| US 7,473,072 B2 | ||
| Turbine blade tip and shroud clearance control coating system | ||
| Malak F. Malak, Tempe, Ariz. (US); Derek Raybould, Denville, N.J. (US); and Thomas E. Strangman, Prescott, Ariz. (US) | ||
| Assigned to Honeywell International Inc., Morristown, N.J. (US) | ||
| Filed on Aug. 31, 2005, as Appl. No. 11/218,074. | ||
| Claims priority of provisional application 60/648725, filed on Feb. 01, 2005. | ||
| Prior Publication US 2006/0171813 A1, Aug. 03, 2006 | ||
| Int. Cl. F01D 5/20 (2006.01) | ||
| U.S. Cl. 415—173.4 [415/174.4] | 21 Claims |
| 1. A turbine blade tip and shroud clearance control coating system comprising:
a turbine blade, the turbine blade comprising a blade tip;
a dense abrasive coating disposed on the blade tip, the dense abrasive coating comprising 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 nanolayers 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 a thickness of the nanolayers
is varied.
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