Gas turbine engine thermal management system for heat exchanger using bypass flow
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United States of America Patent
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app pub date -
Mar 12, 2013
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Sep 28, 2012
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Abstract
A gas turbine engine has a fan nacelle and a core nacelle arranged to provide a bypass flow path. A compressor section is provided within the core nacelle. A heat exchanger is arranged within a duct. The heat exchanger is configured to receive bypass flow from the bypass flow path. The duct is in fluid communication with the compressor section and is configured to pass bleed air through the heat exchanger.
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