Patent ID: 6098397
Filing Date: 2000-08-08
Classification: F05B,F23R

Abstract:
A combustor for a gas turbine engine, said combustor comprising:a combustor cooling shield;a combustor liner having an inlet portion and an outlet portion, said combustor liner being positioned within said combustor cooling shield, said combustor liner being connected with said combustor cooling shield at said outlet portion, said combustor liner having a hot side and a cold side, said cold side and said combustor cooling shield defining a cooling channel therebetween, said hot side defining a combustion zone therein, said combustion zone being adapted to receive compressed air and a fuel at said inlet portion, said combustion zone being adapted to exhaust a combustion gas into a turbine being in fluid communication with said outlet portion, said cooling channel being.adapted to receive a compressed air stream; anda plurality of concavities disposed on said cold side, said concavities being adapted to increase convective cooling of said combustor liner.