A sprayable thermal barrier coating powder mixture for a gas turbine engine includes: a dry composition having a low surface area ceramic powder having a median particle size distribution greater than 5 microns and less than 50 microns, and a high surface area ceramic powder having a median particle size distribution smaller than 5 microns, wherein the low surface area ceramic powder makes up at least 50% by weight of the dry composition of the sprayable thermal barrier coating powder mixture.

An electrical connecting structure (10) for use as a means for transmitting electrical energy between a first electrical component and a second electrical component, wherein the connecting structure (10) is formed from a number of layers (20, 30, 40, 50) arranged serially with one another, a first outer layer (20) consisting of aluminum or an aluminum alloy and a second outer layer (50) preferably consisting of aluminum or an aluminum alloy, and a third and preferably fourth layer (30, 40), specifically one or two inner layers, being provided between the outer layers (20, 50), the inner layer or inner layers (30, 40) being respectively produced by cold gas spraying.

A coated steel substrate has a steel substrate having a surface. A coating layer is atop the surface. The coating layer includes: aluminum activated by indium; and a ceramic binder. The coating also may comprise of multiple layers with different properties to facilitate the galvanic protection capability.

A powder for coating or sintering exhibits a peak assigned to orthorhombic YAlO.sub.3 in an X-ray diffractometry. Of peaks exhibited in the X-ray diffractometry, the peak assigned to the (112) plane of orthorhombic YAlO.sub.3 is a peak that has the highest peak intensity. Preferably, the value of the ratio of S2 to S1, S2/S1, is less than 1 in an X-ray diffractometry using CuKα radiation, where SI represents the peak intensity of the peak assigned to the (112) plane of orthorhombic YAlO.sub.3 and S2 represents the peak intensity of the peak assigned to the (104) plane of trigonal Al.sub.2O.sub.3.

A method for repairing a secondary battery according to an embodiment of the present invention for solving the above problems includes: a step, in which cracks are formed in an outer surface of a battery case of the pouch-type secondary battery; a step of locally applying a metal solution to the cracks; and a step of drying the metal solution to form a coating part.

The invention relates to a coating system for a component of a turbomachine, which includes at least two different base powders. Each of the at least two different base powders has an individual predetermined distribution within the coating system. Further, each of the at least two different base powders is responsible for a specific property of the coating system.

Methods for repairing the conventional physical barrier coating barrier on a component having a damaged portion. Applying a coating on the outer surface of the damaged portion of the component. The coating containing a reactive oxide. Initiating a reaction between the coating and the molten sulfates within the outer surface of the component. The reaction catalytically decomposes molten sulfates at the outer surface of the damaged portion of the component.

A sliding member of the present invention includes a coating on a base material. The coating contains hard metal particles and corrosion-resistant metal particles that have hardness lower than that of the hard metal particles. The hard metal particles contain particles that have at least Vickers hardness of 600 Hv or higher. The corrosion-resistant metal particles are made of at least one kind of metal selected from the group consisting of copper (Cu), cobalt (Co), chromium (Cr), and nickel (Ni), or are made of an alloy containing said metal. The coating has a cross section in which the hard metal particles are dispersed in an island manner in a particle aggregate of the corrosion-resistant metal particles and in which an area ratio of the corrosion-resistant metal particles is 30% or larger. Thus, corrosion of the hard metal particles in the coating is prevented, whereby the sliding member maintains wear resistance for a long time.

A method for inspecting and repairing a surface of a component of a gas turbine engine, the method including: inserting an inspection and repair tool into an interior of the gas turbine engine; inspecting the surface of the component with the inspection and repair tool; performing a repair of the surface of the component with the inspection and repair tool from within the interior of the gas turbine engine, the inspection and repair tool remaining within the interior of the gas turbine engine between inspecting the component and performing the repair of the surface of the component.

A polycrystalline diamond is formed on a substrate to form a polycrystalline diamond compact (PDC) cutter for a tool. The polycrystalline diamond has a cross-sectional dimension of at least 4 millimeters. The substrate includes tungsten carbide. An outer surface of the PDC cutter is at least partially surrounded with at least a single layer of coating by atomic layer deposition. The single layer of coating is configured to protect the PDC cutter from thermal degradation in response to exposure to a temperature greater than 700 degrees Celsius (° C.) and less than about 1050° C.