Variable area nozzle assisted noise control of a gas turbine engine
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United States of America Patent
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Nov 20, 2012
Grant Date -
Dec 3, 2009
app pub date -
Oct 12, 2006
filing date -
Oct 12, 2006
priority date (Note) -
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Abstract
An example turbofan engine sound control system includes a core nacelle (12) housing a compressor and a turbine. The core nacelle is disposed within a fan nacelle (34). The fan nacelle includes a turbofan. A bypass flow path downstream from the turbofan is arranged between the two nacelles. A controller (50) is programmed to manipulate the nozzle exit area to control sound propagating from the engine. In one example, the controller manipulates the nozzle exit area using hinged flaps (42) to control engine sound. The hinged flaps open and close to adjust the nozzle exit area and the associated bypass flow rate.
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