Aircraft power system
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United States of America Patent
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Mar 13, 2018
Issued Date -
N/A
app pub date -
Dec 26, 2013
filing date -
Mar 4, 2013
priority date (Note) -
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Abstract
A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.
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