Scoop of a running-gap control system of an aircraft gas turbine
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United States of America Patent
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Apr 2, 2013
Grant Date -
Sep 9, 2010
app pub date -
Mar 3, 2010
filing date -
Mar 4, 2009
priority date (Note) -
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Abstract
A scoop for a fairing 1 of a core engine 2 of an aircraft gas turbine allows air to be supplied from a bypass flow in a bypass duct 3 to several cooling-air distributors in a core-engine ventilation compartment 4. The scoop includes a first tubular flow duct 5, whose inlet opening 6 is arranged in the bypass duct 3 and which extends through the fairing 1, as well as a second tubular flow duct 7, which at least partly encompasses the first flow duct 5 and whose inlet opening 8 is rearwardly offset relative to the inlet opening 6 of the first flow duct 5 in the direction of flow.
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