DEVELOPMENT OF THE TECHNOLOGY FOR REPAIR MICROPLASMA POWDER CLADDING OF FLANGE PLATFORM FACES OF AIRCRAFT ENGINE HIGH-PRESSURE TURBINE BLADES

摘要

Described is the technology developed by the E.O. Paton Electric Welding Institute for repair microplasma powder cladding of flange platform faces of high-pressure turbine blades made from alloy JS32-VI for engine D18T by using an additive powder with a composition similar to that of the base metal. It was shown that the one-layer deposited metal preserves the preferred inheritance of structure of the base metal. It was established that specimens simulating the repair cladding conditions, when tested to long-time strength at a temperature of 1000℃, exhibited a strength level of about 50% of that of the base metal along the fusion line.