Bleed duct assembly for a gas turbine engine
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United States of America Patent
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Mar 13, 2018
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N/A
app pub date -
Aug 8, 2014
filing date -
Aug 21, 2013
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Abstract
A bypass duct has a support unit comprising a pair of aerofoils arranged as an “A” frame. A bleed duct assembly is provided on the radially inner wall of the bypass duct annulus and the aerofoils project from the surface and extend across the annulus between the inner wall and an outer wall of the annulus. The aerofoils lean at an acute angle to the surface with the first flank facing toward the inner wall and adjoining a bleed duct opening. The bleed duct having a bleed duct passage and a submerged scoop.
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