Abstract: A solid oxide fuel cell stack for an aircraft engine includes ring-shaped fuel cell assemblies of parallel tubular oxide fuel cells circumferentially around a central axis. A first stacking manifold for each fuel cell assembly is in contact with a first side of the individual fuel cell assembly, a second stacking manifold is in contact with a second side of the individual fuel cell assembly, and a central recess for leading an engine shaft through. Each fuel cell includes a tubular anode and tubular cathode, the fuel cell assemblies stacked in an axial direction through pairs of first and second stacking manifolds contacting each other. Each first stacking manifold includes a hydrogen inlet and is connected to first ends of the anodes of the fuel cells. Each second stacking manifold includes a hydrogen and steam outlet and is connected to second ends of the anodes of the fuel cells.