US3526499A - Nickel base alloy having improved stress rupture properties - Google Patents

Nickel base alloy having improved stress rupture properties Download PDF

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US3526499A
US3526499A US662305A US3526499DA US3526499A US 3526499 A US3526499 A US 3526499A US 662305 A US662305 A US 662305A US 3526499D A US3526499D A US 3526499DA US 3526499 A US3526499 A US 3526499A
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stress rupture
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Richard J Quigg
Henry E Collins
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Northrop Grumman Space and Mission Systems Corp
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TRW Inc
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    • 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

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  • This invention relates to nickel base superalloys par- A mFkel Superancy Partlcularb' for use 15 ticularly useful for jet engine parts including blades, vanes,- turbme englne blades because of P vastly F Y buckets, and the like, the alloys consisting essentially of stress rupture properties and other physical characteristics, the following ingredients: the alloy containing 0.05 to 0.25% carbon, from 5 to Percent 8% chromium, from 0.5 to 4.0% molybdenum, from 0.5 Carbon 0.05025 to 2.0% titanium, from 4.5 to 6.5% aluminum, from 1 20 Chromium to 10% cobalt, from 4 to 8% tungsten, from 0 to 2% Molybdenum rhenium, from 0.2 to 3.0% hafnium, from 0.01 to 0.50% Titanium zirconium, from 0.005 to 0.200% boron, from 6 to 10% Aluminum tantalum, from 0 to
  • the physical testing of the samples was carried out in the following way.
  • the stress rupture testing was performed in air and in commercially pure argon atmosphere.
  • the chambers were flushed with argon before heating and then the atmosphere was maintained after the test until the specimen was cooled to less than 1,000 F.
  • Charpy impact testing was performed on a standard impact tester in accordance with ASTM standards.
  • the pendulum velocity was 17 feet per second.
  • the test specimens were unnotched with dimensions of 2.165 inches by 0.394 inch by 0.394 inch, and were machined from the as cast material.
  • Thermal fatigue testing was performed in the following manner. The specimens were heated with an oxyacetylene fiame, the specimens being precision cast wedges 2 inches long, inch at the large end and inch at the pointed end, and inch wide. Some specimens were run at a test temperature of 2,100 F. and others at 1,875 F. Temperature measurements were made with an optical pyrometer. A reading was made after the first ten cycles, at 20 cycle intervals up to 50 cycles, and at 50 cycle intervals thereafter to the completion of the examination interval. The cycle intervals for crack examination varied for the two test temperatures. At 2,100" F.
  • the specimens were examined at 30 cycle intervals up to 150 cycles, at 50 cycle intervals up to 400 cycles, at cycle intervals up to 1,500 cycles, at 200 cycle intervals up to 3,100 cycles, and at 500 cycle intervals thereafter to failure.
  • the number of cycles to first crack detection were recorded.
  • the specimens were examined at 50 cycle intervals up to 200 cycles, at 100 cycle intervals up to 1,000 cycles, at 200 cycle intervals up to 2,400 cycles, and 400 cycle intervals thereafter, to a maximum of 4,000 cycles.
  • oxidation testing Two methods were employed to evaluate the corrosion resistance of the alloys, consisting of oxidation tests and hot corrosion tests.
  • the specimens utilized were 0.5 inch diameter cylinders, /2 inch long.
  • the specimens were placed in high purity alumina crucibles and weighed before heating.
  • the specimens in the crucibles were then heated in air at one of the test temperatures and times.
  • a new specimen was used for each test condition.
  • the crucibles were covered to prevent loss of scale due to flaking during cooling. After cooling, the crucible and contents were then weighed to determine the change in weight due to oxidation.
  • Hot corrosion testing was done by means of a gravimetric method using the same size specimen as the oxidation tests. The specimens were weighed and then partially covered with a 1% sodium chloride, 99% sodium 94,000 p.s.i.
  • IV-Y 1 4, 100 5, 100 2, 100
  • alloy VI-A has the best high temperature properties of the three. Its stress rupture life is the highest and represents approximately a 50 F. increase in temperature over the lives of present-day high strength nickel base alloys. Its tensile strength and impact properties are comparable with suchalloys. Its ductility appears to be adequate and it does not appear to suffer a severe reduction in tensile ductility in the 1,400 F. to 1,600? F. temperature range. In addition, alloy VI-A has a good thermal fatigue'and corrosive resistance for a high strength alloy and does not appear to suffer from microstructural instability, that is, formation of sigma, Laves, or mu phase formation.
  • a nickel-base alloy having improved stress rupture properties consisting essentiallyofthe following in- Essentially..thebalancee the sum of the molybdenum, tungsten, and tantalum contents being in the range from 15 to 20%, the tungsten being present in an amount greater than the molybdenum but less than the amount of tantalum, the stress rupture life of the alloy at an applied stress of 15,000 p.s.i. at a temperature of 2,000 F. being at least 20 hours.
  • the sum of the molybdenum, tungsten, and tantalum contents being in the range from 15 to 20%, the tungsten being present in an amount greater than the molybdenum but less than the amount of tantalum, the stress rupture lift of the alloy at an applied stress of 15,000 p.s.i. at a temperature of 2,000 F. being at least 20 hours.
  • the sum of the molybdenum, tungsten, and tantalum contents being in the range from 15 to 20% the stress rupture life of the alloy at an applied stress of 15,000 p.s.i. at a temperature of 2,000 F. being at least 20 hours.
  • Nickel (1) 1 Essentially the balance.
  • said alloy having a stress rupture life at an applied stress of 15,000 p.s.i. at a temperature of 2,000 F. of at least 20 hours.
  • said alloy having a stress rupture life of at least 20 hours at an applied stress of 15,000 p.s.i. and at a temperature of 2,000 F.
  • said alloy having a stress rupture life of at least 20 hours at an applied stress of 15,000 p.s.i. and at a temperature of 2,000 F.
  • a turbine engine blade composed of the alloy of claim 1.
  • a turbine engine blade composed of the alloy of claim 2.
  • a turbine engine blade composed of the alloy of claim 3.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
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Description

United States Patent 3 526 499 NICKEL BASE ALL OY HAVING IMPROVED STRESS RUPTURE PROPERTIES Richard J. Quigg, South Russell, and Henry E. Collins,
gi zf g ghgggb fz fi g to TRW Cleveland 5 about to hours. In contrast, the alloys of the present No Drawing. Filed Aug. 22, 1967, Ser. No. 662,305 invention have a stress rupture life of at least hours Int. C1, C22(: 19/00 under the same conditions and consistently exceed 30 US. Cl. 75171 10 Claims hours. The most preferred embodiments of the invention 10 have an average stress rupture life under these conditions in excess of 60 hours.
ABSTRACT OF THE DISCLOSURE SUMMARY OF THE INVENTION This invention relates to nickel base superalloys par- A mFkel Superancy Partlcularb' for use 15 ticularly useful for jet engine parts including blades, vanes,- turbme englne blades because of P vastly F Y buckets, and the like, the alloys consisting essentially of stress rupture properties and other physical characteristics, the following ingredients: the alloy containing 0.05 to 0.25% carbon, from 5 to Percent 8% chromium, from 0.5 to 4.0% molybdenum, from 0.5 Carbon 0.05025 to 2.0% titanium, from 4.5 to 6.5% aluminum, from 1 20 Chromium to 10% cobalt, from 4 to 8% tungsten, from 0 to 2% Molybdenum rhenium, from 0.2 to 3.0% hafnium, from 0.01 to 0.50% Titanium zirconium, from 0.005 to 0.200% boron, from 6 to 10% Aluminum tantalum, from 0 to 2% columbium, from 0 to 1% vana- Cobalt 140 dium, and the balance being essentially nickel, all per- 25 Tungsten centages being by weight. Rhem-um Hafnium 0.2-3.0 Zirconium 0.01-0.50 The invention described herein was made in the per- Boron O'OOLO'ZOO Tantalum 6-10 formance of work under a NASA contract and is sub ect Columbium 0-2 to the provisions of Section 305 of the National Aero- Vanadium nautics and Space Act of 1958, Public Law 85-568 (72 Nickel Stat. 435; 42 U.S.C. 2457). 1E Pi g;
Rights to practice the invention for any use primarily ssen la y e a related to aeronautical and space applications are availa- The Sum of e molybdenum, tungsten, and tantalum ble through the National Aeronautics and Space Adminis- :Qntents Should be? 1114116 range 'P about 15 to 20%, nation with the tungsten being present in an amount greater than the molybdenum but less than the amount of tan- BACKGROUND OF THE INVENTION 40 talllm- Within the broader ranges specified above, particularly The present invention is in the field of nickel base improved alloys are provided with the following superalloys particularly useful in the manufacture of turanalyses: 'bine blading for jet aircraft. These alloys are capable Percent of maintaining their strength and their creep, oxidation, Carbon 0.10-0.20 and thermal fatigue resistance at high temperatures while Chromium 5-7 still evidencing a reasonable amount of ductility. Molybdenum 1-3 Titanium 0.75-1.50 DESCRIPTION OF THE PRIOR ART Alummum Cobalt 2-8 The art of nickel base superalloys for jet engine blades Tungsten 5-7 has been developed quite substantially in recent years. Rhen um 0-1 Typical among the US. patents in this field are the folloW- Hafnlum 0.3-2.5 ing: 2,570,193; 2,945,758; 2,951,757; 2,974,036; 2,977,- Zirconium 0.02-0.30 222; 3,061,426; 3,164,465; 3,166,412. 5 Bor n 0.010.1 One of the most recent alloys of this type containing Tantalum 7-9 substantial amounts of refractory metals is described in Columbium 0-1 Freche et al. US. Pat. 3,276,866, issued Oct. 4, 1966. Vanadlum 0-1 Commercially available nickel base superalloys are Nickel (1) represented in the following table: 1 Essentially the balance.
TABLE 1.NOMINAL COMPOSITIONS OF CONTEMPORARY NICKEL-BASE SUPERALLOYS Cast or Alloy wrought C Cr Mo Ti A1 00 W Zr B Ta Cb V Fe Nimonie W 0.04 20.0 InconelX W 0. 04 15.0 Waspaloy W 0.08 19.5 0. 09 10.0 0.08 15.0 0.12 12.5 0.13 10.0 0.15 9.0 0.125 6.0 0.125 6.0
3,526,499 Patented Sept. 1, 1970 While the art is thus quite highly developed, the stress rupture properties of these alloys can stand a substantial amount of improvement. To our knowledge, the stress rupture life of these alloys at an applied stress of 15,000 psi. and at a temperature of 2,000 F. does not exceed 3 DESCRIPTION OF THE PREFERRED EMBODIMENT The alloys of the present invention use substantial amounts of solid solution strengtheners such as tantalum, tungsten, and molybdenum in proper balance to achieve strength properties without depreciating the oxidation resistance of the alloy. The addition of hafnium has been found to be particularly effective in securing the properties desired. The addition of rhenium is optional but may be used to improve corrosive properties of the alloy in some instances.
In order to illustrate more completely the substantial improvements in physical properties which are achieved by the alloys of the present invention, we are listing below typical stress rupture properties of existing alloys under various conditions:
TABLE 2.STRESS RUPTURE PROPERTIES OF CONTEMPORARY ALLOYS (A) 1,800 F. tests Hours of life for given stress, psi.
(B) 1,900" F. tests Hours of life for given stress Wrought niekel-base alloys, Udimet Cast nickel-base alloys:
Ineo 713 0 After considerable experimentation, we determined that the three best alloy compositions coming within the broader analyses recited previously were the following, wh ch we called alloys IV-Y, VI-A and VI-D:
TABLE 3 Alloy IV-Y: Percent Carbon 0.15 Chromium 6.0 Molybdenum 2.0 Titanium 1.0 Aluminum 5.4 Cobalt 5.0 Tungsten 5.5 Rhenium 1.0 Hafnium 2.0 Zirconium 0.03
Boron 0.02 Tantalum 8.0
Columbium 1.0 Nickel Balance Alloy VI-A:
Carbon 0.13 Chromium 6.1 Molybdenum 2.0 Titanium 1.0 Aluminum 5.4 Cobalt 7.5 Tungsten 5.8 Rhenium 0.5 Hafnium 0.4 Zirconium 0.13 Boron 0.02
Tantalum 9.0 Columbium 0.5
Nickel Balance 4 Alloy VI-D:
Carbon 0.15 Chromium 5.4 Molybdenum 2.0 Titanium 1.0 Aluminum 5.4 Cobalt 5.0 Tungsten 6.0 Hafnium 1.75 Zirconium 0.08 Boron 0.02 Tantalum 8.5 Columbium 0.5 Vanadium 0.5 Nickel Balance The average stress rupture life of these three alloys, at 2,000 F. and at an applied stress of 15,000 pounds per square inch was 41.3 hours for alloy IV-Y, 62.9 hours for alloy VI-A, and 67.3 hours for alloy VI-D.
The physical testing of the samples was carried out in the following way. The stress rupture testing was performed in air and in commercially pure argon atmosphere. In the argon tests, the chambers were flushed with argon before heating and then the atmosphere was maintained after the test until the specimen was cooled to less than 1,000 F.
Tensile tests were performed on the specimens as cast and after heat treatment consisting of a 300 hour age at 1,875 F. in an argon atmosphere.
Charpy impact testing was performed on a standard impact tester in accordance with ASTM standards. The pendulum velocity was 17 feet per second. The test specimens were unnotched with dimensions of 2.165 inches by 0.394 inch by 0.394 inch, and were machined from the as cast material.
Thermal fatigue testing was performed in the following manner. The specimens were heated with an oxyacetylene fiame, the specimens being precision cast wedges 2 inches long, inch at the large end and inch at the pointed end, and inch wide. Some specimens were run at a test temperature of 2,100 F. and others at 1,875 F. Temperature measurements were made with an optical pyrometer. A reading was made after the first ten cycles, at 20 cycle intervals up to 50 cycles, and at 50 cycle intervals thereafter to the completion of the examination interval. The cycle intervals for crack examination varied for the two test temperatures. At 2,100" F. the specimens were examined at 30 cycle intervals up to 150 cycles, at 50 cycle intervals up to 400 cycles, at cycle intervals up to 1,500 cycles, at 200 cycle intervals up to 3,100 cycles, and at 500 cycle intervals thereafter to failure. The number of cycles to first crack detection were recorded. At 1,875 F., the specimens were examined at 50 cycle intervals up to 200 cycles, at 100 cycle intervals up to 1,000 cycles, at 200 cycle intervals up to 2,400 cycles, and 400 cycle intervals thereafter, to a maximum of 4,000 cycles.
Two methods were employed to evaluate the corrosion resistance of the alloys, consisting of oxidation tests and hot corrosion tests. For oxidation testing, the specimens utilized were 0.5 inch diameter cylinders, /2 inch long. The specimens were placed in high purity alumina crucibles and weighed before heating. The specimens in the crucibles were then heated in air at one of the test temperatures and times. A new specimen was used for each test condition. Upon removal from the furnace, the crucibles were covered to prevent loss of scale due to flaking during cooling. After cooling, the crucible and contents were then weighed to determine the change in weight due to oxidation.
Hot corrosion testing was done by means of a gravimetric method using the same size specimen as the oxidation tests. The specimens were weighed and then partially covered with a 1% sodium chloride, 99% sodium 94,000 p.s.i.
Life, E1on., hrs. percent the specimens were reweighed and the loss of weight used as a measure of the sulfidation attack.
The following tables illustrate representative values obtained when testing the three preferred alloys of the present invention.
85,000 p.s.i. 00,000 p.s.i.
' Life, Elon., L1fe,- E10n., "hrs. percent ILA. hrs. percent TABLE 4.STRESS RUPTURE FOR CAST ALLOYS IN AIR AT 1,400 F.
sulfate mixture in silica crucibles. The crucibles with the specimens and salt mixture were heated in air for 1 hour at a temperature of 1,800? F. The scale produced during the corrosion of the specimens was removed by cathodical- 1y descaling in molten sodium hydroxide. After descaling,
Alloy 67717901 1 3 2 3L1JL3 35,000 p.s.i.
Life, Elon., hrs. percent 25,000 p.s.i.
Life, Elon.,- hrs: percent TABLE 5.STRESS RUPTURE RESULTS FOR CAST ALLOYS IN AIR AT 1,875 F.
main 4 31197 4 25,000 p.s.i.
Life, E1on., hrs. percent 20,000 p.s.i.
Life, Elon., hrs. percent 15,000 p.s.i. Life Elon., .hrs. percent RA.
TABLE 6.-.STRES S RO'PTURE RESULTS FOR CAST ALLOYS IN AIR AT 1,950 F.
753553481 ZHMZA GHMA LKW saaaasa & 3 4352M2 085 21112HMU VID-- R.A., percent AT 15,000 P.S.I. LOAD Elongation, R.A., Elongation, Life, hrs. percent percent Life, hrs. percent;
TABLE 7.STRESS RUPTURE RESULTS FOR CAST ALLOYS IN ARGON "AHOY IVY 036691300 lamuolemd omlm VI-A-..--
VI-D..-...
TABLE 8.TENSILE RESULTS FOR CAST ALLOYS Room temperature 1,200 E. v
Ultimate 0.2% ofiset Elongation, R.A., Ultimate 0.2% ofiset Elongation, RA Alloy (10 p.s.i.) yield (10 p.s.i.) percent percent (10 p.s.i.) yield (10 p.s.i.) percent percent Ultimate 0.2% ofisct Elongation, R.A., Ultimate 0.2% ofiset Elongation, R.A., Alloy p.s.i.) yield (10 p.s.i.) percent percent (10 p.s.i.) yield (10 p.s.i.) percent percent Ultimate 0.2% offset Elongation, R.A., Ultimate 0.2% oiiset ":Elongation, R.A., Alloy (10 p.s.i.) yield (10 p.s.i.) percent percent (10 p.s.i.) yield (10 p.s.i.) percent percent 69. 8 61. 0 6. 5 6. 6 58. 2 52. 0 6. 3 8. 1 71. 1 61. 8 5. 9 5. 9 58.0 51. 9 5. 2 6. 2 73. 0 62. 1 4. 4 5. 5 57. 1 50. 0 6. 0 5. 9 73. 0 63.2 3. 9 4. 7 57. 4 50. 4 3. 8 2. 7 VI-D 73. 6 65. 5 3. 3 9. 6 60. 0 54. 8 2. 1 2. 0 74. 1 66. 6 2. 2 5. 9 61. 2 56. 1 2. 3 2. 4
1 Broke in shoulder.
TABLE 9.THERMAL FATIGUE RESULTS FOR CAST ALLOYS First cracking 'lgest Alloy observed Failure temp.,
IV-Y, 1 4, 100 5, 100 2, 100
713C vir in Incol inf" 1, 000 1, 400 2, 100 2 1, 150 1, 600 2, 100
N 100 VT in): I 1- S i 450 1,600 2,100 2 150 1,600 2,100
100 rt IN Li f fu 450 1, 050 2, 100 2 300 300 2, 100
TABLE 10.OXIDATION RESULTS FOR CAST ALLOYS Hot corrosion results for east alloys Alloygl Y Weight loss (grgnsigg VI A :IZIIIIIIII: 0.150; 0.271 VI-D 1.633; 1.968
In addition to the control of the molybdenum, tungsten and tantalum contents as previously specified, the nickel, aluminum, and titanium contents, for best results, should also be controlled. In this connection, we prefer to use H the relationship between these metals which is specified in U.S. Pat. No. 3,254,994 owned by the assignee of the present invention. As, described "in. that patent, it is desirable to produce an intermetallic compound between the three metals, wherein the compound has the formula Ni A1 Ti where x plus y=1,-but y is not more than 0.6. This intermetallic compound is a face centered cubic structure which constitutes the gamma prirne phase of the nickel-aluminum .phase diagram.
4 From our studiesywe have 'concluded'that the preferred alloys of the present invention represent a substantial improvement in stress rupture life over present-day alloys. The alloy identified as VI-A has the best high temperature properties of the three. Its stress rupture life is the highest and represents approximately a 50 F. increase in temperature over the lives of present-day high strength nickel base alloys. Its tensile strength and impact properties are comparable with suchalloys. Its ductility appears to be adequate and it does not appear to suffer a severe reduction in tensile ductility in the 1,400 F. to 1,600? F. temperature range. In addition, alloy VI-A has a good thermal fatigue'and corrosive resistance for a high strength alloy and does not appear to suffer from microstructural instability, that is, formation of sigma, Laves, or mu phase formation.
We claim as ourinvention:
1. A nickel-base alloy having improved stress rupture properties and consisting essentiallyofthe following in- Essentially..thebalancee the sum of the molybdenum, tungsten, and tantalum contents being in the range from 15 to 20%, the tungsten being present in an amount greater than the molybdenum but less than the amount of tantalum, the stress rupture life of the alloy at an applied stress of 15,000 p.s.i. at a temperature of 2,000 F. being at least 20 hours.
2. A nickel-base alloy having improved stress rupture properties and consisting essentially of the following ingredients:
1 Essentially the balance.
the sum of the molybdenum, tungsten, and tantalum contents being in the range from 15 to 20%, the tungsten being present in an amount greater than the molybdenum but less than the amount of tantalum, the stress rupture lift of the alloy at an applied stress of 15,000 p.s.i. at a temperature of 2,000 F. being at least 20 hours.
3. A nickel-base alloy having improved stress rupture properties and consisting essentially of the following ingredients:
Percent Carbon 0.13-0.15 Chromium 5.4-6.1 Molybdenum 1-3 Titanium 0.75-1.50 Aluminum 5.0-6.0 Cobalt 5 .0-7.5 Tungsten 5.5-6.0 Rhenium -1.0 Hafnium 0.43-2.0 Zirconium 0.03-0. 13 Boron 0.01-0.1 Tantalum 8 .0-90 Vanadium 0-0.5 Nickel (1) 1 Essentially the balance.
the sum of the molybdenum, tungsten, and tantalum contents being in the range from 15 to 20% the stress rupture life of the alloy at an applied stress of 15,000 p.s.i. at a temperature of 2,000 F. being at least 20 hours.
4. The alloy of claim 1 in which there is sufiicient nickel present to provide the compound Ni Al Ti where x plus y: 1, but y is not greater than 0.6-.
5. A nickel-base alloy having improved stress rupture properties and consisting essentially of the following ingredients:
Percent Carbon 0.15 Chromium 6.0 Molybdenum Titanium Aluminum 5.4 Cobalt 5 Tungsten 5 Rhenium 1.0
Percent Hafnium 2.0 Zirconium 0.03
Boron 0.02
Tantalum 8.0
Columbium 1.0
Nickel (1) 1 Essentially the balance.
said alloy having a stress rupture life at an applied stress of 15,000 p.s.i. at a temperature of 2,000 F. of at least 20 hours.
6. A nickel-base alloy having improved stress rupture properties and consisting essentially of the following ingredients:
Percent Carbon 0.13 Chromium 6.1 Molybdenum 2.0 Titanium 1.0 Aluminum 5.4 Cobalt 7.5 Tungsten 5.8 Rhenium 0.5
Hafnium 0.43
Zirconium 0.13
Boron 0.02 Tantalum 9.0 Columbium 0.5 Nickel (1) 1 Essentially the balance.
said alloy having a stress rupture life of at least 20 hours at an applied stress of 15,000 p.s.i. and at a temperature of 2,000 F.
7. A nickel-base alloy having improved stress rupture properties and consisting essentially of the following ingredients:
Percent Carbon 0.15 Chromium 5.4 Molybdenum 2.0 Titanium 1.0 Aluminum 5.4 Cobalt 5.0
Tungsten 6.0 Hafnium 1.75 Zirconium 0.08 Boron 0.02 Tantalum 8.5 Columbium 0.5 Vanadium 0.5 Nickel (1) 1 Essentially the balance.
said alloy having a stress rupture life of at least 20 hours at an applied stress of 15,000 p.s.i. and at a temperature of 2,000 F.
8. A turbine engine blade composed of the alloy of claim 1.
9. A turbine engine blade composed of the alloy of claim 2.
10. A turbine engine blade composed of the alloy of claim 3.
References Cited UNITED STATES PATENTS 3,005,705 10/1961 Cochardt 171 3,164,465 1/ 1965 Thielemann 75171 3,310,399 3/1967 Baldwin 75-171 RICHARD O. DEAN, Primary Examiner UNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION Patent No. 3,526 499 Dated September 1, 1970 Inventor(s) Richard]. Quigg and Henry E. Collins It is certified that error appears in the above-identified patent and that said Letters Patent are hereby corrected as shown below:
Column 7, line 18, (second table of Table 8, in the third column) "104. 4" should read --140. 4--.
Column 8, line 35,
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US3677331A (en) * 1969-07-14 1972-07-18 Martin Marietta Corp Casting process for nickel base alloys
US3711337A (en) * 1970-12-16 1973-01-16 United Aircraft Corp Columnar-grained nickel-base superalloy castings
US3753698A (en) * 1971-01-22 1973-08-21 Martin Marietta Corp Nickel-base alloy
US3887363A (en) * 1973-12-18 1975-06-03 Gen Electric Nickel-base superalloy cast article
US3904402A (en) * 1973-06-01 1975-09-09 Gen Electric Composite eutectic alloy and article
US3944416A (en) * 1974-06-24 1976-03-16 General Electric Company Directionally solidified nickel-base eutectic alloys
US4169742A (en) * 1976-12-16 1979-10-02 General Electric Company Cast nickel-base alloy article
DE3016027A1 (en) * 1979-04-27 1980-11-13 Gen Electric OBJECT OF A NICKEL ALLOY AND ALLOY THEREFOR
EP0032812A1 (en) * 1980-01-17 1981-07-29 Cannon-Muskegon Corporation Nickel base alloy and turbine engine blade cast therefrom
US4388124A (en) * 1979-04-27 1983-06-14 General Electric Company Cyclic oxidation-hot corrosion resistant nickel-base superalloys
US4492672A (en) * 1982-04-19 1985-01-08 The United States Of America As Represented By The Secretary Of The Navy Enhanced microstructural stability of nickel alloys
GB2220422A (en) * 1988-05-17 1990-01-10 Hitachi Metals Ltd Heat resistant single-crystal nickel-base super alloy
US5035958A (en) * 1983-12-27 1991-07-30 General Electric Company Nickel-base superalloys especially useful as compatible protective environmental coatings for advanced superaloys
US5043138A (en) * 1983-12-27 1991-08-27 General Electric Company Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys
US5068084A (en) * 1986-01-02 1991-11-26 United Technologies Corporation Columnar grain superalloy articles
US5439640A (en) * 1993-09-03 1995-08-08 Inco Alloys International, Inc. Controlled thermal expansion superalloy
EP0683239A1 (en) * 1994-05-20 1995-11-22 United Technologies Corporation Oxidation resistant nickel based super alloy
US6632299B1 (en) 2000-09-15 2003-10-14 Cannon-Muskegon Corporation Nickel-base superalloy for high temperature, high strain application
US20040221925A1 (en) * 2003-05-09 2004-11-11 Hideki Tamaki Ni-based superalloy having high oxidation resistance and gas turbine part
US20130177442A1 (en) * 2010-09-20 2013-07-11 Paul Mathew Walker Nickel-base superalloy
CN103572098A (en) * 2012-07-24 2014-02-12 苏州宏久航空防热材料科技有限公司 Non-uniform-aperture centrifugation disc for glass fiber centrifugation and preparation method thereof
US9017605B2 (en) 2009-07-09 2015-04-28 Alstom Technology Ltd. Nickel-based superalloy
EP3034639A1 (en) 2014-12-16 2016-06-22 Honeywell International Inc. Nickel-based superalloys and additive manufacturing processes using nickel-based superalloys

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US20070163682A1 (en) * 2003-05-09 2007-07-19 Hitachi, Ltd. Ni-based superalloy having high oxidation resistance and gas turbine part
US9017605B2 (en) 2009-07-09 2015-04-28 Alstom Technology Ltd. Nickel-based superalloy
EP2451986B2 (en) † 2009-07-09 2017-10-18 Ansaldo Energia Switzerland AG Nickel base superalloy
US20130177442A1 (en) * 2010-09-20 2013-07-11 Paul Mathew Walker Nickel-base superalloy
US9593583B2 (en) * 2010-09-20 2017-03-14 Siemens Aktiengesellschaft Nickel-base superalloy
CN103572098A (en) * 2012-07-24 2014-02-12 苏州宏久航空防热材料科技有限公司 Non-uniform-aperture centrifugation disc for glass fiber centrifugation and preparation method thereof
CN103572098B (en) * 2012-07-24 2016-07-27 苏州维艾普新材料股份有限公司 A kind of centrifugal glass fibre non-uniform hole centrifugal pan and preparation method thereof
EP3034639A1 (en) 2014-12-16 2016-06-22 Honeywell International Inc. Nickel-based superalloys and additive manufacturing processes using nickel-based superalloys

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