High entropy alloy
An alloy comprising by weight percent: 16.0-26.0 Cr; 23.0-34.0 Mo; 21.0-31.0 Ta; 0.50-3.5 Ti; and 17.0-27.0 V.
1 . An alloy comprising by weight percent:
19.25-23.25 Cr;
27.10-31.10 Mo;
24.25-28.25 Ta;
0.5-2.25 Ti;
15-24.15 V; and
no more than 5.0 Zr, if any.
2 . The alloy of claim 1 comprising by weight percent:
no more than 4.5 Zr, if any; and
0.5-5.0 said Ti and Zr combined.
3 . The alloy of claim 2 further comprising:
no more than 4.0 Nb, if any;
no more than 4.0 W, if any;
no more than 4.0 Al, if any;
no more than 3.0 all other elements individually, if any; and
no more than 6.0 all other elements, if any, combined.
4 . The alloy of claim 1 comprising by weight percent:
20.25-22.25 Cr;
28.10-30.10 Mo;
25.25-27.25 Ta;
0.75-1.75 Ti; and
21.15-23.15 V.
5 . The alloy of claim 1 comprising in weight percent:
20.25-22.25 Cr;
28.10-30.10 Mo:
25.25-27.25 Ta;
0.75-1.75 Ti; and
21.15-23.15 V.
6 . The alloy of claim 5 further comprising:
no more than 1.0 all other elements individually, if any; and
no more than 3.0 all other elements, if any, combined.
7 . The alloy of claim 1 wherein by weight percent:
(Mo+Ta) is 45.0-80.0; and
(Cr/V) is 0.25-1.6.
8 . The alloy of claim 1 further comprising:
no more than 4.0 Nb, if any;
no more than 4.0 W, if any;
no more than 4.0 Al, if any;
no more than 3.0 all other elements individually, if any; and
no more than 6.0 all other elements, if any, combined.
9 . The alloy of claim 1 further comprising:
no more than 1.0 all other elements individually, if any; and
no more than 3.0 all other elements, if any, combined.
10 . The alloy of claim 1 consisting essentially of:
said Cr; said Mo; said Ta; said V; said Ti, if any; said Zr, if any;
up to 2.0 weight percent each Y and Si, if any; and
up to 0.50 weight percent each B, C, O, and N, if any.
11 . The alloy of claim 1 having at least one of:
a density of 8.80 to 9.10 grams per cubic centimeter;
a 1300° C. yield point of at least 500 MPa; and
a melting point of at least 1600° C.
12 . The alloy of claim 1 having a BCC structure.
13 . The alloy of claim 1 as a coated substrate having a coating comprising one or more:
silicide-based coatings;
zirconia-yttria based coatings;
rare-earth oxide coatings; and
mixtures thereof.
14 . A gas turbine engine component comprising:
a substrate comprising:
4.8-26.0 Cr;
21.75-41.0 Mo;
21.0-50.0 Ta;
6.0-27.0 V;
no more than 18.0 Ti, if any; and
no more than 5.0 Zr, if any; and
a coating.
15 . The gas turbine engine component of claim 14 wherein:
the component is a hot section component.
16 . The gas turbine engine component of claim 15 wherein the component is selected from the group consisting of:
blades, vanes, blade outer air seals; combustor shell pieces, combustor heat shield pieces, combustor fuel nozzles, and combustor fuel nozzle guides.
17 . A coated substrate having:
a substrate comprising:
4.8-26.0 Cr;
21.75-41.0 Mo;
21.0-50.0 Ta;
6.0-27.0 V;
no more than 18.0 Ti, if any; and
no more than 5.0 Zr, if any; and
a coating comprising one or more:
silicide-based coatings;
zirconia-yttria based coatings;
rare-earth oxide coatings; and
mixtures thereof.
18 . The coated substrate of claim 17 wherein:
the coated substrate is a hot section component.
19 . The coated substrate of claim 18 wherein the component is selected from the group consisting of:
blades, vanes, blade outer air seals; combustor shell pieces, combustor heat shield pieces, combustor fuel nozzles, and combustor fuel nozzle guides.
20 . An alloy comprising by weight percent:
4.8-26.0 Cr;
21.75-41.0 Mo;
21.0-50.0 Ta;
6.0-27.0 V;
no more than 18.0 Ti, if any; and
no more than 5.0 Zr, if any,
the alloy having at least one of:
a density of 8.80 to 9.10 grams per cubic centimeter;
a 1300° C. yield point of at least 500 MPa; and
a melting point of at least 1600° C.