Patent ID: 8276392

Claim:
A turboprop engine with an apparatus for the generation of a cooling airflow, comprising: an engine nacelle; at least one bleed air line from a low-pressure compressor; at least one cooling air duct connecting at least one air intake disposed on the periphery of the engine nacelle with an interior of the engine nacelle; at least one nozzle being positioned in the cooling air duct to form, with the cooling air duct, an ejector that creates a cooling air flow through the cooling air duct, the ejector positioned within the engine nacelle in a forward part of the turboprop engine; wherein the nozzle of the ejector is connected to the bleed air line on the low-pressure compressor; wherein the bleed air line is connected to the nozzle of the ejector to supply an entire bleed air flow through the bleed air line to the nozzle.