Gas turbine and combustor therefor

Details Gas turbine and combustor therefor Gas turbine and combustor therefor

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/42 (2006.01) F23M 5/08 (2006.01) F23R 3/00 (2006.01)

Patent

CA 2409122

A combustor section (14) is disposed downstream of a nozzle section (11). The combustor section (14) extends from a downstream end of the nozzle section (11) to an entrance of a gas turbine and supplies a combustion gas which is generated by combusting a premixed gas to a gas turbine. The combustor section (14) is formed by an inner tube and a tail tube unitarily. The combustor (10) is provided with a wall cooling apparatus for cooling a wall surface of the combustor (10). On the inner wall of the combustor section (14), grooves are formed. An entrance for introducing an air for cooling action is disposed on the outer wall of the combustor section (14). The introduced air performs a film cooling and connective cooling in a combined manner. By doing this, the temperature of the combustion gas may be high, and a highly efficient gas turbine is realized.

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