Turbine section architecture for gas turbine engine

Details Turbine section architecture for gas turbine engine Turbine section architecture for gas turbine engine

F - Mech Eng,Light,Heat,Weapons

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F01D 25/30 (2006.01) F01D 5/06 (2006.01) F01D 21/14 (2006.01) F01D 25/24 (2006.01) F02K 1/00 (2006.01) F02K 1/78 (2006.01)

Patent

CA 2713316

A turbine section of a gas turbine engine is described, which includes an aftmost rotor extending, an aftmost stator located upstream of the aftmost rotor, and a second to last aftmost rotor located upstream of the aftmost stator. The second to last aftmost rotor being spaced apart a first axial distance from the aftmost stator. A turbine exhaust case is located downstream of the aftmost rotor and includes an inner radial wall and an outer radial wall defining a main gas path duct downstream of the aftmost rotor. The turbine exhaust case being axially spaced apart from the aftmost rotor a second axial distance that is greater than the first axial distance.

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