Aircraft gas turbine having a booster bleed duct in a stator vane root element of a bypass duct
作者： Knut Rosenau , Lars Pettersson , Lutz Bilger , Andrew Cox
DOI:
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摘要: The present invention relates to an aircraft gas turbine having a core engine and bypass duct surrounding the latter, where includes in its inflow zone booster, area of which at least on booster bleed is provided for supplying airflow from into duct, stator vane row arranged n downstream fan, characterized that root designed as structural element mounting engine, inside issues duct.
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