FIELD: aviation.
SUBSTANCE: air intake of a helicopter gas turbine engine comprises a compressor and a duct for air supply to the compressor, edges (30, 32) and an anti-icing grid (36). The anti-icing grid is mounted on the outer ends (30a, 32a) of the edges (30, 32) of the air intake and is located in the path of the airflow entering the air intake (34). At least one edge (30, 32) of the air intake is made of a thin metal sheet.
EFFECT: significant amount of bypass flow during icing.
10 cl, 6 dwg
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|---|---|---|---|
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