Material system for high temperature jet engine operation
AssigneeGeneral Electric Company
InventorMelvin R. Jackson
Life of this patent
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Abstract
A materials system is provided which is adapted for use in jet engines operable at high temperature and at lower density than possible with nickel base superalloys. A range of niobium base alloys is combined with a range of protective metallic coatings to provide a material system which permits a wide variety of alloy properties and performance characteristics to be combined in structural components of jet engines.
Claims5
A composite structure having high strength at high temperatures, said structure comprising a shaped structural metal substrate of at least one metal selected from the group consisting of the following niobium base alloys as follows:.
- A Niobium;
- 31-48 a/o titanium;
- 8-21 a/o aluminum
- B Niobium;
- 32-48 a/o titanium;
- 8-16 a/o aluminum;
- 2-12 chromium provided that the sum (Al+Cr).ltoreq.22% a/o, and where Ti is less than 37 a/o the sum (Al+Cr).ltoreq.16 a/o
- C Niobium;
- 40-48 a/o titanium;
- 12-22 a/o aluminum;
- 0.5-6 a/o hafnium
- D Niobium;
- 32-45 a/o titanium;
- 8-15 a/o hafnium;
- 3-18 a/o aluminum
- E Niobium;
- 35-45 a/o titanium;
- 8-15 a/o hafnium
- F Niobium;
- 4-10 a/o hafnium;
- 4-10 a/o aluminum;
- 5-18 a/o titanium;
- 3-8 a/o chromium
- G Niobium;
- 5-18 a/o hafnium;
- 5-22 a/o aluminum
- and a protective metal coating on at least a portion of the substrate surface to protect the substrate from environmental attack, said coating having the composition as defined within the enclosure A of FIG. 3.
Dependencies are inferred from the claim text.