Patent ID: 6089825
Filing Date: 2000-07-18
Classification: C23C,F01D,Y02T,Y10S,Y10T

Abstract:
An air seal for use in a gas turbine engine having reduced susceptibility to deflagration during operating conditions in which an excessive amount of seal material is liberated from the seal, comprising:a seal substrate;a thermally sprayed metallic bond layer applied to at least a portion of the seal substrate, the bond layer composed of thermally sprayed nickel powder and aluminum powder; andan abradable seal layer applied to the bond layer, the abradable layer consists essentially of thermally sprayed aluminum powder and silicon powder forming a metal matrix, and co-deposited methyl methacrylate filler particles embedded in the metal matrix, wherein the filler particles are composed of a material with reduced ignitability relative to polyester particles.