FIELD: shell-type blades for gas-turbine engines.
SUBSTANCE: turbine blade primarily used in gas-turbine engines has shell that forms feather profile and is joined to locking part. Shell material is composed of two or more layers. Materials of adjacent layers are chosen so that coefficient of linear expansion of layer material having higher temperature is lower than that of layer material having lower temperature. Thermal and mechanical properties of layer materials of shell meet expression claimed by invention. In using existing methods for blade design measures are taken to prevent thermal stresses.
EFFECT: enhanced blade heat cycle period and in-service geometric stability of shape; facilitated manufacture of blade at reliable fixation of shell.
3 cl, 6 dwg
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