Abstract: A gas turbine engine comprises (A) a turbine including a nozzle and shroud assembly supported within the engine; the nozzle and shroud assembly including an inner annular ring member, an outer annular ring structure and a plurality of airfoils being positioned between the inner and outer ring structure, wherein at least one of the airfoils of the plurality comprises; (i) a substrate comprising a first electrically conducting material; and (ii) a wire of dissimilar electrically conducting material extending a measured distance in intimate contact with the substrate at a reference point and electrically insulated to a measuring point.

Abstract: A composition of matter is about 1 to about 3 percent rhenium, from about 6 to about 9 percent aluminum, from 0 to about 0.5 percent titanium, from about 4 to about 6 percent tantalum, from about 12.5 to about 15 percent chromium, from about 3 to about 10 percent cobalt, from about 2 to about 5 percent tungsten, from 0 to about 0.2 percent hafnium, from 0 to about 1 percent silicon, from 0 to about 0.25 percent molybdenum, from 0 to about 0.25 percent niobium, balance nickel and minor elements. The composition is preferably made into a substantially single crystal article, such as a component of a gas turbine engine.

Abstract: A solid oxide fuel cell comprises at least one hollow manifold, an anode, an electrolyte, and a cathode. The at least one hollow manifold comprises a wall that defines a chamber therein. A plurality of openings extending through, such that the plurality of openings are in flow communication with the chamber. The anode is formed on an exterior surface of the wall. The electrolyte is deposited on the anode, and the cathode is deposited on the electrolyte.

Abstract: A barrier coating is disclosed, containing about 15 atom % to about 95 atom % chromium; and about 5 atom % to about 60 atom % of at least one of rhenium, tungsten, and ruthenium. Nickel, cobalt, iron, and aluminum may also be present. The barrier coating can be disposed between a metal substrate (e.g., a superalloy) and an oxidation-resistant coating, preventing the substantial diffusion of various elements at elevated service temperatures. A ceramic overcoat (e.g., based on zirconia) can be applied over the oxidation-resistant coating. Related methods for applying protective coatings to metal substrates are also described.

Abstract: A system for measuring a condition of a turbine engine component comprises an assemblage of at least a film comprising an electrically conducting material disposed on a film of an electrically non-conducting material, the assemblage being disposed on a surface of the turbine engine component without removing material from the turbine engine component to compensate for thickness of at least one of the films. The electrically non-conducting material has a thermal expansion coefficient such that each of the films remains adhered to adjacent films through at least one cycle of extreme operating temperature. In addition, communication links can be provided to transmit the measurement representing the condition of the turbine engine to a remote user.

Abstract: An article for use in a hot gas path of a gas turbine assembly, a metallic skin for such an article, and a method for making such an article are presented with, for example, the article comprising a spar, the spar providing mechanical support for the article and comprising a cooling fluid delivery system, a top end, and a bottom end; a standoff structure attached to the spar, the standoff structure comprising a plurality of spacing elements in a spaced-apart relation to each other, the spacing elements having first ends adjacent to the spar and second ends opposite to the first ends; a skin conformally surrounding the spar and the standoff structure, the skin comprising a top end and a bottom end, wherein the standoff structure separates the spar and the skin, wherein the plurality of spacing elements is disposed with an inner surface of the skin adjacent to the second ends of the spacing elements to form a plurality of plena between the spar and the skin, the plena in fluid communication with the cooling flu

Abstract: A group of alloys suitable for use in a high-temperature, oxidative environment, a protective coating system comprising a diffusion barrier that comprises an alloy selected from the group, an article comprising the diffusion barrier layer, and a method for protecting an article from a high-temperature oxidative environment comprising disposing the diffusion barrier layer onto a substrate are presented.

Abstract: A method of introducing small amounts of a refractory element into a vapor deposition coating. A second material (30), containing at least two elements which are desired to be deposited as a coating on a base material, has placed over it a first material (20) substantially comprising such two elements and a refractory element. The first material (20) is adapted to permit transport of the at least two elements in the second material (30) through the first material (20) when the first (20) and second (30) material are in a molten state and in touching contact with the other so as to permit evaporation of the two elements and the refractory element from an exposed surface. Heat is supplied to the first (20) and second (30) materials to permit evaporation of the at least two elements of second material (30) and the refractory element in the first material (20), and the resulting vapors are condensed as a deposit on a base material (50).

Abstract: A method and apparatus for casting a near-net-shape article from a high temperature material, such as a refractory metal intermetallic composite material. The apparatus includes: a means for forming a molten material comprising at least one of a metal and an alloy; a means for pouring the molten material; a mold assembly comprising a solid shell having a face coat interposed between the solid shell and molten material; and a heater assembly for maintaining the solid shell at a temperature. The molten material solidifies within the solid shell to form a near-net shape of the article. The near-net shape article may be a turbine assembly component, such as, but not limited to, a vane or airfoil.

Abstract: A on-line method is provided for detecting wear and/or damage to gas turbine parts. Preferred embodiments of the invention provide a gas turbine comprising parts with smart coatings and collection and detection means to measure wear and erosion of gas turbine parts. In other preferred embodiments, smart coatings are provided comprising chemical taggants that can be collected and detected downstream, thus providing an on-line or in situ evaluation technology for wear and damage to gas turbine parts.

Abstract: An environmentally resistant coating (34) for improving the oxidation resistance of a niobium-based refractory metal intermetallic composite (Nb-based RMIC) at high temperatures, the environmentally resistant coating (34) comprising silicon, titanium, chromium, and niobium. The invention includes a turbine system (10) having turbine components (11) comprising at least one Nb-based RMIC, the environmentally resistant coating (34) disposed on a surface (33) of the Nb-based RMIC, and a thermal barrier coating (42) disposed on an outer surface (40) of the environmentally resistant coating (34). Methods of making a turbine component (11) having the environmentally resistant coating (34) and coating a Nb-based RMIC substrate (32) with the environmentally resistant coating (34) are also disclosed.

Abstract: A wall structure for a gas turbine engine component is provided which comprises a wall having a first side facing a flow of hot gases and a second side exposed to a source of cooling fluid. The wall has a plurality of holes formed therethrough, and an outer layer disposed on the first side. The holes greatly increase the wetted surface area of the wall exposed to cooling flow.

Abstract: A turbine airfoil is provided having an integral tip cap and a pair of tip walls which extend radially outward past the tip cap to form a squealer tip. A coaxial pair of first and second holes extend through the tip cap and one of the tip walls respectively at an acute inclination angle, with the first hole being disposed so as to direct impingement cooling air on the tip wall having the second hole. A protective layer comprising a high temperature foil is disposed on the tip wall having the second hole therein.

Abstract: A method and apparatus for casting a near-net-shape article from a high temperature material, such as a refractory metal intermetallic composite material. The apparatus includes: a means for forming a molten material comprising at least one of a metal and an alloy; a means for pouring the molten material; a mold assembly comprising a solid shell having a face coat interposed between the solid shell and molten material; and a heater assembly for maintaining the solid shell at a temperature. The molten material solidifies within the solid shell to form a near-net shape of the article. The near-net shape article may be a turbine assembly component, such as, but not limited to, a vane or airfoil.

Abstract: Articles for use in a high-temperature, oxidative environment, methods for manufacturing such articles, and a material system for protecting articles in such an environment are provided where, for example, one article comprises a substrate and a protective layer disposed over the substrate, the protective layer comprising at least about 60 atomic percent of a metal selected from the group consisting of platinum (Pt), palladium (Pd), rhodium (Rh), osmium (Os), iridium (Ir), and mixtures thereof.

Abstract: An alloy and a gas turbine engine component comprising an alloy are presented, with the alloy comprising from about three atomic percent to about nine atomic percent of at least one precipitation-strengthening metal selected from the group consisting of zirconium, niobium, tantalum, titanium, hafnium, and mixtures thereof; from about one atomic percent to about five atomic percent ruthenium; and the balance rhodium; the alloy further comprising a face-centered-cubic phase and an L12—structured phase.

Abstract: An article for use in a hot gas path of a gas turbine assembly, a metallic skin for such an article, and a method for making such an article are presented with, for example, the article comprising a spar, the spar providing mechanical support for the article and comprising a cooling fluid delivery system, a top end, and a bottom end; a standoff structure attached to the spar, the standoff structure comprising a plurality of spacing elements in a spaced-apart relation to each other, the spacing elements having first ends adjacent to the spar and second ends opposite to the first ends; a skin conformally surrounding the spar and the standoff structure, the skin comprising a top end and a bottom end, wherein the standoff structure separates the spar and the skin, wherein the plurality of spacing elements is disposed with an inner surface of the skin adjacent to the second ends of the spacing elements to form a plurality of plena between the spar and the skin, the plena in fluid communication with the cooling flu

Abstract: The present invention provides for a squealer tip to include some proportion of a highly oxidation-resistant material, and a method for casting same, such that if any environmental coating were removed, the tip would retain some increased level of environmental resistance. The oxidation-resistant material optionally may also be a high abrasion resistance material, such that recession of the tip due to rubbing against a stator would be reduced. In a preferred embodiment, an abrasion-resistant and/or oxidation-resistant material is placed and suitably anchored into the tip region of a wax precursor used to cast a turbine airfoil. During the casting operation, the abrasion-resistant and/or oxidation-resistant material is not completely melted. As the alloy used to form the majority of the turbine blade solidifies, the abrasion and/or oxidation resistant material is incorporated into the turbine airfoil by the solidification of the alloy around it.

Abstract: A system and method for repairing defects such as bumper holes, cracks, freckles and inclusions, in a cast article, such as a turbine component. The system comprises a device for locating a defect in a cast article, a repair material that is disposable at a defect site, at least one heat source capable of heating the repair material and a portion of the cast article to a molten state. The method of using the system comprises locating a defect in the cast article, providing a repair material to the defect site, melting the repair material and cast article at the defect site, and cooling the molten repair material and portion of the casting article such that they resolidify and fuse together. The method may further comprise removing a portion of the cast article at the defect site, removal of excess repair material and inspecting the cast article following repair of the defect.

Abstract: A gas turbine airfoil and methods for manufacturing and repair of an airfoil, the airfoil comprising a wall, the wall defining the perimeter of the airfoil and comprising a leading edge section and a trailing edge section, wherein a majority of the surface area of the wall comprises a first material, the first material having an oxidation resistance and a melting temperature, and at least one portion of the wall comprises a second material, the second material having an oxidation resistance that is greater than the oxidation resistance of the first material and a melting temperature that is at least about 83 degrees Celsius (about 150 degrees Fahrenheit) greater than the melting temperature of the first material, the at least one portion of the wall located in at least one section of the wall selected from the group consisting of the leading edge section and the trailing edge section.