THRUST NOZZLE FOR A TURBOFAN ENGINE ON A SUPERSONIC AIRCRAFT
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United States of America Patent
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Issued Date -
Oct 22, 2020
app pub date -
Dec 11, 2018
filing date -
Dec 19, 2017
priority date (Note) -
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Abstract
The invention relates to a thrust nozzle for a turbofan engine of a supersonic aircraft, wherein the thrust nozzle includes a thrust nozzle wall, and a flow channel that is delimited radially outwards by the thrust nozzle wall, wherein the flow channel has a nozzle throat surface and a central body that is arranged in a flow channel. According to the invention, the central body forms a bypass channel, which extends within the central body, and which is designed for the gas of the flow channels to flow through. The bypass channel has at least one upstream inlet opening, which is arranged upstream of the nozzle throat surface of the flow channel, and at least one downstream outlet opening, which is arranged downstream of the nozzle throat surface of the flow channel
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