FIELD: engines and pumps.
SUBSTANCE: anti-ice system 2 on aircraft gas turbine engine inlet cone 4 comprises air diffuser 18 arranged in engine inlet cone to feed hot air therein. Said system comprises also circuit 20 to remove supercharged air from constricted cavity of turbine engine. Said circuit communicates with diffuser to supply hot air therein. Aircraft turbine engine incorporates above described anti-ice system. Proposed method of de-icing features the use of above described system.
EFFECT: perfected operating performances.
13 cl, 3 dwg
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