Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
AssigneeUnited Technologies Corporation
InventorsMelvin Freling, Dinesh K. Gupta, Ken Lagueux, Jeanine T. DeMasi-Marcin
Life of this patent
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Abstract
A gas turbine engine seal system includes a rotating member having an abrasive tip disposed in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface.
Claims20
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.
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 zirconium oxide abrasive coat having a columnar structure, 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 mixtures thereof and the abrasive tip is deposited onto a substantially grit-free surface on the rotating member.
A gas turbine engine blade comprising an abrasive tip, wherein the abrasive tip comprises a zirconium oxide abrasive coat having a columnar structure, 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.
A gas turbine engine knife edge comprising an abrasive tip, wherein the abrasive tip comprises a zirconium oxide abrasive coat having a columnar structure, wherein the zirconium oxide abrasive coat comprises zirconium oxide and about 6 wt % to about 20 wt % of a stabilizer selected from the group consisting of yttrium oxide, magnesium oxide, calcium oxide and a mixture thereof.
Dependencies are inferred from the claim text.