Patent ID: 6397603
Filing Date: 2002-06-04
Classification: F05B,F23D,F23R

Abstract:
A combustor for use in a gas turbine engine, comprised of:a forward cowl made from a metallic material capable of withstanding elevated temperatures of combustion in an oxidative and corrosive atmosphere having a first coefficient of thermal expansion; an aft seal attached to a seal retainer, the aft seal having a second coefficient of thermal expansion and the seal retainer having a third coefficient of thermal expansion, each made from a metallic material capable of withstanding elevated temperatures of combustion in an oxidative and corrosive atmosphere; and a combustion liner made from a ceramic matrix composite material capable of withstanding elevated temperatures of combustion in an oxidative and corrosive atmosphere having a fourth coefficient of thermal expansion less than the first coefficient of thermal of the forward cowl and less than the second coefficient of thermal expansion of the aft seal and less than the third coefficient of thermal expansion of the seal retainer, the combustor liner positioned between the forward cowl and aft seal with attached seal retainer in a manner to permit differential thermal expansion of the ceramic combustor liner, the forward cowl and the aft seal with attached seal retainer without introducing stresses into the liner sufficient to fracture the liner as a result of differential thermal expansion at elevated temperatures.