Efficiently cooled transition duct for a large plant...

F - Mech Eng,Light,Heat,Weapons – 02 – C

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F02C 7/141 (2006.01) F01D 9/02 (2006.01) F23R 3/00 (2006.01)

Patent

CA 1183695

12 ABSTRACT OF THE DISCLOSURE A transition duct for a large plant combustion turbine comprises an elongated outer tubular wall member arranged to be coupled with a combustion chamber at its upstream end and to be supported at its downstream end to direct the hot driving gases through the annular turbine blade space. The tubular wall has at least a portion thereof structured for internal wall cooling including an outer tubular shell member and a skin member having a continuous inner tubular surface and disposed peripherally about and against an inward facing tubular surface of the shell member. Coolant channels are arranged peripherally about and in the skin member to face the shell member and to direct coolant generally longitudinally of the duct portion. The shell member has entry means for directing compressor discharge coolant air from the duct exterior to and through the skin coolant channels. The coolant is discharged from the channels to the duct gas flow from at least one location longitudinally spaced from the entry means. The entry means comprises at least one substan- tially transverse coolant channel disposed about said tubular shell member to face inwardly toward the tubular skin member. A plurality of openings extend from the shell coolant channel through the shell wall to the duct exterior are disposed about the shell member. The channels extend longitudinally between the upstream and downstream ends of said internally cooled 13 turbine wall portion, and the discharge means includes openings from the skin channels through the downstream end of the skin member.

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