Bypass turbomachine with artificial variation of its throat section
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United States of America Patent
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May 31, 2011
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N/A
app pub date -
Jul 19, 2007
filing date -
Aug 1, 2006
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Abstract
The invention relates to a bypass turbomachine comprising a gas turbine engine provided with a fan disposed on a longitudinal axis of the turbomachine, and an annular nacelle surrounding the engine so as to define a cold stream flow channel, the nacelle having an upstream end surrounding the fan of the engine and a stationary downstream end forming a gas exhaust nozzle, the nozzle having a throat section that corresponds to its smallest cross-section. The turbomachine further comprises means for taking in air from the cold stream flow channel upstream from the nozzle throat section, and means for injecting the taken-in air downstream from the nozzle throat section so as to open the throat section artificially.
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