Patent ID: 6190124
Filing Date: 2001-02-20
Classification: C23C,F01D,F05D

Abstract:
A gas turbine engine seal system, comprising a rotating member having an abrasive tip disposed in rub relationship to a stationary, abradable seal surface, wherein the abrasive tip comprises a material harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface, characterized in that:the abrasive tip comprises a metallic bond coat deposited onto a substantially grit-free surface on the rotating member, an aluminum oxide layer disposed on the metallic bond coat, and a zirconium oxide abrasive coat having a columnar structure is deposited on the aluminum oxide layer, wherein the zirconium oxide abrasive coat comprises zirconium oxide and about 3 wt % to about 25 wt % of a stabilizer selected from the group consisting of yttrium oxide, magnesium oxide, calcium oxide and a mixture thereof.