Aircraft gas turbine with variable bypass nozzle by deforming element
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United States of America Patent
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Oct 7, 2014
Grant Date -
Jan 10, 2013
app pub date -
Jul 3, 2012
filing date -
Jul 8, 2011
priority date (Note) -
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Abstract
The present invention relates to an aircraft gas turbine with a core engine which is surrounded by a bypass duct enclosed radially outwards by a bypass wall, with a radially inner wall of the bypass duct forming with the radially outer bypass wall a bypass nozzle, and with the radially inner wall including an adjusting element extending along the circumference of the inner wall and being deformable radially outwards.
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