Abstract: A gas turbine engine is constructed having a forward differentially geared power output with an adjacent inlet for the introduction of airflow to the engine. After the airflow is compressed, it is discharged into an annular regenerator which is heated by exhaust gases. A reverse flow can-type combustor is located within the annular regenerator and receives the preheated air therefrom. The exhaust gas from the combustor is directed forward, first, to the power turbine and then to the gasifier turbine, after which it is exhausted through the regenerator.