System and method for cooling an aircraft wing
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United States of America Patent
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Sep 27, 2016
Grant Date -
Nov 20, 2014
app pub date -
Nov 29, 2011
filing date -
Nov 29, 2011
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Abstract
An aircraft comprises a turbine engine suspended from a wing by means of a pylon. Compressed hot air is bled off from the turbine engine. A bleed air duct in the wing conveys the compressed hot air towards a fuselage. In order to prevent overheating of aircraft parts that are relatively close to the bleed air duct, the following solution is proposed. The pylon comprises an opening with a covering structure projecting into a bypass exhaust flow from the turbine engine. The covering structure leaves a slit facing away from the bypass exhaust flow. An airflow path extends from openings in the wing to the slit left by the covering structure.
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