FIELD: mechanical engineering; gas-turbine building.
SUBSTANCE: invention relates to designs of working blades of axial-flow compressors, particularly, of gas-turbine engines. Proposed composition blade of turbomachine has feather made up of alternating and orientated layers of composite material connected by binder, and metal cover plate with cross cuts found on leading edge of blade feather. Metal cover plate with cross cuts is located both on leading edge of blade feather and trailing edge of blade feather. Inlet and outlet metal cover plates are provided with stepped developed ends fitted into inner layers of composite material of blade feather. Holes with diameter exceeding width of cross cuts are made on said ends of metal cover plates at each cross cut.
EFFECT: provision of blade of axial-flow compressor with required stiffness and strength for operation under standard conditions, adapted to non-designed external loads, for instance, impact.
3 dwg
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