Abstract: Provided is a method for heat treating a precipitation-hardened article having a thick section and a thin section so that the thin section can be solution annealed while the metallurgical structure of the thick section is substantially unaffected by the solution-annealing process. The method restores the microstructure of the thin section uniformly by solution annealing the thin section to achieve a preselected microstructure but without affecting the microstructure of the thick section.

Abstract: Provided is a method for heat treating a precipitation-hardened article having a thick section and a thin section so that the thin section can be solution annealed while the metallurgical structure of the thick section is substantially unaffected by the solution-annealing process. The method restores the microstructure of the thin section uniformly by solution annealing the thin section to achieve a preselected microstructure but without affecting the microstructure of the thick section.

Abstract: A fixture and method for repairing superalloy articles. The fixture ideally holds the article in place if repairs are made. An interface between the fixture and the article facilitate transfer of heat between the article and the fixture so that the article can be differentially heat treated. A portion of the article extends from the fixture. This portion of the article, which may be repaired within the fixture or may be repaired elsewhere, is solution heat treated while in the fixture so that the area extending from the fixture is solutioned, while heat is transferred from the article through the fixture, thereby preventing the temperature of the portion of the article within the fixture from being elevated so as to modify its microstructure. The solutioned portion can then be heat treated, while in the fixture, to precipitation harden it as desired.

Abstract: A method of depositing a ceramic thermal barrier coating on an article that will be subjected to a hostile environment, such as turbine, combustor and augmentor components of a gas turbine engine. The thermal barrier coating is deposited by electron beam physical vapor deposition (EBPVD) using process parameters that include an absolute pressure of greater than 0.010 mbar and an oxygen partial pressure of greater than 50%, preferably at or close to 100%. Under these conditions, the desired ceramic material is evaporated with an electron beam to produce a vapor that deposits on the component to form a thermal barrier coating of the ceramic material.