Abstract: A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes a first multiple of CMC plies which define a suction side, a first airfoil portion of the first multiple of CMC plies at least partially parallel to an airfoil axis. A second multiple of CMC plies define a pressure side, a second airfoil portion of the second multiple of CMC plies at least partially parallel to the airfoil axis and bonded to the first airfoil portion.

Abstract: A ceramic composite article includes ceramic carbide fibers and a ceramic matrix in which the ceramic carbide fibers are embedded. The ceramic matrix includes a laminar structure with at least one layer of a first ceramic material and at least one layer of a second, different ceramic material.

Abstract: A ceramic composite article includes ceramic carbide fibers and a ceramic matrix in which the ceramic carbide fibers are embedded. The ceramic matrix includes a laminar structure with at least one layer of a first ceramic material and at least one layer of a second, different ceramic material.

Abstract: A Ceramic Matrix Composite (CMC) airfoil segment for a gas turbine engine includes a box-shape fiber geometry which defines a rectilinear pressure side bond line and a rectilinear suction side bond line.

Abstract: A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes a first multiple of CMC plies which define a suction side, a first airfoil portion of the first multiple of CMC plies at least partially parallel to an airfoil axis. A second multiple of CMC plies define a pressure side, a second airfoil portion of the second multiple of CMC plies at least partially parallel to the airfoil axis and bonded to the first airfoil portion.

Abstract: A high temperature die casting system includes a die casting tool that has dies that are adapted for forming a component. The die casting tool is operable to heat and maintain a temperature of the dies above 500° F./260° C. At least a portion of the die casting tool that is exposed for contact with molten die casting material has a substrate and barrier coating on the substrate to protect from the molten die casting material.

Abstract: An example die casting system includes a die comprised of a plurality of die components that define a die cavity configured to receive a molten metal. One of the die components comprises a material that is not reactive with the molten metal and has a melting temperature above 815 degrees Celsius.

Abstract: A coated article includes an article having at least one surface and composed of a molybdenum based refractory metal alloy base substrate, a niobium based refractory metal alloy base substrate or a silicon base substrate. A bond coat layer is disposed upon the surface. The bond coat layer includes a molybdenum disilicide base compound and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A process for coating the article includes the steps of applying upon the article's surface the aforementioned bond coat layer. A functionally graded material layer is applied upon the bond coat layer. The functionally graded material layer comprising molybdenum disilicide, mullite and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A thermal barrier coating layer is then applied upon the functionally graded material layer.

Abstract: A coated article includes an article having at least one surface and composed of a molybdenum based refractory metal alloy base substrate, a niobium based refractory metal alloy base substrate or a silicon base substrate. A bond coat layer is disposed upon the surface. The bond coat layer includes a molybdenum disilicide base compound and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A process for coating the article includes the steps of applying upon the article's surface the aforementioned bond coat layer. A functionally graded material layer is applied upon the bond coat layer. The functionally graded material layer comprising molybdenum disilicide, mullite and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A thermal barrier coating layer is then applied upon the functionally graded material layer.

Abstract: A coated article includes an article having at least one surface and composed of a molybdenum based refractory metal alloy base substrate, a niobium based refractory metal alloy base substrate or a silicon base substrate. A bond coat layer is disposed upon the surface. The bond coat layer includes a molybdenum disilicide base compound and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A process for coating the article includes the steps of applying upon the article's surface the aforementioned bond coat layer. A functionally graded material layer is applied upon the bond coat layer. The functionally graded material layer comprising molybdenum disilicide, mullite and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A thermal barrier coating layer is then applied upon the functionally graded material layer.

Abstract: Molybdenum alloys are provided with enhanced oxidation resistance. The alloys are prepared by the addition of silicon and boron in amounts defined by the area of a ternary system phase diagram bounded by the points Mo-1.0% Si-0.5% B, Mo-1.0% Si-4.0% B, Mo-4.5% Si-0.5% B, and Mo-4.5% Si-4.0 B. The resultant alloys have mechanical properties similar to other high temperature molybdenum alloys while possessing a greatly enhanced resistance to oxidation at high temperature. The alloys are composed of a matrix of body centered cubic molybdenum surrounding discrete intermetallic phases. A variety of alloying elements are added to the base composition to modify the alloy properties.

Abstract: Methods of enhancing oxidation resistance and methods of making molybdenum alloys are provided. In these methods, alloys are prepared by the addition of silicon and boron in amounts defined by the area of a ternary system phase diagram bounded by the points Mo-1.0%Si-0.5%B, Mo-1.0%Si-4.0%B, Mo-4.5%Si-0.5%B, and Mo-4.5%Si-4.0 B. The methods utilize rapid solidification followed by consolidation at below the melting point. The resultant alloys have mechanical properties similar to other high temperature molybdenum alloys while possessing a greatly enhanced resistance to oxidation at high temperature.

Abstract: A method is taught for preparing titanium alloys having high temperature oxidation resistance, whereby a coating of a copper bronze containing up to 10 percent aluminum and up to 6 percent silicon is applied to the titanium substrate by cathodic arc deposition or ion vapor deposition.

Abstract: Composite materials comprising beta titanium alloy matrices containing high strength, high stiffness filaments are described. The matrix materials are true beta titanium alloys having very limited solid solubility for the filament materials. This low reactivity permits high fabrication temperatures and high use temperatures without formation of deleterious brittle phases. Also described is a method for fabricating such composites.

Abstract: A beta titanium alloy having exceptional high temperature strength properties in combination with an essential lack of combustibility is described. In its basic form the alloy contains chromium, vanadium and titanium the nominal composition of the basic alloy being defined by three points on the ternary titanium-vanadium-chromium phase diagram: Ti-22V-13Cr, Ti-22V-36Cr, and Ti-40V-13% Cr. The alloys of the invention are comprised of the beta phase under all the temperature conditions, have strengths much in excess of the prior art high strength alloys in combination with excellent creep properties, and are nonburning under conditions encountered in gas turbine engine compressor sections.

Abstract: Improved technology for the melting and casting of a particular class of true beta-type titanium alloys is described. A typical alloy is titanium--35% vanadium--15% chromium. By providing carbon surfaces for contacting molten beta titanium alloys of this type improved melting and casting procedures are effectuated.

Abstract: Process for improving the crack growth behavior of titanium alloys containing substantial beta stabilizers and at least 3% molybdenum, such as Ti-6-2-4-6. The process includes the steps of forging above the beta transus temperature, cooling at a controlled rate through the beta transus temperature, heating to a temperature between 50.degree.-150.degree. F. below the beta transus temperature, cooling the alloy at a rate in excess of that produced by air cooling, and aging the material between about 900.degree. F. and 1100.degree. F. The resultant material has substantially improved crack growth behavior when contrasted with material processed according to the prior art.