US3904403A - Heat resisting nickel-aluminum-molybdenum alloy - Google Patents

Heat resisting nickel-aluminum-molybdenum alloy Download PDF

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US3904403A
US3904403A US421971A US42197173A US3904403A US 3904403 A US3904403 A US 3904403A US 421971 A US421971 A US 421971A US 42197173 A US42197173 A US 42197173A US 3904403 A US3904403 A US 3904403A
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alloy
range
atomic percent
heat resisting
nickel
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Noboru Komatsu
Takatoshi Suzuki
Nobuyuki Yamamoto
Yukikazu Tsuzuki
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Toyota Central R&D Labs 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
    • C22C19/007—Alloys based on nickel or cobalt with a light metal (alkali metal Li, Na, K, Rb, Cs; earth alkali metal Be, Mg, Ca, Sr, Ba, Al Ga, Ge, Ti) or B, Si, Zr, Hf, Sc, Y, lanthanides, actinides, as the next major constituent

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  • ABSTRACT A nickel base heat resisting alloy having high tensile strength and excellent oxidation resistance at high temperatures in the range of l ()0U*l 200C and toughness at room temperature characterized by the alloy comprising 91-999 atomic percent of a basic constituent, up to 6 atomic percent silicon, and between 0.1-3 atomic percent of a second or additive constituent consisting of one or more elements se lected from a group of elements consisting of titanium, chromium, zirconium, niobium tantalum and tungsten.
  • the basic constituent comprises nickel alumi num and molybdenum in the following atomic pcrcents of the basic constituent: nickel 62-83% alumi num 11-26% and molybdenum 6-1271.
  • the silicon comprises ()'7( and the basic constituent comprises between 97-999 atomic percent of the alloy. 1n the other embodiment, the silicon is in a range of (J.56 atomic percent and the basic constituent is in a range of 91-994 atomic percent of the alloy.
  • the addition of the silicon improves the oxidation resistance of the alloy when heated to an elevated temperature 15 Claims, 8 Drawing Figures PATENTED SEP 91975 3. 9 O4. 40 3 Alur/.%
  • the present invention relates to a heat resistant nickel base alloy having a high tensile strength at high temperatures and toughness at room temperature.
  • heat resisting steels are applicable for use tor a temperature below 800C and that heat resisting alloys containing either nickel (Ni) or cobalt (Co) as the principle component may be used up to a temperature of l.00()(.
  • Ni nickel
  • Co cobalt
  • these alloys experience a deterioration in strength and therefore. their use is limited to a temperature range which does not exceed the above-mentioned temperature
  • the manufacture of most of these conventional alloys can involve many difficulties. for example. many of these alloys must be melted in a vacuum.
  • Heat resisting metal alloys such as molybdenum (Mo). niobium (Nb) and tantalum (Ta) or ceramics may serve for a long period of time at elevated temperatures above [000 C
  • Mo molybdenum
  • Nb niobium
  • Ta tantalum
  • the metal alloys are inferior in their resistance to oxidation at elevated temperatures and thus are limited in their use to atmosphere or service conditions in which oxidation is not present. If they are to be used in oxidizing atmosphere, the alloy must be provided with a surface treatment for the prevention of oxidation.
  • the ceramics have a disadvantage of a lack ofductility and thermal impact resistance. For example. ceramics will tend to break due to a sudden change in temperature. Thus.
  • the present invention is directed to providing a heat resisting alloy or alloys which are free from the drawbacks of the conventional heat resisting alloys as described hereinabovc and which alloys have excellent mechanical strength.
  • toughness and oxidation resistance at elevated temperatures ranging from i.i)00-l.200C.
  • Alloys of the present invention comprise )l-Ql) atomic percent of a basic constituent, 0. l 3 atomic percent of an additive or second constituent and up to atomic percent silicon.
  • the basic con stituent comprises nickel.
  • the additive or second constituent con sists of at least one element selected from a group of el ements consisting of titanium, chromium. zirconium. niobium, tantalum and tungsten. If oxidation resistance is not a problem. the addition of the silicon can be eliminated so that the alloy contains 0 atomic percent silicon and the basic constituent will then have an atomic percent of 97-999 atomic percent of the alloy. When the silicon is required. between 0.56 atomic percent is added and the basic constituent then comprises 91-994 atomic percent of the alloy.
  • FIG. 1 is a triangular coordinate diagram which rep resents by atomic percent the range of composition of the nickel. aluminum and molybdenum of the basic component or constituent of the nickel base alloy of the present invention
  • FIG. 2 is a triangular coordinate diagram representing in weight percent the range of composition of the nickel. aluminum and molybdenum of the basic com ponent or constituent of the nickel base alloy of the present invention
  • FIG. 3 is a cross-sectional view oi'a metal melting de vice utilized in preparing a Lini-direetionally solidified rod to be used in tensile tests and other tests performed on the alloys of the present invention
  • FIG. 4 is a graph illustrating the change in tensile strength at l.()()0C of different nickel-aluminum molybdenum alloys in relationship to a variation of the content of molybdenum;
  • FIG. 5 is a graph illustrating the effect of changes in the molybdenum contact in a niekel-aluminummolybdenum alloy on the measuring loads used in a toughness test at room temperature;
  • FIG. 6 is ,a graph illustrating the effect of adding dif fcrent amounts of one or more additive elements of titanium. chromium. Zirconium. niobium. tantalum and tungsten to a nickel-aluminum-molybdenum alloy on the tensile strength at l.l()()C-.
  • FIG. 7 is a graph illustrating the effect of different amounts of silicon in a nickcl-aluminum-molybdcnum alloy of the present invention on the weight increase due to oxidation when the alloy is subjected to heating at [200C for 21 hours;
  • FIG. 8 is a graph illustrating the changes in tensile strength at I,IOUC of the alloy of the present invention containing silicon with respect to changes in the content of silicon.
  • the principles of the present invention are particularly useful for providing nickel base heat resisting al Ioys having a main or base constituent or component comprising nickel. aluminum and molybdenum with a second constituent or additive consisting of one or more elements selected from a group of elements consisting of titanium, chromium. Zirconium. niobium. tantalum or tungsten with or without the addition of silicon which improves the resistance of the alloy to oxidation.
  • the alloys of the present invention are a result of a study which was concentrated on improving the prop ertics of conventional heat resisting alloys and particularly an improving of the alloys high temperature ten- 3 r sile strength characteristics and their toughness at room temperature.
  • an intermetallic compound of nickel and aluminum alloy which has the formula of Ni;,Al. has an excellent resistance to oxidation at elevated temperatures when compared with conventional heat resisting alloys.
  • the additive elements of the alloy of the present invention are for the purpose of increasing the high temperature tensile strength of the Ni;.Al alloy and the tough ness at room temperatures.
  • an embodiment of the alloys of the present invention includes the addition of a small quantity of silicon to increase the resistance to oxidation without detrimcntally affecting the high temperature tensile strength properties.
  • a nickel base alloy having the following composition presents high tensile strengths at elevated temperatures as well as excellent toughness at room temperatures.
  • the composition consists principally of nickel. aluminum and molybdenum having atomic percent of the basic component or constituent of the alloy with the percentages being enclosed by the straight lines con necting points A. B. C and D in an equilateral triangular coordinate diagram illustrated in FIG. I.
  • the point A in FIG. 1 represents an alloy having 83% nickel. l 19 aluminum and 6% molybdenum; point B represents an alloy having 68% nickel. 26% aluminum and 6% molybdenum; point C represents an alloy having 62% nickel. 26% aluminum and 12% molybdenum; and point D repr'esents an alloy having 77% nickel.
  • the alloy of the present invention includes at least an additive or second con -stituent which consists of at least one element selected from a group of elements consisting of titanium. chro mium. zirconium. niobium. tantalum and tungsten with the basic component or constituent ranging from 97-999 atomicpcrccnt and the contents of the additive or second constituent ranging from 0. l-3 atomic percent.
  • an embodiment of the alloys of the present invention containing 9 [-99.4 atomic percent of the basic component or constituent. from 0.
  • the triangular coordinate diagram of FIG. I is an equilateral triangular coordinate diagram with three sides having equal divided gradations to show the relationship between the content of nickel. aluminum and molybdenum for alloys containing more than atomic percent of nickel.
  • the atomic percent of aluminum is plotted on the base of the UL angular coordinate diagram.
  • the atomic percent of the nickel is on the left side.
  • the atomic percent of the i molybdenum is on the right side. Accordingly, the content of aluminum (percentages) is represented by a line extending parallel to the left side.
  • the content of the nickel is r'cpresented by a line extending parallel to the right side and the content of molybdenum is represented by a line extending parallel to the base.
  • a point Y in FIG. 1 represents a composition consisting of 709? nickel. 10)? aluminum and molybdenum.
  • the proportions of the respective elements illustrated in FIG. 1 represent the ratio of the elements in the basic constituent; but not the ratio of the elements in an alloy which includes the additive elements.
  • an alloy contains 98% of the basic constituent.
  • an additive constituent of 2V titanium and the basic constituent consists of nickel. 10% aluminum and 10% molybdenum.
  • the atomic percentage of the elements of the basic constituent in the alloy are: nickel 70 X 0.98 68.6 atomic percent. aluminum 20 X (1.98 19.6 percent. molybdenum It) X 0.98 9.8 percent. and titanium is 2%.
  • the amount of nickel. aluminum and molybdenum in the alloys of the present invention have been expressed in atomic percent of the basic constituent which may between 9 [-99.9 atomic percent of the alloy. Using the above described calculation. the alloys of the present invention can be described in atomic percent range of the alloy as follows: nickel 56.42-82.9l7r; aluminum lU.0I25.974'/r; molybdenum S.46ll.988'/(; additive constituent (1.l3"r; and silicon (l-fi'7r. If silicon is not present.
  • the alloys of the present invention will have the following range of atomic percents for the elements of the basic constituent: nickel 6U.l482.9l'/r alumin'uni ll).o7-2S.974l; and molybdenum 5.824 1.988%. If silicon is present. the alloys of the present invention will have the follow ing ranges of atomic percents for the element of the basic constituent: nickel Sb.42-82.5ll2'/r; aluminum MIDI-25.84471; and molybdenum 5.46% IFJZSQ. It should be noted that if the additive constituent is (I. l i and silicon is not present or only 0.5%. the difference between the total percentage of the elements of the base constituents in the alloy and their percentage in the base constituent is extremely small.
  • FIG. 2 An equilateral triangular coordinate diagram which represents the ratio of nickel. aluminum. molybdenum by weight percent is shown in FIG. 2.
  • the quantity of aluminum in the basic constituent of a nickel base alloy according to the present invention is restricted to a range of between Hand 26% for the following reasons. It is well known that a nickel base heat resisting alloy. which consists of only -y phase at a desired high temperature, will include a solid solution of the other elements in the nickel and the alloy cannot achieve the desired strength. To achieve the increased tensile strength for the alloy at high temperature. at least a precipirate such as Ni Al must be dispersed in the phase or the Ni Al should be the principal component of the alloy. The presence of such a precipitate in a solid solution of nickel is an important factor to obtain the improved tensile strength at high temperature.
  • the basic constituent of the alloy of the present invention which constituent consists of nickel-alummum-molybdenum has aluminum in an atomic percentage of more than l 1' 1 so that the 1 phase and the Ni;;Al coexist at l.2()l)C.
  • the alloys In the area of the right hand side of a curve g (FIG. 1) and particularly the area where the content of the molybdenum is low. the alloys contain only a solid solution of NiAl in w hich nickel and molybdenum are dissolved (this solution is hereafter referred to as y phase).
  • the nickel-alummum-molybdenum alloy having the composition within this range has extremely low tensile strength at elevated temperaturesv Likewise in the area of the diagram of FIG.
  • the alloy when at about l.2(10C contains eutectic crystals of the y phase and the molybdenum with nickel and aluminum solidly dissolved therein and thus the alloy becomes very brittle and weak as the temperature increases. Specifically, when the phase is suddenly cooled from the elevated temperatures. there takes place a Martcnsite type transformation and the alloy composed of the 7' phase is hardened and bc comes extremely brittle.
  • the basic alloy of nickelaluminum-molybdcnum alloys of this invention contain less than 26% aluminum and provided toughness of more than 50 kg according to a toughness test method which will be described hereinafter.
  • nickel-aluminum-molybdcnum alloy having a composition at a point P of FIG. 1 has a low toughness of about 1 to lt) kg. Accordingly. in the basic constituent of nickelaluminum-molybdenum of the alloy of this invention. the quantity of aluminum. is limited to less than 26% which is within the area of the left side of the curve g.
  • the quantity of molybdenum in the basic constituent is limited to a range of from 6-l2 atomic percent as shown in FIG 1.
  • the amount of molybdenum in the basic constituent is increased and the constituent contains mainly Ni;,Al.
  • the resulting nickcl-aluminummolybdenum alloys present peak values and high temperature tensile strength for a molybdenum content in a range of from 6l27(.
  • the quantity of molybdenum is limited to the range of 6-12 atomic percent.
  • composition of the basic nickel-alurninum-molybdenurn which is the basic constituent or component of the nickel base heat resisting alloy ofthis invention are limited to a range of from 68-83% nickel. l [-26% aluminum and 6-12'7r molybdenum.
  • the nickel base alloy of the present invention contains a second or additive constituent or component in an amount of 0. l3 atomic percent which constituent Consists of one or more elements selected from a group of elements consisting of titanium. chromium. zirconium. noibium, tantalum. tungsten.
  • the addition of the second component or constituent provides extremely high tensile strengths at elevated temperatures. It is believed that the increase in the high tensile strength at high temperatures is based on the fact that the nickelaluminum-molybdenum alloy is reinforced by dissolving one or more of the additive elements into the alloy as a solid solution.
  • atoms of one or more ofthc additive elements dissolve in the alloy are consid- (ill ered to be present as a solid solution in place of atoms of the elements forming the nickel-aluminum molybdenum alloy and thereby strengthen the alloy structure.
  • the addition of less than 0.1% of the additive constituent exerts little influence on the strength of the alloy.
  • the addition of more than 3% causes the formation of globulars or a square-flake shape crystalline structure of a large grain size in the dense structure of the nickel-a]uminum-molybdenum alloy. It is considered that when a stress acts on the alloys having the large crystalline structure.
  • the alloys of the present invention may contain a small amount of boron as an impurity.
  • An embodiment of the alloys of the present invention contain the basic component or constituent of nickelaluminum-molybdcnum. (ll-3% of the additive constituent or component and from (XS-6% of silicon and these alloys not only display high strength at elevated temperatures. toughness at room temperatures. but also have excellent oxidation resistance at elevated temperatures.
  • the addition of the silicon greatly improves the oxidation rcsistance of the nickel base alloy of the present invention.
  • the addition of between (LS-6% silicon is greatly effective and the addition of from 2-47( silicon will provide the maximum oxidation resistance for the alloy.
  • the addition of silicon less than i 0.5% or more than 6% is improper for use in improving oxidation resistance.
  • the addition of the silicon to the alloy causes a slight decrease in the strength of the alloy at elevated temperatures. However. the effect and the improvement in the oxidation resistance is far greater despite the decrease in strength at high temperatures.
  • the heat resisting alloys of the present invention will be further explained with the following test examples and embodiments showing the mechanical strength of the inventive alloy.
  • Each of the alloys for the test samples of the following examples and embodiments was obtained from raw materials consisting of electrolytic nickel. high purity aluminum. high purity molybdenum. and high purity raw materials of the additi ⁇ e elements such as titanium. chromium. zirconium. niobium. tantalum and tungsten. These raw materials were subjectcd to a high frequency melting in an alumina cruci ble under a protective atmosphere of argon gas and the resultant molten metal was cast into a cast product. The cast product thus attained was subjected to oxidation resistance tests. tensile tests and hardness tests which will each be described hereinbelow.
  • Ni;.AI greatly vary with the solidification direction. i.e. Ni Al has anisotropic properties. Therefore. each of the samples for the tensile tests was produced from a unidirectionally solidified rod so as to have a given direction of solidification.
  • FIG. 3 a unidirectional solidification device illustrated in FIG. 3 was utilized.
  • the device of FIG. 3 has a quartz tube 2 which has a lower end sealed with a heat resisting material I for retaining a sample.
  • the quartz tube is supported and can be moved up and down by a support 8.
  • An air tight sealing member 7 is provided on the upper end of the glass tube 5 and has a small tube 6 for introducing an inert gas into the quartz tube 2 and the glass tube 5.
  • a high frequency induction work coil 4 surrounds the glass tube 5.
  • the inert gas introduced through the small tube 6 fills the inside of the quartz tube. and covers the outer peripheral portion of the quartz tube 2 to shut out the atmosphere. The inert is discharged to the atmosphere through the lower end of the glass tube 5.
  • a sample I was placed in a bed 3 of alumina powder (Al O;,) which bed is contained in the quartz tube 2. Then the air inside of the quartz tube 2 was replaced with argon gas by continuously supply ing the argon gas through the small tube 6. After the argon gas has purged the air from the quartz tube. a high frequency induction current was applied to a high frequency work coil 4 to melt the sample I by means of heating it from the lower end or part thereof. The support 8 was gradually moved downward so that the sample 1 was solidified from the lower end thereof. In this manner a unidirectionally solidified rod for making test pieces or samples with the direction of their crys* tals arranged in the longitudinal direction was pro Jerusalem.
  • the test piece was made from the above stated unidirectionally solidified rod by machining the rod to a size with a length of 35 mm. a diameter in the parallel portion of4 mm and a length in the parallcl portion of 17 mm. The test piece was maintained in the test temperature ranging from l.0O0-l.lt)t)C for minutes and then tested at a tensile speed of 2.5 mm/minutes. The test results are represented in terms of tensile strength (kg/mm For the oxidation test which examined the oxidation resisting properties of the sample. a test piece was prepared by cutting the above stated rod into a test piece hzning a diameter of It) mm and a length of It) mm.
  • each of the test pieces was polished into a metallic surface. After weighing each of the test pieces. it as heated to I.2(]()C and maintained in an air atmosphere for 21 hours. After completing the period of heating. the weight of each test sample was again measured and the amount ol o ⁇ idation would be indicated by any increase in the weight of the sample. From this test the oxidation weight (AWg) and the spalling (flaking. exfoliation) weight (AWf) were obtained in the following manner. Assuming that the weight of the test piece before the oxidation test is W0. and that its surface area is So. that the weight of the test piece after the oxidation test is Wg and that the weight of the oxides. which spalled or flaked off. is Wf. the oxidation weight (AWg) can be expressed as follows:
  • test samples were pressed with a Vickers hardness tester which is generally employed in measuring the toughness of superhard alloys. The toughness thereof was judged by the load which caused cracks around the trace of pressure or the indentation which was formed by the load during the tests. Samples that tend to produce such cracks under lighter loads were judged to be too brittle.
  • the samples were subjected to varied Vickcrs loads of l. 5. It). 20. 3t) and kg. respectively. with each of the loads being impressed into three different areas of each sample. and each of the indentations was inspected or examined to determine whether or not cracks were produced by a given load.
  • the maximum load (kg) that produced no cracks in all of the three im pressed indentations is considered to be the degree of toughness.
  • FIG. 4 illustrates the relation between the tensile strength at l.()(l0C for nickel-aluminum-molybdcnum alloy as the percentage of molybdenum is changed from 0 to approximately 14%.
  • the curves H. I and .l of FIG. 4 correspond to lines h. i andj in the diagram of FIG. 1. respectively. and the curves H. I and J, respec tivcly. represent the tensile strength at I.OUOC of the nickcl-aluminum-molybdenum alloy having the composition represented by the lines I1. i andj of FIG. 1.
  • the lines Ii. i and j of FIG. I are obtained from the lines Ii. i and j of FIG. I by referring to the contents of molybdenum of the said given point. respectively.
  • the line 11. represents the composition of alloy wherein the aluminum of the Ni Al is replaccd with molybdenum and is a line connecting Ni; Al with the Ni;.Mo (FIG. 1
  • the linej represents the composition of an alloy wherein the nickel of the Ni Al is replaced with molybdenum while the line i' is position between the lines I: and wherein molybdenum is added to the Ni Al.
  • the tensile strength curves H. I and .l of FIG. 4 illustrate the maximum tensile strengths 56 kg/mnr". 44
  • kgrlnin and Mt lsgrmin [e-qccti cl t. and the ltltt ⁇ l' mum strengths and obtained when the atomic percent of molybdenum is between llllr'.
  • lhe LftIHBs also il lustrate that a high tensile strength is obtained over a range of (will niohbdenuni in the nielsclalltiminunr moly denum 'lllo Thwsc carves reveal that the clet'llILtl temperature ten ile strength is more than [.5 times as much as the tensile strength of l) kgrmm at l ""i . ⁇ l tor l twat csisting alloy.
  • Tht addi tit ol mt vbtlenuni in excess of ill! causes an abrupt decrease oi the high temperature tensile strength lor the alloys.
  • Example ll Fl('1. 5 illustrates a relationship between the toughness at room temperature for the nickel aluminumniolvbdcnum alloy and a var ing percentage content of molybdenum.
  • the illustrated allo 's include a range of the basic constituent oi the nickel based alloy of the present in ⁇ ention.
  • the test samples ⁇ vcrc selected from a nieltel aluminum-inol bdciunn allov having a compo sition re resented by the line it in Flt) l and the con tents of the nickel and the aluminum in each test sam ple are obtained from the line h of FIG. 1 by referring to the percentage content ot the niolyi' denum of each test sample '1 he toughness ot each of the test samples is illustrated from the data of FIG. 5.
  • tantalum and tungsten being added to the alloy are illustrated with the per centage ot' the atlditixe constituent being from U 5 atomic percent
  • the ordtnutc represents the tensile strength tkg mnr'l and the abscissa represents the content ot'the additive element or constituent. in H0. (J
  • the curve R represents the maximum tensile strength for respective contents of the atlditnc element and the curve T represents the nnnimuin tensile strength
  • Fig. 6 shows that the allo s obtained by the addition of the additive element or constituent to the basic constituent of uicltcluluntiniun-molybdenum provides a tensile strength ranging from limucen the curves R and T.
  • the minimum addition oi the udditi ⁇ c consti uent causes an abrupt increase in the tensile strength to obtain the maximum value in the content ranging from (l.52.5% the maximum tensile strength is 5 kgrirnn and the lower limit of the strength is 4. kgrmm Compared with the tensile strength of 38 kgrmrn of the nickclailuminunr molybdenum allo vvithout containing the additive element. the tensile strength of the nickel-aluminumttiol ⁇ l7del
  • the spalling eight was measured simultaneous with the measurement of the weight increased due to oxida tion and presents four times as much as the weight increase due to oxidation.
  • the addition of silicon also re prises the spalling weight in a manner similar to the decrease of the oxidation weight. This proves that the oxidation in the nickel-aluminum'molybdcnum alloy proceeds with spalling. According to other tests. the addition of silicon to the nickel aluminum alloy which contains no molybdenum did not produce any improve merit in osidation resistance.
  • the tensile strength follows substantialh a linear decrease with an increase in the content otsihcon and the tensile strength oi the nickcLaIuminummoi l dcnum allo ⁇ vithout containing silicon is approxand imately 50 kg/mm".
  • the nickel-aluminum molybdenum alloy containing 6% silicon has .a tensile strength lower to approximately 30 ltg/mm'i
  • the decrease in the tensile strength at high temperatures due to the addition. of silicon is commonly found in all of the nicke1a1uminummolybdenum alloys containing one or more of the additive elements and silicon.
  • Embodiment l Twenty-four samples of the alloys according to the present invention were prepared from electrolytic nickel. high purity aluminum, high purity molybdenum and high purity titanium, chromium. zirconium, niobium. tantalum and tungsten were prepared by melting in the argon gas atmosphere.
  • the alloys 01 this invention contain the basic constituent of nickc1 a1uminum-molyhdenum and at least one element of titanium. chromium. zirconium. niobium. tantalum and tungsten present extremely high tensile strengths at e1evated temperatures.
  • the tensile strength of alloys 1 through 17 consisting of the alloy K which has a composition of point K in FIG. I and additive element such as titanium is from 43 to 54 leg/mm" approximately and this is higher by 5 to 16 kg/mm than the elevated temperature strength of 38 kg/mm of the alloy K without any of the additive elements.
  • Alloys of the present invention having a base constituent comprising the alloys L or M and one or more additive elements hereinbefore described have a tensile strength at high temperatures from approximately 35 to 39 1tg/mm and from about 30 to 32 kg/mm respectively. These alloys are higher in tensile strength by 5 to 9 kg/mm' and by 5 to 7 kg/mm in comparison with the tensile strength of 30 kg/mm and the tensile strength of kg/mm of the basic alloys L and M. respectively. None of the alloys presented have a toughness of less than 50 kg. This means that the alloys of the present invention have excellent toughness properties at room tempera ture.
  • Embodiment 11 Some of the same alloys as those used in the table of Embodiment I. and a high purity silicon were melted under an argon gas atmosphere to prepare six kinds of alloys having a composition shown in Table 1!. Alloys number 30 through are equivalent to the alloys number 1. 3, 5, 7, 10 and 13 which are tabulated in Table 1 and have approximately 2% silicon added TABLE I
  • Tensile test Weight in- Alloy Composition (Atomic percent) at 1 100C crease due Tough- No.
  • the heat resisting alloys of the present invention which consists of three basic elements such as nickel. aluminum and molybdenum as a basic con stituent whose composition falls in a range defined by the points.
  • A, B, C and D in FIG. 1 and includes 0. l3 atomic percent of one or more elements of titanium. chromium, zirconium, niobium, tantalum and tungsten exhibit greatly improved tensile strengths at elevated temperatures and excellent toughness at room temperature.
  • the alloys consisting of the basic constituents comprising nickel-aluminum-molybdcnum having the above-mentioned composition. one or more additive elements mentioned above and from 0.5-6 atomic percent silicon exhibit high tensile strengths at elevated temperatures.
  • the alloys of the present invention are versatile as heat rcsisting materials which are applicable for use in steam turbines. gas turbines, devices for use in chemical in erly come within the scope of our contribution to the art.
  • a heat resisting alloy which has excellent mechanical strength. toughness and oxidation resistance at elc vatcd temperatures in the range of l.OO()-1.2()()C. said alloy consisting essentially of 93-98.) atomic percent of a basic constituent comprising nickel. aluminum and molybdenum in the following atomic percents of the basic constituent. nickel 62-83%. aluminum l 1-2671. and molybdenum 6.42%; 0.14% atomic percent of a second constituent consisting of at least one element selected from a grou pconsisting of titanium. chromium. zirconium. niobium. tantalum and tungsten; and 1-4 atomic percent silicon.
  • a heat resistance alloy which has excellent me chanical strength. toughness and oxidation resistance at elevated temperatures in a range of 1.00()1.2UUC. said 'alloyconsisting essentially of the following atomic percentages of constituents:
  • an additive constituent selected from a group of elements consisting of titanium. chromium. zirconium. niobium. tantalum. and tungsten. said additive constituents comprising at least one of said elements from said group.

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4012241A (en) * 1975-04-22 1977-03-15 United Technologies Corporation Ductile eutectic superalloy for directional solidification
US4111723A (en) * 1976-01-19 1978-09-05 United Technologies Corporation Directionally solidified eutectic superalloy articles
US4288259A (en) * 1978-12-04 1981-09-08 United Technologies Corporation Tantalum modified gamma prime-alpha eutectic alloy
WO1982000477A1 (en) * 1980-08-11 1982-02-18 United Technologies Corp Heat treated single crystal articles and process
DE3242608A1 (de) * 1981-11-27 1983-06-01 United Technologies Corp., 06101 Hartford, Conn. Superlegierung auf nickelbasis
FR2533232A1 (fr) * 1982-09-22 1984-03-23 United Technologies Corp Article a haut module d'elasticite
EP0593824A1 (de) * 1991-10-03 1994-04-27 Avco Corporation Monokristalline Nickelaluminid-Basis-Legierungen und Verfahren
DE19926669A1 (de) * 1999-06-08 2000-12-14 Abb Alstom Power Ch Ag NiAl-beta-Phase enthaltende Beschichtung

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS55120103U (de) * 1979-02-16 1980-08-26
JPH0613743B2 (ja) * 1987-11-19 1994-02-23 工業技術院長 ニッケル基超合金の固相接合法

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US1461178A (en) * 1918-08-26 1923-07-10 Kemet Lab Co Inc Alloy
US2542962A (en) * 1948-07-19 1951-02-20 His Majesty The King In The Ri Nickel aluminum base alloys
US3655462A (en) * 1971-03-22 1972-04-11 United Aircraft Corp Cast nickel-base alloy

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Publication number Priority date Publication date Assignee Title
US1461178A (en) * 1918-08-26 1923-07-10 Kemet Lab Co Inc Alloy
US2542962A (en) * 1948-07-19 1951-02-20 His Majesty The King In The Ri Nickel aluminum base alloys
US3655462A (en) * 1971-03-22 1972-04-11 United Aircraft Corp Cast nickel-base alloy

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4012241A (en) * 1975-04-22 1977-03-15 United Technologies Corporation Ductile eutectic superalloy for directional solidification
US4111723A (en) * 1976-01-19 1978-09-05 United Technologies Corporation Directionally solidified eutectic superalloy articles
US4288259A (en) * 1978-12-04 1981-09-08 United Technologies Corporation Tantalum modified gamma prime-alpha eutectic alloy
US4328045A (en) * 1978-12-26 1982-05-04 United Technologies Corporation Heat treated single crystal articles and process
WO1982000477A1 (en) * 1980-08-11 1982-02-18 United Technologies Corp Heat treated single crystal articles and process
DE3242608A1 (de) * 1981-11-27 1983-06-01 United Technologies Corp., 06101 Hartford, Conn. Superlegierung auf nickelbasis
FR2533232A1 (fr) * 1982-09-22 1984-03-23 United Technologies Corp Article a haut module d'elasticite
EP0593824A1 (de) * 1991-10-03 1994-04-27 Avco Corporation Monokristalline Nickelaluminid-Basis-Legierungen und Verfahren
DE19926669A1 (de) * 1999-06-08 2000-12-14 Abb Alstom Power Ch Ag NiAl-beta-Phase enthaltende Beschichtung
US6471791B1 (en) 1999-06-08 2002-10-29 Alstom (Switzerland) Ltd Coating containing NiAl-β phase

Also Published As

Publication number Publication date
JPS4982516A (de) 1974-08-08
JPS5124452B2 (de) 1976-07-24

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