An approximation method for estimation of the residual stress relaxation in a face-hardened blade in a mass-force field under creepстатьяПеревод
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Дата последнего поиска статьи во внешних источниках: 19 октября 2015 г.
Аннотация:An approximation method for the evaluation of the residual stress relaxation in face-hardened blades of gas turbine engines under creep is reported. A hypothesis that allows for the blade to be decomposed into the blade “body” and a thin hardened surface layer underlies this method, which enables one to divide the problem under consideration into a series of boundary value problems that are solved in sequence. A model analysis of the residual stress relaxation in the face-hardened layers of a number of blades is made, in particular, for the first stage of the high-pressure turbine of the GTK-10-4.