Patent ID: 6314716
Filing Date: 2001-11-13
Classification: F23R

Abstract:
A combustor for a gas turbine engine comprising:a combustor liner, said combustor liner having an inlet end portion and an exit end portion, said combustor liner defining a combustion zone therein;cooling air passage being defined by a cooling shield and said combustor liner, said cooling air passage having a plurality convection enhancing devices being disposed on said combustor liner;an air passage being fluidly connected with said cooling air passage proximate said exit end portion;a combustion air plenum being fluidly connected with said cooling air passage proximate said inlet end portion, said combustion air plenum being fluidly connected with said combustion zone;a flow diverting mechanism being positioned intermediate said cooling air passage and said combustion air plenum, said flow diverting mechanism being movable between a first and second position, said first position allowing fluid communication between said cooling air passage and said combustion air plenum, said second position preventing fluid communication between said combustion air plenum and said cooling air passage.