Aircraft gas turbine having a booster bleed duct in a stator vane root element of a bypass duct
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United States of America Patent
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Mar 6, 2018
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N/A
app pub date -
Apr 9, 2013
filing date -
Apr 10, 2012
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Abstract
An aircraft gas turbine has a core engine and a bypass duct surrounding the latter, where the core engine includes in its inflow zone a booster, in the area of which at least one booster bleed duct is provided for supplying an airflow from the booster into the bypass duct, and a stator vane row arranged in the bypass duct downstream of a fan. A vane root of the stator vane is designed as a structural element mounting the core engine, and the booster bleed duct is provided inside the vane root and issues downstream of the stator vane into the bypass duct.
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