| US 7,510,370 B2 | ||
| Turbine blade tip and shroud clearance control coating system | ||
| Thomas E. Strangman, Prescott, Ariz. (US); Derek Raybould, Denville, N.J. (US); Paul Chipko, Blairstown, N.J. (US); and Malak F. Malak, Tempe, Ariz. (US) | ||
| Assigned to Honeywell International Inc., Morristown, N.J. (US) | ||
| Filed on Sep. 14, 2005, as Appl. No. 11/227,780. | ||
| Claims priority of provisional application 60/648781, filed on Feb. 01, 2005. | ||
| Prior Publication US 2008/0166225 A1, Jul. 10, 2008 | ||
| Int. Cl. F01D 5/20 (2006.01) | ||
| U.S. Cl. 415—173.4 [415/174.4] | 20 Claims |
| 1. A turbine blade tip and shroud clearance control coating system comprising:
a turbine blade, the turbine blade comprising a blade tip;
an abrasive grit coating disposed on the blade tip, the abrasive grit coating comprising an oxidation resistant bond coating
and grit particles embedded into the oxidation resistant bond coating and grit particles embedded into the oxidation resistant
bond coating, wherein the grit particles comprise abrasive crystalline particles of cubic zirconia, cubic hafnia or mixtures
thereof;
a turbine shroud, the shroud comprising an inner surface, wherein the inner surface is in a rub relationship with the blade
tip; and
a nanolaminate thermal barrier coating on the inner surface of the turbine shroud, the nanolaminate thermal barrier coating
comprising alternating layers of a first material with a second material, the first material comprising stabilized zirconia,
hafnia or mixtures thereof, and the second material comprising at least one metal oxide, wherein the nanolaminate thermal
barrier coating comprises from about 5 wt % to about 70 wt % of the metal oxide and from about 30 wt % to about 95 wt % of
stabilized zirconia, hafnia or mixtures thereof.
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