Turbine rotor blade tip coated with alumina-zirconia ceramic
AssigneeThe Perkin-Elmer Corporation
InventorsBurton A. Kushner, Anthony J. Rotolico, John E. Nerz, Lawerence A. Saia
Life of this patent
Estimating the term…
Abstract
A rotor blade is for a gas turbine engine having a plurality of rotor blades and a substantially coaxial shroud encompassing the tips of the blades. A ceramic layer is bonded to the blade tip, the ceramic layer consisting of a combination of aluminum oxide and zirconium oxide or at least partially stabilized zirconium oxide. The ceramic layer is formed as a plasma sprayed coating or a high velocity oxy-fuel sprayed coating.
Claims29
A rotor blade for a gas turbine engine having a plurality of rotor blades and a substantially coaxial shroud encompassing the tips of the blades, comprising a blade member with an inner end adapted for mounting on a rotation hub and with a blade tip located opposite the inner end, and a ceramic layer bonded to the blade tip, the ceramic layer consisting essentially of aluminum oxide and a zirconia-based oxide selected from the group consisting of zirconium oxide and at least partially stabilized zirconium oxide.
A method of manufacturing a rotor blade for a gas turbine engine having a plurality of rotor blades and a substantially coaxial shroud encompassing the tips of the blades, the rotor blade having an inner end adapted for mounting on a rotation hub and a blade tip located opposite the inner end, the method comprising thermal spraying a ceramic layer consisting essentially of aluminum oxide and zirconia-based oxide onto the blade tip, the zirconia-based oxide being selected from the group consisting of zirconium oxide and at least partially stabilized zirconium oxide.
Dependencies are inferred from the claim text.