Patent ID: 8591196
Filing Date: 2013-11-26
Classification: C23C,F01D,F05C,F05D,Y10T

Abstract:
1. A gas turbine or turbine component partially or fully coated with a damping surface layer, wherein the damping surface layer has a thickness between 0.1 and 2000 microns and is capable of dissipating vibration or modifying a resonance frequency of the gas turbine or turbine component at ambient room temperatures including operational temperatures greater than 500° F., and wherein the damping surface layer comprises at least one of (a) at least two layers comprising a first layer of at least one hard material and a second layer comprising at least one soft material, (b) a composite comprising a nickel alloy with a heat softenable chemistry, (c) a fine-grained nickel-based superalloy, or (d) a porous metallic coating, a porous metallic and ceramic coating, or a ceramic coating wherein the damping surface layer comprises a composite with a softenable phase, wherein the composite comprises an oxidation resistant metallic material, and wherein the softenable phase comprises a silica-based glass.