US Patent 12065977 Multi-duct exhaust system for gas turbine engine
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US Patent 12065977 Multi-duct exhaust system for gas turbine engine
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Patent abstract
A system is provided for an aircraft. This aircraft system includes an exhaust duct, an exhaust flow regulator, a nozzle bypass duct and a bypass flow regulator. The exhaust duct extends longitudinally to an exhaust nozzle. The exhaust flow regulator is configured to regulate fluid flow through the exhaust duct to the exhaust nozzle. The nozzle bypass duct projects out from a side of the exhaust duct. The bypass flow regulator is configured to regulate fluid flow from the exhaust duct into the nozzle bypass duct. The bypass flow regulator is disposed upstream of the exhaust flow regulator.
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Patent Applicant
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Patent Number
Patent Inventor Names
Steven W. Burd0
Date of Patent
August 20, 2024
0Patent Application Number
180918480
Date Filed
December 30, 2022
0Patent Citations
Patent Primary Examiner
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