DE2034608A1 - Cast alloys - Google Patents

Description

Dr. W. Schalk, DipMnfl. P. We * Dipl-lng. G. Dannmberg Dr. V, Schmied-Kowarzik Dr. P. WeinhoW, Dr. D. GucU

6 FremkfurljM., Gr. ΕκΙηηΚ «ηΜΤ Sh-. 39

-15354 Wd / Hn / hn

Martin Metals Company 277 Park Avenue

Hew York, N Y. ₀ 10017, USA

Cast alloys

The present invention "relates to cast alloys, especially special cast alloys based on nickel and nickel / cobalt, which also include chromium, carbon and aluminum and more than about 5% by weight of a previously remelted and cast Alloy included.

In the German patent application P 19 21 359 · 3, the Applicant deals with one of the occurring in the development of alloys used for manufacturing cast hot stage gas turbine metal parts major problems is that of the alloy at temperatures of about 760 ⁰ G to give sufficient ductility. According to this patent application, it is _v possible by incorporation of about 1.0 to about 4.0 wt - produce% hafnium in a ^ -Primärphanenenthaltende cast alloys based on nickel, to be used for the preparation of Heißetufen gas turbine metal parts, highly reliable and resistant alloys. that when tested under a load of ^{6,600 kg / cm 2} at 76O ⁰ O during the creep strain of the third

109810 / U49

_ P -

Relatively uniform, predictable failure level demonstrate.

Alloy B described in this patent application is an alloy that contains O, / T % carbon, 8 % chromium, 10 % cobalt, 6 % molybdenum, 4.25% tantalum, 1 % titanium, 6 % aluminum, Contains 0.015 % boron, 0.10% zirconium, the remainder nickel. The statistical analysis of this engineered alloy, which is referred to in the above-mentioned patent application as alloy B, shows that the values for the percentage previous creep that occurs when the alloy is examined for creep fracture ^{at 760 ° C} 1 of the accompanying drawing as curve A. The percentage previous creep elongation means the percentage creep elongation more than 1 hour before the break produced batch "or" remelted batch "is to be understood as an alloy melt ^ which contains about 5% by weight or more of a metal _% that has previously been remelted and poured into the alloy mold Main alloy is first poured into an ingot, the ingot is then melted and shaped into for Men are cast which have the shape of the end products, the excess parts being cut away from the cast product and these excess parts being converted into the subsequent batch either alone or with the addition of a fresh ingot material. will. Another analysis has shown that this sloping curve is the result of a statistical distribution between fresh and remelted batches

A slightly different itatißtieek © analysis, the ISS: fig practice is "1 illustrated the accompanying drawings _t -feat g @ s @ IGF _s .that the curve A a synthesis of dta RgieohdelrauBgabruok. the second stage, curve B ₁ and the creep expansion bridge of the third stage »

also called "Zeitatand Behavior" -

f09810 / 1

Curve C. It is possible that the low levels of both fresh and remelted batches are caused by failure of the second stage creep. Although this undesirable creep strain s / ^{V r} t ^a Ser second stage occurs more frequently in remelted batches, it also occurs in fresh batches.

It is therefore an aim of the present invention to manufacture of highly beneficial turbine engine metal parts made from batches containing remelted material, that, if it were left unmodified, own * - would have a technical scope that lie at the lower end of the scatter area «

Another object of the present invention is to a method of making cast metal gas turbine engine parts from batches containing remelted alloys that have a normal statistical distribution of technical properties.

'Further objects of the present invention are to provide a Specify methods of manufacturing gas turbine engine metal parts cast from batches of remelted alloys; which has a greatly improved resistance to the adverse effects of time at high temperature on the Have impact resistance, as well as in it, new alloys and alloys with a to create improved ductility. ·

The Fig. 1 of the accompanying drawing is a graphical representation of the frequency of occurrence of the values of percentage in the previous creep tested at 76o C ⁰ formations both within and outside the scope of '' the present invention.

Nine batches of alloys according to the invention were made with the composition of alloy B, but the '. instead of an equal amount of nickel about 1 to about 2% by weight

109810/1 U9

Contained hafnium .. Five of these alloy batches were made made using remelted metal, four of the batches were made from fresh materials. Processed samples from produced from these batches. Shovels were used to determine the breaking strength / and the percentage of previous creep elongation at 760 C and 6 600 kg / cm tested * None of the alloys of the invention failed at the second-stage creep, indicating excellent reliability. The distribution curve for the values of the previous percentage creep strain for these alloys is curve D of FIG. 1 of the accompanying drawings. Drawing and the values on which this curve is based are given in Table I below.

V or R * Table I. 1.70 Hours. 760 ° C / 6600 kg / cm ² Batch Gewo% Hf test at previous creep No. • 86.6 elongation in % V 91.1 5.59 1 1.40 94.7 5.76 87.7 3.83 75.3 4.51 V 83.4 3.80 2 1.29 69.1. 5.44 119.7 4.02 126.6 7.42 V 91.1 6.82 3 1.40 50.4 , 4.66 65.5 2.30 65.7 5.85 V 93.7 3.56 4th 61.9 6.59 94.7 * 3.46- 5.99

"^ '(Term for time to break)

109810 / U49

Continuation; from (Table I.

Batch V or R * wt.% Hf • Test at 760 ° C / 6600 kgf / cm ² Mr. Hours. previous creep 1.46 elongation in; ό 5 R. 1.48 - 91.5 5.50 91.4 5.40 107.9 5.10 1.06 55.8 5.08 6th R. 1.64 * - 85.2 4.51 • 77.8 4.75 97.6 4.71 1.45 85.2 5.92 7th R. 70.1 5.46 78.2 4.08 89.6 4.55 remelted 104.3 5.55 8th R. 97.8 6.07 85.4 4.46 108.1 7.1 119.5 6.30 9 R. 100.1 5.45 76.0 4.30 101.4 4.72 63.1 2.62 • freshness or Batch

A statintinche evaluation of the information in the table above with respect to the percent previous creep following »

109810 / t 4 4 9

6 - fresh
Batch 0.1315 2Ö348Q8 together
put batch 4.975 % • 16 umgeschmol
zene batch 4.92 % average value 1.423 * not beveled distributions 4.88 % 1.19. Sigma. Bevel value (IbdeviationP, 00013 *
(Measure of Skewness) 1.01 0 ^ 0000 * Frequency value,
(Measure of Kurtosis) 0.0000 * 0 * 074 Number of measuring points 0.1659 36 20th

The same batches with no added hafnium showed an average (2) of 1.37% previous creep strain with a standard deviation of 0.69. Obviously, this is heavily sloped, since the X-2 sigma value is an impossibly negative one Is worth.

From the above, it is apparent _that% no substantial difference between fresh and remelted batches exists when in place in the alloy B amounts greater than about 1% hafnium, the same weight amounts of nickel are introduced. Moreover, since the probability curve for the values of the percentage previous creep strain of the alloys of the invention is a normal probability curve, it is clear _f that more than 95% der.Proben the alloys of the invention which have been / nergesteilt of buckets, presumably under the specified test conditions prior creep strain of have more than 2.5%.

Ea is also interesting that the breaking strength of the Alloys according to the invention indicated in Table I from a minimum value of about 50 hours to a maximum value of about 125 hours. Appropriate test samples tiner unmodified alloy B showed breaking strengths within the range of about 2 to about 28 hours to *

The compositions in wt .- # of further examples of

aptnabhebimd ("machined from")

ORIGINAL INSPECTED

advantageous, hafnium-containing alloys against the adverse effects of remelted material are stable are given in Table II below.

Table II Example no.

Element 1 2 5 4 5 β 0 0.12 0.14.0.05 0.10 0.13 0.10 Cr 9 9 9 9.0 9.0 9.0 Co 9 9 9 10 10 10 W 9.9 9 , 6 10. 12.2 11.5 11.8 Mo 2.5 ■ 2.4 ■ - ■■ ₄ ■ ■ - - -Ta - ■ - '1.5 .'- ■■■■ - Nb - - - 1.0 1.1 1.0 Ti ■ 1.5 1.5 -1.5 2.0 2.0 2.0 Al 5.5 5.5 5.5 5.0 5.0 5.0 Hf 1.5 3.3 4.5 '1.6 1.1. 2.3 Ni remainderE remainderE remainderE remainderE remainderE Zr 0.05 0.05 0.05 0.05 0.05 0.05 B 0.0150.0150.0150.0150.0150.015

Each of the examples in Table II above exhibited an excellent combination of mechanical properties and was generally used in the manufacture of gas turbine metal parts Suitable for precision casting.

Fresh alloys according to the invention have compositions which are generally within the ranges stated in patent application P 19 21 359.3, with the exception that it has been found to be expedient to keep the Hafniunehalr within the range of about 0.7 or even 1 to to hold about 5 wt .-%. The total percentage of titanium, + aluminum should be at least 6%, preferably about 6.5 to _; , be about 10.5% and the carbon content can be up to · 0.5% by weight>. It is very useful to match the hafnium content to the carbon content so that the two elements are present in approximately equal amounts on an atomic basis.

_{10981fl / m9}

Cobalt, if present, is preferably on 'one Amount limited to about 20% by weight, the total percentage of tantalum + chromium not exceeding 16%, and the alloys according to the invention, both the fresh and the remelted alloys, have a hardness factor (HF), which is within the range of 60 to 72 and is calculated from the following equation: 1x% Cr + 1.1x% (W + Mo) + 3.4x% (Nb + Ta) + 4.3% Ti + 6x # Al = HF the percentages of the various elements relate on weight.

For the sake of convenience, the numerical value represented by this equation is referred to as the "hardness factor" in the following description and in the claims. If this Hartbarkeitsfaktor thus defined as the value exceeds 60, the cast samples produced from this alloy, in general, have a breaking strength of at least about 1000 hours when tested at 898 ⁰ C under a load of 1404 kg / cm. Most of the alloys according to the invention have breaking strengths of 1000 hours under a load of 1,440 kg / cm at temperatures above 926 ^° C. The temperature at which an alloy has a breaking strength of 1000 hours at a load of 1404 kg / cm, is sometimes referred to as the "temperature capability" of this alloy. Further examples of alloys according to the invention are given in Table III below.

• 1 0 9 8 1 Π / 1 U 9

7th Tabel 8th 9 III 11 0 12th 13th 14th alloy 0.15 0.12 0.18 10 0.12 9 , 14 0.05 0.12 C. 9.0 10.0 10.0 0.05 9 9 9 12.5 Cr 10.0 - 15.0 12.0 9 2 9 - Co - 1.5 - - 2.5 9 A. 4.2 - Mon 10.0 2.0 - 4.5 9.9 1 , 6 10 - - W. 1.5 1.0 - 1.5 5 , 5 1.5 0.8 Ti 5.5 6.5 5.5 0.6 5.5 , 5 5.5 6.1 Al 0.015 0.020 0.014 5.9 - - - - B. 0.05 0.10 Q, 06 0.010 - - - Zr 1.5 2.0 - 0.10 - 3 - 1.5 - Ta 2.5 2.5 2.5 ■ - 1.5 , 3 1.5 Hf rest rest rest 1.5 Rest* Rest* Rest* Rest* Ni - 1.0 - Rest, - - 2.0 Nb M. _ * 1.0 2.0 V mm ' - -

* contains small, common amounts of boron and zirconium

The results of room temperature tests performed with cast turbine wheels of alloy F, a known one, about 0.5 wt.% Carbon, about 12 wt.% Chromium, about 4.5 wt.% Molybdenum, about 0.6 wt. -% titanium, about 5.9 wt. -96 aluminum, about 2 wt.% Niobium, about 0.010 wt.% Boron, about 0.1 wt 10), which contained 1.5% by weight of hafnium instead of an equal amount by weight of nickel, samples were prepared, are given in Table IV below.

Table IV

Zuntand the properties unmodified modified Lep; ifining LBflierunf); F Len ^ erum »; F.

poured UTß. (kg / cm ² ) * 8075 8425

(Aß-Cant)

gonnrm Yn (kg / cm ² ) 7021 7221

Elongation% 5 12

1098 1 Π / 1 AA 9

- ίο -

Continuation from Table IV

State of properties unmodified modified :: -

Alloy alloy F alloy?

heat treated * UTS (kg / cm ² ) 8004 8425

¹¹ YS (kg / cm ² ) 7161-021

"Elongation % 2.0.12

* Hold at 982 ⁰ C for 4 hours,
** ultimate tensile strength
*** Stretch limit

Table IV above shows that for moldings from the Alloy F not only enhances the present invention the tensile elongation, but also for the production of a molding with less sensitivity to the adverse effects of heat treatment, often as part of a process to produce a corrosion protection coating on esa molding is necessary, is useful.

The present invention also relates to the impact

. . , Stress. . , _ _m ^ * _ * .- *. effects of high /. Nickel-based alloys which are resistant to high temperatures and which are also particularly resistant to the loss of impact resistance when heated are known to occur at high temperatures Heating to temperatures of about 1093 ⁰ C without any effect: irf ^ ^s ^ ^pu iߧi considerable loss ar. Room temperature impact resistance occurs. Data which show this loss compared to alloy A, which is described in patent application P 19 21 359.3, and the great improvement in the modification of this alloy A by replacing 2.1% by weight of molybdenum with an equal amount by weight of hafnium , are given in Table V below.

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Table V

Impact strength in mkg Impact strength in n> g of sample X * of sample Y **

Alloy cast after 50 hours, cast after 50 hours "___ (as cast ) at 1093 0. ______ at 1093 3

Alloy A 4.14-6.9 2.76-4.14 1.8-2.0? 0.69 alloy

with Hf 11.05-14.1 12.7 3.86-4.97 5.10-5.52

* Sample X was an unnotched Charpy round notch sample.

ρ represents that of a rod with a cross-section of 0.993 cm duration.

** Sample Y was an unnotched Charpy round notch sample which consisted of a round rod with a diameter of 0.713 cm.

The data given in the above label V show not only that the hafnium-containing alloy not only that a much higher initial impact strength than the comparative alloy showed, but that also when heated / (e.g. 50 Hours at 1093 ° C.) there was no noticeable reduction in this impact strength.

This is demonstrated by the values in Table V above Aspect of the present invention is in part also on alloys with a hardened ^ primary phase based on nickel that contain molybdenum. So far had Molybdenum has been shown to be an effective alloying element in alloys for use in the hot stages of gas turbine engines are suitable. However, if engine temperatures and alloy content are both forged and also increase on cast alloys, the loading is approaching. operating temperatures such temperatures at which certain harmful carbides and other phases can arise in the alloy. It is believed that by replacing molybdenum hafnium prevents the formation of these harmful phases during operation. The fact that the replacement

'to high temperatures

109810/1449

of molybdenum does more with hafnium than merely eliminating a disadvantage of the molybdenum-containing alloys. The as-cast condition of the as-cast condition of the hafnium-containing alloy is considerable. higher than the impact strength of alloy A, which indicates a considerable technical step. The mkg values given in Table V for the hafnium containing alloy are essentially the same as the _t values measured on some alloys originally used for aircraft gas turbine engines during development in Great Britain in the late 1930s and "early 1940s". These British alloys had a temperature performance, defined as the temperature at which breakage occurs at 1406 kg / cm in 1000 hours, of no more than about 788 C. Alloy A and its modification containing hafnium have one Temperature output of about 971 ⁰ C on. Generating the fact that it is possible to have the same resistance to sudden forces in alloys that can be used up to 971 ⁰ C, as indicated for the alloys can only be used up to 788 ⁰ C, of paramount importance to the development of gas turbine engines from a practical point of view.

Compositions of other alloys of the invention in% by weight are given in Table VI below.

BATH 109810 / 1U 9

1? Table VI 17th • 1.1 18th 19th 20th 21st LeRierunR 0.15 16 0.13 rest 0.10 0.12 0.18 0.05 C. 9.0 0.10 9.0 1.1 9.0 10.0 10.0 12.0 Size 10.0 9.0 10.0 10.0 - 15.0 ■ - - Co - 10.0 - - 1.5 mm 4.5 Mon 10.0 - 11.5 11.8 2.0 - .- .. W. 1.5 12.2 2.0 2.0 1.0 0.6 Ti 5.5 2.0 5.0 5.0 6.5 5.5 5.9 Al 0.015 5.0 0.01 0.01 0.020 0.014 0.010 B. 0.05 0.01 0.05 0.05 0.10 0.06 0.10 Zr 1.5 0.05 2.0 - - Ta 2.5 - 2.3 2.5 2.5 - 1.5 Hf rest 1.6 rest rest Rest rest Ni - Best 1.0 1.0 - 2.0 Nb 1.0 1.0 _ V

How important it is to keep the hafnium content at about 0.7 or 0.8 % in order to achieve considerable advantages in fresh alloys can be seen from a comparison of the alloys of Examples 16, 17 and 18 with an alloy which is identical in composition therewith which, however, only contains 0.6 % hafnium. Such a comparison is shown in the following Table VII over samples which have been heat-treated in an identical manner by long aging at about 84-5 ⁰ C

6 Hf dragonfly VII Load ^ > 6319 0.6 Creep rape
at 760 ^° C Elongation % R.A.9 & Example p
Mr. 1.1 lifetime previous
Hour creep
(Tool life) now ^ % N.M. * Ν, Μ. · Comparative-
alloy 1.6 79.1 N.M. * 1.5 4.2 16 2.3 407.8 1.5 3.0 6.4 17th 467.1 2 * 0 3.5 6.8 18th 448.1 3, oa

• K.M, - not measurable

tO98in / U49

The above Table VII shows that an alloy which is essentially a modification of the alloy C of the patent application P 19 21 359.3, and contains 0.6% hafnium, an unsatisfactory behavior in the creep strain at break / □ when at 760 ^Q C was tested after a heat treatment, which should highlight the disadvantages at this test temperature. Table VII above. also shows that the effect of hafnium in improving the alloy is noticeable at 1.1% and gradually increases with increasing hafnium content up to about 2%. These data illustrate the general rule given above that at least 0.7 % hafnium is required to achieve a significant improvement in the primary alloys. Changes in the alloy composition can vary the minimum effective percentage of hafnium within the range of more than 0.5% to more than 0.7 % .

From a certain point of view, it may also be more appropriate to use at least about 1.0 % hafnium, ζ. B. incorporate about 1.5 % hafnium in the fresh alloys, but hafnium is a relatively expensive element. Since practical needs dictate that the best results should be obtained at the lowest possible cost, the lower limit on the hafnium content for fresh alloys has been set at "at least greater than 0.05 %" to accommodate situations in which the results according to the invention can be achieved at the lowest possible cost.

Creep test

Claim «! 1 0 9 8 1 Π / 1 A 4 S OHlGlNAL INSPECTED

Claims (18)

-ν * 203460a Pat e nt a n s ρ r ü c h e, 1. Cast alloy that is more than about 5% by weight of a previously Remelted and cast alloy contains, on a nickel or nickel / cobalt basis, the chromium, carbon and aluminum contains, characterized in that it contains about 0.3 to about 5% by weight of hafnium and one or more of the elements tungsten, molybdenum, tantalum, niobium, titanium, vanadium, zirconium and boron so that it has a Ϋ primary phase in the as-cast condition and is particularly suitable in the cast state is for use under load at temperatures above about 898 ° C. 2. cast alloy according to claim 1, dadurch.gekennzeichnet that up to 6 wt.% Tantalum, about 6 to about 12 wt.% Aluminum + titanium and having a hardenability factor of at least about 60 · 3 · cast alloy according to claim 1, characterized in that it comprises about 0.02 to about 0.2 wt% carbon, about 7 to about 13 wt .-% chromium, up to about 35 wt -..% Cobalt, up to about 14 wt .-% tungsten, up to about 8 wt .-% molybdenum, up to about 6 wt .-% tantalum, about 0.5 to about 6 wt -..% titanium, about 4 to about 7 wt% aluminum, about 6.5 to about 10.5% by weight aluminum + titanium, about 0.002 to about 0.2 % by weight boron, up to about 0.15% by weight zirconium, up to about 3% by weight niobium and Contains up to about 1.5% by weight of Vr-nadine. ■ " 4. cast alloy according to claim 1, characterized in that it comprises about 0.1 to about 0.18 wt% carbon, about 7 to about 11 wt .-% chromium, about 6 to about 13 wt -..% Cobalt, about 8 to about 12 wt .-% tungsten, about 2 to about 3 wt .-% molybdenum, up to about 3 wt .-% tantalum, about 1 to about 2 wt .-% titanium, about 5 to about 6 wt -.% Contains aluminum, about 0.004 to about 0.02 wt.% Boron, about 0.02 to about 0.2 wt.% Zirconium, and about 0.3 to about 4 wt.% Hafnium, the remainder being essentially Niekei is ·. 109810 / 1Λ4 9 5 · Cast alloy according to claim 1, characterized in that it contains about 0.03 to about 0.13 wt .- # carbon, about 7 to about 10% by weight of chromium, about 6 to about 13% by weight of high, up to about 2 wt .-% tungsten, about 4 to about 8 wt .-% molybdenum, about 2.5 to about 4.5 wt% tantalum, about 0.5 to about 1.5% by weight titanium, about 5 »5 to about 6.5% by weight aluminum, about 0.004 to about 0.02 weight percent boron, about 0.02 to about 0.2 weight percent zirconium, and about 0.3 to about 4 weight percent hafnium with the remainder being essentially nickel. 6. A castable alloy containing a eutectic jp-primary Gußpiiase, characterized in that it consists of about 0.02 to about 0.5 wt -.% Carbon, about 7 his about 13 Gei> .-% chromium, up to about 35 wt .-% cobalt, up to about 8 wt .-% molybdenum, up to about 14 wt .-% tungsten, up to about 3 wt .-% & niobium, up to 6 wt .-% tantalum, about 4 to about 7% by weight of aluminum, about 0.5 to about 6% by weight of titanium, the total amount of aluminum plus titanium being about 6.5 to about 10.5% by weight; ^: is, up to about 1.5% by weight vanadium, up to about 0.2% by weight zirconium, about 0.002 to about 0.2% by weight boron and about 0.7 to about 5% by weight % Hafnium, with the remainder being essentially nickel and that nickel is present in an amount of at least about 36% by weight, that it has a hardenability factor of at least about 60, for use under stress at temperatures up to about 1037 _tons 8 ° C is suitable and compared to correspondingly composed, hafnium-free alloys has an improved ductility at temperatures of about 704 to about 815 ° C. In that it comprises 7. The alloy of claim 6, characterized in that a hardenability factor of about 60 to about 72, about 1 to about 4 wt -.% Hafnium, up to about 20 wt .- £ contains cobalt, the carbon and? Hafnium content are coordinated so that these elements together in . approximately equal amounts, based on an atomic basis, are present 8. Alloy according to claim 6, characterized in that it 1098 10 / U49 about 1 to about 2 wt .-% hafnium and up to about 15 wt .-% Contains cobalt. 9. Alloy according to claim 6, characterized in that it contains a maximum of 13% by weight of tantalum plus tungsten. 10. A castable alloy which has a eutectic ^ -Primär-Gußphase, characterized in that it consists essentially of about 0.04 to about 0.35 wt .-% carbon, from about 7 to about 13 wt -.% Chromium, about 0 to about 15 wt .-% cobalt, up to about 12.5 wt .-% tungsten., up to about 6 wt .-% molybdenum, up to about 5 wt .-% tantalum, with the proviso that the sum of the amount by weight of tantalum plus tungsten less than 13 wt .-%, is from about 0.6 to about 5 wt -.% titanium, about 4.5 to about 6.7 wt -.% aluminum, the total amount of aluminum plus titanium is at least about 6.5 wt -.%, is from about 1 to about 5 wt -.% hafnium, up to about 1.1 wt .-% vanadium, up to about 2.2 wt -.% niobium, up to about 0.2 wt% zirconium, about 0.002 to about 0.2 wt% boron, with the remainder consisting essentially of nickel. 11. Castable alloy, characterized in that it is in essentially consists of about 0.10 to about 0.18% by weight Carbon, about 7 to about 11 wt% Ohrom, about 6 to about 13% by weight cobalt, about 8 to about 12% by weight tungsten, ' about 2 to 3% by weight molybdenum, up to about 3% by weight tantalum, about 1 to 2% by weight titanium, about 5 to about 6% by weight aluminum, wherein the total amount of aluminum plus titanium is at least about 6.5 wt%, about 0.004 to 0.02 wt% boron, about 0.02 to 0.2% by weight of zirconium and about 1 to 5% by weight of hafnium, the remainder consisting essentially of nickel. 12. Castable alloy, characterized in that it consists essentially of about 0.03 to 0.13 wt .-% carbon, about 7 to 10 weight percent chromium, about 6 bia 13 wt -.% Cobalt, up to about 2 wt .-% tungsten, about 4 wt .-% bia 8 molybdenum, about 2.5 to 4.5 wt .-% of tantalum, 1.5 wt EBWA 0.5 bie .-% titanium, > / Ζ ;; V '■■■ 109810/1 /, 4 9 about 5.5 to 6.5 wt .- ^ aluminum, the total aluminum plus-titanium is at least about 5 wt .-% 6 _f. about 0.004 to 0 _? 02 wt -.% Boron, about 0.02 to 0.20 wt _e -% zirconium, and about 1 to 5 wt .-% hafnium, the balance being. consists essentially of nickel. Pourable Leglerungj characterized in that it consists essentially of about 0.05% by weight carbon, about 12% by weight chromium, about 4.5% by weight molybdenum, about 0.6 Wt% titanium, about 5.9 wt% aluminum, about 0.010 wt% Boron, about 0.10 wt% zirconium, about -2.0 wt% niobium, about 1 to about 5% by weight of hafnium, with the remainder essentially consisting of nickel »· 14. Fresh alloy or greater than about 5% by weight of a previous one Alloy containing remelted and cast alloy on a nickel and / or nickel / cobalt basis, which contains chromium, Contains carbon and aluminum, characterized in that it contains about 0.3 to 5% by weight of hafnium, at least one of the contains the following elements: tungsten, molybdenum, tantalum, niobium, titanium, vanadium, zirconium and boron, and that it contains 0.02 to 0.5% by weight carbon, 7 to 18% by weight chromium, to 0.3% by weight of zirconium and a total of 6.5 to 12% by weight Aluminum plus titanium. 15 · Process to minimize the adverse effects of the content of remelted material on alloy batches based on nickel and nickel / cobalt, which contain chromium, carbon and aluminum as well as at least one of the elements tungsten, molybdenum, tantalum, NioTbj titanium, vanadium, zirconium and boron included, wherein the alloy in the solidified casting form has a y-primary phase and sum casting in the geachraolsenem state to final forms is particularly suitable and imatande, in the cast state under one. Load to be used at temperatures above about 898 ⁰ C, "characterized in that it contains about 0.3 to @ about 5 Oewo-% Hafniua ^ that 'is incorporated into a batch of this alloy _ö dia ain ° - deatena § about 5 % By weight of a previously lamgesehssolEöaea wiä cast 109810 / U49 Material contains "before casting to thereby avoid any adverse effect of the content of remelted material to neutralize the batch treated in this way, and that then this alloy is cast to the final shape. 16. The method according to claim 15, characterized in that that the alloy is in the molten state under high vacuum conditions is held until the alloy has solidified in its final shape. 17 · The method according to claim 15 »characterized in that the alloy is composed to have a hardenability factor of at least about 60 and about 6 to about 12% by weight aluminum "plus titanium and up to 6% by weight tantalum contains ·. ~ 18. Use of a casting alloy according to claim 1-14 for Manufacture of turbine metal parts, in particular metal parts for gas turbine engines. 1098TO / 1U9 e e QD rse ite