The working blade of the first stage in a marine gas turbine engine made from the chromium-nickel alloy EI826 was studied. Tests were run under service conditions in the actual engine, and also in a gasdynamic test bed which applied cyclic thermal loading to the blade in a gas flow of variable parameters simulating the most dangerous transient working conditions of the engine. The residual service life was determined by the complete fracture method, using a VL-1 electrodynamic vibratory test machine. The procedure for the test is described.