Gas turbine combustor

摘要

A gas turbine combustor in which an inequality of distribution of temperature at the outlet of the combustor which is caused by cooling air introduced to the combustor to cool it is prevented. A liner 2 having an outer liner 2' and an inner liner 2'' is disposed within a casing 3 composing the gas turbine combustor 1. The liner 2 is composed of a liner inner cylinder 15 in which liner cooling paths 16 are created and a liner outer cylinder 14. Fuel supplied via upstream side manifolds 9 and 10 flows through the liner cooling paths 16 and is discharged from a downstream side manifold 11 after cooling the liner 2. The fuel is boosted by a pump and is supplied to a fuel-air pre- mixer 13 from a fuel supply port 12 to be burned in the combustion chamber.