FIELD: engines and pumps.
SUBSTANCE: invention relates to gas turbine engines and, in particular, turbine blades pin seal. Gas turbine engine disk assembly includes turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot, extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. Pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. Pin seal includes a cylindrical shape and is located within a seal slot, formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades.
EFFECT: invention is aimed at increasing turbine cost effectiveness.
10 cl, 7 dwg
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