FIELD: mechanical engineering; gas turbine engines and plants.
SUBSTANCE: proposed turbine blade consists of root and feather whose leading and trailing edges are provided with air inlet and outlet holes. Coating of heat insulating material is found on surface of leading edge, on part of convex surface adjoining leading edge, on parts of concave surface adjoining leading edge and root and on tail part of blade feather. Coating is made variable in thickness over profile and height of blade. Coating can be additionally made on remaining part of concave surface of blade feather up to trailing edge. Thickness of coating in each point on blade surface is found from formula protected by invention.
EFFECT: increased service life of blade owing to reduction of heat stresses and stresses caused by centrifugal forces owing to use of variable thickness coating.
6 cl, 3 dwg
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|---|---|---|---|
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|
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