Patent ID: 8480032

Claim:
An engine nacelle of an aircraft gas turbine having a de-icing device, comprising: an annular air duct, positioned in an inlet lip of an inflow area of the engine nacelle and extending circumferentially around the inlet lip, into which heated air is introduced; at least one oil cooler positioned in the engine nacelle rearward of the annular air duct, to which engine oil is fed and which is supplied with ambient air to be heated by the oil cooler; an inflow duct flowingly positioned between the oil cooler and the annular air duct for routing the heated air flow leaving the oil cooler to the annular air duct, to be routed circumferentially around the inlet lip through the annular air duct; an air efflux duct positioned rearward and downstream of the annular air duct for exhausting the heated air flow that has passed through the annular air duct and warmed the inlet lip; the annular air duct being closed between the inflow duct and the air efflux duct.