High temperature-resistant material based on gamma titanium aluminide

In a heat engine, a high temperature-resistant material with inter-metallic compounds in the titanium/aluminum system, comprising an aluminum content of from 45 to 48 atom %, a niobium content of from 0.5 to 3 atom %, a chromium content of from 0.5 to 3 atom %, a silicon content of from 0.1 to 2 atom %, an oxidation resistance-enhancing element selected from the group consisting of, in atom %, 0.5 to 3 tantalum, 0.5 to 3 molybdenum, 0.5 to 3 tungsten, 0.5 to 3 vanadium, 0.1 to 1 boron, 0.01 to 1 carbon, 0.01 to 1 nitrogen, 0.01 to 1 yttrium, 0.01 to 1 cerium, 0.01 to 1 erbium, and 0.01 to 1 lanthanum, and a remainder of titanium;

• said yttrium, cerium, lanthanum and erbium summing to a total of no more than 2 atom %;
• and
• said niobium, chromium, silicon, tantalum, molybdenum, tungsten, vanadium, boron, carbon, and nitrogen summing to a total of no more than 10 atom %.

In an internal combustion engine, a high temperature-resistant material with inter-metallic compounds in the titanium/aluminum system, comprising an aluminum content of from 45 to 48 atom %, a niobium content of from 0.5 to 3 atom %, a chromium content of from 0.5 to 3 atom %, a silicon content of from 0.1 to 2 atom %, an oxidation resistance-enhancing element selected from the group consisting of, in atom %, 0.5 to 3 tantalum, 0.5 to 3 molybdenum, 0.5 to 3 tungsten, 0.5 to 3 vanadium, 0.1 to 1 boron, 0.01 to 1 carbon, 0.01 to 1 nitrogen, 0.01 to 1 yttrium, 0.01 to 1 cerium, 0.01 to 1 erbium, and 0.01 to 1 lanthanum, and a remainder of titanium;

• said yttrium, cerium, lanthanum and erbium summing to a total of no more than 2 atom %;
• and
• said niobium, chromium, silicon, tantalum, molybdenum, tungsten, vanadium, boron, carbon, and nitrogen summing to a total of no more than 10 atom %.

In a gas turbine, a high temperature-resistant material with inter-metallic compounds in the titanium/aluminum system, comprising an aluminum content of from 45 to 48 atom %, a niobium content of from 0.5 to 3 atom %, a chromium content of from 0.5 to 3 atom %, a silicon content of from 0.1 to 2 atom %, an oxidation resistance-enhancing element selected from the group consisting of, in atom %, 0.5 to 3 tantalum, 0.5 to 3 molybdenum, 0.5 to 3 tungsten, 0.5 to 3 vanadium, 0.1 to 1 boron, 0.01 to 1 carbon, 0.01 to 1 nitrogen, 0.01 to 1 yttrium, 0.01 to 1 cerium, 0.01 to 1 erbium, and 0.01 to 1 lanthanum, and a remainder of titanium;

• said yttrium, cerium, lanthanum and erbium summing to a total of no more than 2 atom %;
• and
• said niobium, chromium, silicon, tantalum, molybdenum, tungsten, vanadium, boron, carbon, and nitrogen summing to a total of no more than 10 atom %.

In an aircraft engine, a high temperature-resistant material with inter-metallic compounds in the titanium/aluminum system, comprising an aluminum content of from 45 to 48 atom %, a niobium content of from 0.5 to 3 atom %, a chromium content of from 0.5 to 3 atom %, a silicon content of from 0.1 to 2 atom %, an oxidation resistance-enhancing element selected from the group consisting of, in atom %, 0.5 to 3 tantalum, 0.5 to 3 molybdenum, 0.5 to 3 tungsten, 0.5 to 3 vanadium, 0.1 to 1 boron, 0.01 to 1 carbon, 0.01 to 1 nitrogen, 0.01 to 1 yttrium, 0.01 to 1 cerium, 0.01 to 1 erbium, and 0.01 to 1 lanthanum, and a remainder of titanium;

• said yttrium, cerium, lanthanum and erbium summing to a total of no more than 2 atom %;
• and
• said niobium, chromium, silicon, tantalum, molybdenum, tungsten, vanadium, boron, carbon, and nitrogen summing to a total of no more than 10 atom %.