AIRCRAFT DUAL-FLOW TURBINE ENGINE ASSEMBLY, THE ASSEMBLY BEING EQUIPPED WITH INCIDENCE-CONTROLLED AIR DISCHARGE FINS
An aircraft dual-flow turbine engine assembly includes: an internal shroud for externally delimiting a primary flow path of the turbine engine gases; an external shroud for internally delimiting a secondary flow path of the turbine engine gas; and at least one air discharge duct extending between th...
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Main Authors | , |
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Format | Patent |
Language | English |
Published |
21.12.2023
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Subjects | |
Online Access | Get full text |
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Summary: | An aircraft dual-flow turbine engine assembly includes: an internal shroud for externally delimiting a primary flow path of the turbine engine gases; an external shroud for internally delimiting a secondary flow path of the turbine engine gas; and at least one air discharge duct extending between the internal shroud and the external shroud, the air discharge duct opening into the secondary flow path through an outlet orifice equipped with discharge fins. At least some of the discharge fins are movably mounted so as to be able to be incidence-control between a propulsion position, and a reverse thrust position. |
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Bibliography: | Application Number: US202118251290 |