AIRCRAFT GAS TURBINE HAVING A VARIABLE OUTLET NOZZLE OF A BYPASS FLOW CHANNEL
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United States of America Patent
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Sep 20, 2018
app pub date -
Dec 1, 2016
filing date -
Dec 1, 2016
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Abstract
An aircraft gas turbine having a core engine and having a bypass flow channel which surrounds said engine and which forms, with a casing of the core engine and a radially outer housing wall, an outlet nozzle, characterized in that, in the region of the outlet nozzle, there is arranged a ring-shaped element which is able to be displaced in the axial direction, wherein a ring-shaped channel which is able to be varied by way of the displacement of the ring-shaped element is formed between the casing of the core engine and the ring-shaped element.
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