the alloy otherwise consists by weight of approximately 6% aluminum, 2% tin, 4% zirconium, 2% molybdenum, balance titanium and unavoidable impurities.
UNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION Patent NO. Dated S pt 5,
Inventor) Howard B. Bomberger, Jr. et a1.
It is certified that error appears in the aboveidentified patent and that said Letters Patent are hereby corrected as 'shown below:
Column 1, line 15, "0.7 5.03.05" should read Signed and sealed this 10th day of December 1974.
(SEAL) Attest:
McCOY M, GIBSON JR.. C; MARSHALL DANN Atte'sting Officer Commissioner of Patents F ORM I o-1050 (10-69) v USCOMM-DC 60376-P69 ufs. GOVERNMENT ranmuc OFFICE: 93 o

Claims (5)

  1. 2. An alloy as defined in claim 1 in which the silicon content is within the range of 0.08 to 0.09% by weight.
  2. 3. An alloy as defined in claim 1 of a weight composition approximately 6% aluminum, 2% tin, 4% zirconium, 2% molybdenum, 0.08 to 0.09% silicon, balance titanium and unavoidable impurities.
  3. 4. A method of improving the creep properties of a titanium base alloy which otherwise consists by weight of about 5.5 to 6.5% aluminum, 1.7 to 2.3% tin, 0.7 to 5.0% zirconium, 0.7 to 3.0% molybdenum, balance titanium and unavoidable impurities, and which has a residual silicon content of about 0.02 to 0.03%, said method comprising adding silicon to said alloy in an amount to produce a silicon content therein of at least 0.04% but less than 0.10% including the residual, whereby the alloy attains sufficient creep strength that specimens thereof require a minimum time of 35 hours to reach 0.1% deformation when exposed to a stress of 35 Ksi at 950* F, yet retain sufficient notch toughness to have a minimum Charpy V-notch impact energy of 10 ft.-lbs.
  4. 5. A method as defined in claim 4 in which silicon is added to the alloy in an amount to produce a silicon content therein of 0.08 to 0.09%.
  5. 6. A method as defined in claim 4 in which the alloy otherwise consists by weight of approximately 6% aluminum, 2% tin, 4% zirconium, 2% molybdenum, balance titanium and unavoidable impurities.
US00241286A 1972-04-05 1972-04-05 Titanium-base alloy and method of improving creep properties Expired - Lifetime US3833363A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US00241286A US3833363A (en) 1972-04-05 1972-04-05 Titanium-base alloy and method of improving creep properties
CA166,903A CA966334A (en) 1972-04-05 1973-03-23 Titanium-base alloy and method of improving creep properties
GB1573573A GB1433371A (en) 1972-04-05 1973-04-02 Titanium-base alloy and method of improving its creep properties
FR7311971A FR2179055B1 (en) 1972-04-05 1973-04-03
DE2316891A DE2316891C2 (en) 1972-04-05 1973-04-04 Process for processing a titanium alloy
US05/812,881 USRE29946E (en) 1972-04-05 1977-07-05 Titanium-base alloy and method of improving creep properties

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00241286A US3833363A (en) 1972-04-05 1972-04-05 Titanium-base alloy and method of improving creep properties

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US05/812,881 Reissue USRE29946E (en) 1972-04-05 1977-07-05 Titanium-base alloy and method of improving creep properties

Publications (1)

Publication Number Publication Date
US3833363A true US3833363A (en) 1974-09-03

Family

ID=22910057

Family Applications (2)

Application Number Title Priority Date Filing Date
US00241286A Expired - Lifetime US3833363A (en) 1972-04-05 1972-04-05 Titanium-base alloy and method of improving creep properties
US05/812,881 Expired - Lifetime USRE29946E (en) 1972-04-05 1977-07-05 Titanium-base alloy and method of improving creep properties

Family Applications After (1)

Application Number Title Priority Date Filing Date
US05/812,881 Expired - Lifetime USRE29946E (en) 1972-04-05 1977-07-05 Titanium-base alloy and method of improving creep properties

Country Status (5)

Country Link
US (2) US3833363A (en)
CA (1) CA966334A (en)
DE (1) DE2316891C2 (en)
FR (1) FR2179055B1 (en)
GB (1) GB1433371A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4229216A (en) * 1979-02-22 1980-10-21 Rockwell International Corporation Titanium base alloy
US4253873A (en) * 1978-07-28 1981-03-03 Tokyo Shibaura Denki Kabushiki Kaisha Titanium-based alloy having high mechanical strength
US4309226A (en) * 1978-10-10 1982-01-05 Chen Charlie C Process for preparation of near-alpha titanium alloys
US4422887A (en) * 1980-09-10 1983-12-27 Imi Kynoch Limited Heat treatment
JPH01242743A (en) * 1988-03-23 1989-09-27 Nkk Corp Heat-resistant titanium alloy
US5922274A (en) * 1996-12-27 1999-07-13 Daido Steel Co., Ltd. Titanium alloy having good heat resistance and method of producing parts therefrom
US6245428B1 (en) 1998-06-10 2001-06-12 Cpfilms Inc. Low reflective films
US6284070B1 (en) * 1999-08-27 2001-09-04 General Electric Company Heat treatment for improved properties of alpha-beta titanium-base alloys
US10913991B2 (en) 2018-04-04 2021-02-09 Ati Properties Llc High temperature titanium alloys
US11001909B2 (en) 2018-05-07 2021-05-11 Ati Properties Llc High strength titanium alloys
US11268179B2 (en) 2018-08-28 2022-03-08 Ati Properties Llc Creep resistant titanium alloys

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1492262A (en) * 1975-05-07 1977-11-16 Imp Metal Ind Kynoch Ltd Titanium base alloy
CN113943877A (en) * 2021-10-18 2022-01-18 忠世高新材料股份有限公司 Preparation method of Ti6242s alloy cast ingot

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2893864A (en) * 1958-02-04 1959-07-07 Harris Geoffrey Thomas Titanium base alloys
US3049425A (en) * 1958-11-14 1962-08-14 Ici Ltd Alloys
US3343951A (en) * 1963-10-17 1967-09-26 Titanium Metals Corp Titanium base alloy
US3378368A (en) * 1965-01-04 1968-04-16 Imp Metal Ind Kynoch Ltd Titanium-base alloys
US3482968A (en) * 1967-08-08 1969-12-09 Titanium Metals Corp Titanium base alloys of high strength at atmospheric and elevated temperatures
US3619184A (en) * 1968-03-14 1971-11-09 Reactive Metals Inc Balanced titanium alloy
US3756810A (en) * 1972-04-04 1973-09-04 Titanium Metals Corp High temperature titanium alloy

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1156397A (en) 1963-10-17 1969-06-25 Contimet Gmbh Improved Titanium Base Alloy
DE1558461B1 (en) * 1966-06-20 1971-08-26 Contimet Gmbh USE OF A TITANIUM ALLOY FOR OBJECTS THAT REQUIRE LOW SPECIFIC WEIGHT HIGH TEMPERATURE STRENGTH CREEP STRENGTH GOOD TOUGHNESS WELDABILITY AND DEFORMABILITY AND WITHSTAND LOW TEMPERATURE DEMANDS

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2893864A (en) * 1958-02-04 1959-07-07 Harris Geoffrey Thomas Titanium base alloys
US3049425A (en) * 1958-11-14 1962-08-14 Ici Ltd Alloys
US3343951A (en) * 1963-10-17 1967-09-26 Titanium Metals Corp Titanium base alloy
US3378368A (en) * 1965-01-04 1968-04-16 Imp Metal Ind Kynoch Ltd Titanium-base alloys
US3482968A (en) * 1967-08-08 1969-12-09 Titanium Metals Corp Titanium base alloys of high strength at atmospheric and elevated temperatures
US3619184A (en) * 1968-03-14 1971-11-09 Reactive Metals Inc Balanced titanium alloy
US3756810A (en) * 1972-04-04 1973-09-04 Titanium Metals Corp High temperature titanium alloy

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
AFML TR 70 125, Development of a 900 F. Titanium Alloy, Russo et al., July 1970, pp. 5 33 & 84 89. *

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4253873A (en) * 1978-07-28 1981-03-03 Tokyo Shibaura Denki Kabushiki Kaisha Titanium-based alloy having high mechanical strength
US4309226A (en) * 1978-10-10 1982-01-05 Chen Charlie C Process for preparation of near-alpha titanium alloys
US4229216A (en) * 1979-02-22 1980-10-21 Rockwell International Corporation Titanium base alloy
US4422887A (en) * 1980-09-10 1983-12-27 Imi Kynoch Limited Heat treatment
JPH01242743A (en) * 1988-03-23 1989-09-27 Nkk Corp Heat-resistant titanium alloy
US5922274A (en) * 1996-12-27 1999-07-13 Daido Steel Co., Ltd. Titanium alloy having good heat resistance and method of producing parts therefrom
US6284071B1 (en) 1996-12-27 2001-09-04 Daido Steel Co., Ltd. Titanium alloy having good heat resistance and method of producing parts therefrom
US6245428B1 (en) 1998-06-10 2001-06-12 Cpfilms Inc. Low reflective films
US6284070B1 (en) * 1999-08-27 2001-09-04 General Electric Company Heat treatment for improved properties of alpha-beta titanium-base alloys
US10913991B2 (en) 2018-04-04 2021-02-09 Ati Properties Llc High temperature titanium alloys
US11384413B2 (en) 2018-04-04 2022-07-12 Ati Properties Llc High temperature titanium alloys
US11001909B2 (en) 2018-05-07 2021-05-11 Ati Properties Llc High strength titanium alloys
US11674200B2 (en) 2018-05-07 2023-06-13 Ati Properties Llc High strength titanium alloys
US12071678B2 (en) 2018-05-07 2024-08-27 Ati Properties Llc High strength titanium alloys
US11268179B2 (en) 2018-08-28 2022-03-08 Ati Properties Llc Creep resistant titanium alloys
US11920231B2 (en) 2018-08-28 2024-03-05 Ati Properties Llc Creep resistant titanium alloys

Also Published As

Publication number Publication date
FR2179055A1 (en) 1973-11-16
USRE29946E (en) 1979-03-27
CA966334A (en) 1975-04-22
DE2316891C2 (en) 1983-12-15
FR2179055B1 (en) 1977-04-29
DE2316891A1 (en) 1973-10-18
GB1433371A (en) 1976-04-28

Similar Documents

Publication Publication Date Title
US3833363A (en) Titanium-base alloy and method of improving creep properties
CA2014970C (en) Oxidation resistant titanium-base alloy
US4842819A (en) Chromium-modified titanium aluminum alloys and method of preparation
US4229216A (en) Titanium base alloy
US4842820A (en) Boron-modified titanium aluminum alloys and method of preparation
EP0388527B1 (en) Improved titanium aluminide alloys
US4842817A (en) Tantalum-modified titanium aluminum alloys and method of preparation
EP0150456A2 (en) Low temperature underaging of lithium bearing aluminum alloy
US4836983A (en) Silicon-modified titanium aluminum alloys and method of preparation
US4087292A (en) Titanium base alloy
US4857268A (en) Method of making vanadium-modified titanium aluminum alloys
JP2644027B2 (en) Titanium alloy
EP0363598B1 (en) Heat-resistant titanium-aluminium alloy with a high fracture toughness at room temperature and with good oxidation resistance and strength at high temperatures
US3582320A (en) Cobalt base alloy
US3756810A (en) High temperature titanium alloy
US3720509A (en) Nickel base alloy
US3038798A (en) Titanium-niobium alloys
EP0476043B1 (en) Improved nickel aluminide alloy for high temperature structural use
US3627511A (en) High chromium alloys of improved workability
US3188206A (en) Columbium alloy
US4902474A (en) Gallium-modified titanium aluminum alloys and method of preparation
EP0146288B1 (en) high strength titanium alloy for use at elevated temperatures
US3166414A (en) Tantalum base alloys
US3061427A (en) Alloy of titanium
JPH0754081A (en) High corrosion-resistant titanium alloy excellent in cold processibility and weldability