High area-ratio inter-turbine duct with inlet blowing

Details High area-ratio inter-turbine duct with inlet blowing High area-ratio inter-turbine duct with inlet blowing

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 17/14 (2006.01) F01D 25/24 (2006.01) F02C 9/18 (2006.01)

Patent

CA 2509744

A bypass channel (80) for use in an inter-turbine transition duct (10) of a gas turbine engine is connected to a suction port (70) disposed upstream of a high- pressure turbine (20) and an injection port (90) disposed downstream of the high- pressure turbine (20). The flow through the bypass channel (80) is motivated by the natural pressure difference across the high-pressure turbine (20). The flow out of the injection nozzle (90) is used to energize the boundary layer flow downstream of the high-pressure turbine (20) in order to allow for the use of a more aggressively expanded inter-turbine duct (30) without boundary layer separation.

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