| 摘要 |
<p>An engine case (20) of a gas turbine engine (10) is selectively coated with a thermal barrier coating (60) to control axial clearance between rotating (22) and stationary (24) airfoils. The coating (60) is applied to the thinner portions of the engine case (20) to retard thermal expansion of these portions of the engine case during transient conditions of the gas turbine engine operation. The selectively coated engine case responds substantially uniformly to heating and thermal expansion during transient conditions, thereby reducing axial vane (24) lean in gas turbine engines.</p> |
