A turboprop engine (1) includes an engine nacelle (3) and at least one bleed air line (25) on the low-pressure compressor (4) and at least one ejector (21) formed by a cooling air duct (24) and a nozzle (22) to create a cooling air flow within the engine nacelle during critical ground idle operation (controlled or uncontrolled), and without undesirably increasing fuel consumption or disturbing the work cycle of the engine (1). The ejector (21) is arranged within the engine nacelle (3) in the forward part of the turboprop engine (1), with the cooling air duct (24) appertaining to the ejector (21) connecting at least one air intake (23) disposed on the periphery of the engine nacelle (3) with the interior of the engine nacelle (3), and with the at least one nozzle (22) being arranged in the cooling air duct (24).
This information is part of a study by Oasis Global, Inc. of all space inventions filed at the United States Patent and Trademark Office, and is provided for informational purposes only. It is not an endorsement of any particular assignee, inventor or invention. Although Peter A. Koziol represents inventors and assignees of space inventions he does not represent all of the inventors and assignees listed. The prosecuting attorney agent or firm for each patent is identified by the United States Patent and Trademark Office in the patent specfication, which can be viewed by clicking on the patent image or downloading the patent document. For more information regarding Mr. Koziol's background and experience, or to learn more about space inventions, please contact Mr. Koziol.
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