Combustion transition duct providing stage 1 tangential...

Details Combustion transition duct providing stage 1 tangential... Combustion transition duct providing stage 1 tangential...

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/16 (2006.01) F01D 1/04 (2006.01) F02C 9/16 (2006.01)

Patent

CA 2603130

A transition duct (200) for routing a gas flow from a combustor (220) to the first rotating blade of a turbine section in a combustion turbine engine has an internal passage from an inlet (204) to an outlet (210) that is offset from the inlet (204) in the longitudinal, radial and tangential directions. The offset outlet (210) and the curved internal passage discharge the gas flow toward the first stage blade array at an angle (216) in the tangential direction relative to the longitudinal direction. This angled discharge can be presented directly to the blades, thus avoiding the need for first stage vanes and the associated costs and complexity.

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