Abstract: Combustion turbine air intake filter assemblies, their components, and methods of use are disclosed. In certain embodiments, the assemblies may be useful, inter alia, for extending high efficiency filter life, reducing turbine downtime for filter assembly changeouts, or adjusting filter assemblies to address changing local conditions after the assemblies have been put into service.

Abstract: A substrate exposed to high temperatures, the substrate having a TBC layer that includes fibers of reinforcing material to add strength to the layer of TBC. The fibers are made from carbon nanotubes to withstand the high temperatures, and have a diameter of about 0.1 mm or less in order that a thin layer of TBC can completely cover and embed the fibers within the layer. A bond coat is applied to the substrate and the fibers are attached to the bond coat to limit the fibers from being pulled away from the substrate. The carbon nanotubes also provide for improved heat transfer through the TBC to improve the cooling capability of the TBC.

Abstract: Combustion turbine air intake filter assemblies, their components, and methods of use are disclosed. In certain embodiments, the assemblies may be useful, inter alia, for extending high efficiency filter life, reducing turbine downtime for filter assembly changeouts, or adjusting filter assemblies to address changing local conditions after the assemblies have been put into service.

Abstract: An airfoil used in a gas turbine engine exposed to high temperatures, the airfoil having a TBC layer that includes fibers of reinforcing material to add strength to the layer of TBC. The fibers are made from a similar material in which the airfoil is made from to withstand the high temperatures, and have a diameter of about 0.1 mm in order that a thin layer of TBC can completely cover and embed the fibers within the layer.

Abstract: An airfoil for a gas turbine engine, the airfoil includes a plurality of cooling air passages to supply cooling air to an external surface of the airfoil, the cooled surface of the airfoil having a critical temperature in which any cooled surface of the airfoil should not exceed, the cooling air passages having a coating applied within the passages, the coating being made of a material that has an oxidizing property such that the material oxidizes away and opens the passage to more flow when exposed to a temperature above the critical temperature. When the airfoil surface is not properly cooled by a flow passing through the passage, the material oxidizes away until the size of the passage increases to allow for the proper amount of cooling air to flow to cool the airfoil. Each passage is located in a different part of the airfoil that requires more or less cooling flow, and each passage will oxidize until the size of the passage is large enough to allow for the proper amount of cooling flow.