Aircraft gas turbine engine

Details Aircraft gas turbine engine Aircraft gas turbine engine

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 3/13 (2006.01) F02C 9/18 (2006.01) F02K 3/02 (2006.01)

Patent

CA 2732464

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.

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