RETENTION SYSTEM FOR GAS TURBINE ENGINE ASSEMBLIES

摘要

A combustor of a gas turbine engine and a turbine shroud (22) for a turbine of a gas turbine engine are disclosed. The combustor is configured to ignite a mixture of compressed air and fuel in a combustion chamber included therein. The turbine shroud (22) is configured to direct products of the combustion reaction toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades (24) to rotate.