THRUST VECTORING EXHAUST NOZZLE FOR AIRCRAFT PROPULSION SYSTEM
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United States of America Patent
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Issued Date -
Nov 30, 2023
app pub date -
May 26, 2023
filing date -
May 26, 2022
priority date (Note) -
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Abstract
An assembly is provided for an aircraft propulsion system. This assembly includes a bladed rotor and a thrust vectoring exhaust nozzle. The bladed rotor is rotatable about an axis. The thrust vectoring exhaust nozzle is configured to direct gas propelled by the bladed rotor out of the aircraft propulsion system along a first direction during a first mode and along a second direction during a second mode. The first direction is parallel with the axis or angularly offset from the axis by no more than five degrees. The second direction is angularly offset from the axis by at least seventy-five degrees. The thrust vectoring exhaust nozzle has a first exit area during the first mode and a second exit area during the second mode that is greater than the first exit area.
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