Aircraft engine airflow modulation apparatus and method for engine bay cooling and cycle flow matching
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United States of America Patent
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May 31, 2016
Grant Date -
Jun 16, 2011
app pub date -
Dec 11, 2009
filing date -
Dec 11, 2009
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Abstract
The present invention relates to a system and method of LO airflow modulation for use with a DTSA engine. A DTSA engine is positioned within an aircraft fuselage and the second DTSA turbine fan includes it own dedicated decoupled air inlet duct that is formed co-centrically about the housing. An airflow modulator member is positioned in duct to form the duct wall when the modulator is in a closed position. The Modulator member is pivotally connected to the duct wall, and is movable by an actuator to a second open position that allows airflow to escape the third stream duct, and provide airflow to both the DTSA fan blades as well as engine bay for cooling. The method of the present invention provides airflow modulation to an aircraft employing a DTSA engine, said method including the receiving of airflow from a supersonic aircraft intake; sensing a number of parameters, including, but not limited to aircraft speed, temperature, engine load and/or altitude. Calculating an efficient amount of airflow to provide to the DTSA turbine blades thorough a decoupled airstream; and directing movement of a modulator vane located in the intake duct to vary airflow to the DTSA turbine.
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