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TRANSITION DUCT SYSTEM WITH A ROBUST CONVERGING FLOW JOINT AT AN INTERSECTION BETWEEN ADJACENT TRANSITIONS EXTENDING BETWEEN A COMBUSTOR AND A TURBINE ASSEMBLY IN A GAS TURBINE ENGINE

United States Patent Application

20170145839
A1
View the Complete Application at the US Patent & Trademark Office
A transition duct system (110) for routing a combustion exhaust gas flow from a combustor (112) to the first stage (114) of a turbine section (116) in a combustion turbine engine (118) is disclosed, whereby the system (110) imparts a circumferential vector to the combustion exhaust gases expelled from the system (110), thereby negating the need for a conventional row one vane assembly. The transition duct system (110) may include a robust converging flow joint between adjacent transition ducts (122, 124) within the system (110) such that adjacent transition sections (116) may be adjoined to each other via an intersection (126) forming a linear edge (128) which provides for a strong robust intersection (126) between the adjacent transition sections (116). In at least one embodiment, the linear edge (128) at the intersection (126) may be within 10 degrees of being orthogonal to an inner edge (130) of the transition sections (116) at the intersection (126).
Hardes, Jacob William (Charlotte, NC)
15/ 309,472
June 17, 2014
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT [0001] Development of this invention was supported in part by the United States Department of Energy, Advanced Turbine Development Program, Contract No. DE-FC26-05NT42644. Accordingly, the United States Government may have certain rights in this invention.