초록 ▼

An alloy for aircraft roller bearings containing: 0.45 to 1.0 wt. % carbon, max 2.0 wt. % manganese, max 1.0 wt. % silicon, 8.5 to 11.5 wt. % chromium, 1.0 to 4.5 wt. % molybdenum, 1.0 to 2.5 wt. % vanadium, max 2.0 wt. % tungsten,

An alloy for aircraft roller bearings containing: 0.45 to 1.0 wt. % carbon, max 2.0 wt. % manganese, max 1.0 wt. % silicon, 8.5 to 11.5 wt. % chromium, 1.0 to 4.5 wt. % molybdenum, 1.0 to 2.5 wt. % vanadium, max 2.0 wt. % tungsten, max 0.5 wt. % niobium, max 0.5 wt. % tantalum, max 3.0 wt. % nickel, max 0.5 wt. % cobalt, max 0.1 wt. % aluminum, max 0.01 wt. % nitrogen, and the balance being iron and impurities due to production.

대표청구항 ▼

What is claimed: 1. An alloy for aircraft roller bearings, wherein the alloy comprises: from 0.45 to 0.85 wt. % of carbon, not more than 2.0 wt. % of manganese, from 0.05 to 1.0 wt. % of silicon, from 8.5 to 11.5 wt. % of chromium, from 2.5 to 4.5 wt. % of molybdenum, from 1.65 to 2.5 wt. % of vana

What is claimed: 1. An alloy for aircraft roller bearings, wherein the alloy comprises: from 0.45 to 0.85 wt. % of carbon, not more than 2.0 wt. % of manganese, from 0.05 to 1.0 wt. % of silicon, from 8.5 to 11.5 wt. % of chromium, from 2.5 to 4.5 wt. % of molybdenum, from 1.65 to 2.5 wt. % of vanadium, not more than 2.0 wt. % of tungsten, not more than 0.5 wt. % of niobium, not more than 0.5 wt. % of tantalum, from 0.02 to 3.0 wt. % of nickel, not more than 0.5 wt. % of cobalt, not more than 0.1 wt. % of aluminum, not more than 0.01 wt. % of nitrogen, balance iron and impurities due to production. 2. The alloy of claim 1, wherein the alloy comprises from 0.55 to 0.85 wt. % of carbon. 3. The alloy of claim 2, wherein the alloy comprises not more than 0.75 wt. % of carbon. 4. The alloy of claim 1, wherein the alloy comprises from 9.5 to 10.5 wt. % of chromium. 5. The alloy of claim 1, wherein the alloy comprises not more than 3.5 wt. % of molybdenum. 6. The alloy of claim 5, wherein the alloy comprises from 2.65 to 3.25 wt. % of molybdenum. 7. The alloy of claim 1, wherein the alloy comprises from 1.8 to 2.25 wt. % of vanadium. 8. The alloy of claim 1, wherein the alloy comprises not more than 0.5 wt. % of tungsten. 9. The alloy of claim 1, wherein the alloy comprises not more than 0.5 wt. % of nickel. 10. The alloy of claim 1, wherein the alloy comprises from 0.5 to 7% by volume of carbides. 11. The alloy of claim 1, wherein the alloy comprises less than 3% by volume of metal carbides of formula M7C3. 12. An alloy for aircraft roller bearings, wherein the alloy comprises: from 0.55 to 0.85 wt. % of carbon, not more than 0.3 wt. % of manganese, from 0.05 to 0.2 wt. % of silicon, from 9.5 to 10.5 wt. % of chromium, from 2.5 to 3.5 wt. % of molybdenum, from 1.65 to 2.5 wt. % of vanadium, not more than 0.5 wt. % of tungsten, not more than 0.5 wt. % of niobium, not more than 0.5 wt. % of tantalum, from 0.02 to 0.5 wt. % of nickel, not more than 0.5 wt. % of cobalt, not more than 0.1 wt. % of aluminum, not more than 0.01 wt. % of nitrogen, balance iron and impurities due to production. 13. An alloy for aircraft roller bearings, wherein the alloy comprises: from 0.55 to 0.75 wt. % of carbon, from 0.21 to 0.3 wt. % of manganese, from 0.15 to 0.2 wt. % of silicon, from 9.5 to 10.5 wt. % of chromium, from 2.65 to 3.25 wt. % of molybdenum, from 1.8 to 2.25 wt. % of vanadium, not more than 0.5 wt. % of tungsten, not more than 0.5 wt. % of niobium, not more than 0.5 wt. % of tantalum, from 0.02 to 0.5 wt. % of nickel, not more than 0.5 wt. % of cobalt, not more than 0.1 wt. % of aluminum, not more than 0.01 wt. % of nitrogen, balance iron and impurities due to production. 14. A bearing or bearing part, wherein the bearing or bearing part comprises the alloy of claim 1. 15. A bearing or bearing part, wherein the bearing or bearing part consists of the alloy of claim 1. 16. The bearing or bearing part of claim 14, wherein the bearing or bearing part is a roller bearing or roller bearing part. 17. An aircraft turbine, wherein the turbine comprises the bearing or bearing part of claim 14. 18. A method of making a part or component of an aircraft, wherein the method comprises forming the part or component from the alloy of claim 1. 19. The alloy of claim 1, wherein the alloy comprises not more than 0.27 wt. % of manganese. 20. A bearing or bearing part, wherein the bearing or bearing part comprises the alloy of claim 13.