Aircraft gas turbine engine
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorDimitrie NEGULESCU
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Abstract
The invention refers to an aircraft gas turbine engine including a core engine 1 comprising at least a high pressure turbine 6 and a downstream low pressure turbine 7, a bypass duct 18 surrounding the core engine 1, as well as a mixer 19 arranged in an inlet portion of the low pressure turbine 7, into which a bypass flow 20 from the bypass duct 18 and a core flow 22 from the core engine 1 are supplied.
Claims8
An aircraft gas turbine engine including a core engine comprising at least a high pressure turbine (6) and a downstream low pressure turbine, a bypass duct surrounding the core engine, as well as a mixer arranged in an inlet portion of the low pressure turbine, into which a bypass flow from the bypass duct and a core flow from the core engine are supplied.
Dependencies are inferred from the claim text.