SOLID OXIDE FUEL CELL STACK FOR AN AIRCRAFT ENGINE

A solid oxide fuel cell stack for an aircraft engine is proposed, comprising a plurality of ring-shaped fuel cell assemblies of a plurality of tubular solid oxide fuel cells each, the fuel cells being arranged parallel to each other and distributed circumferentially around a central axis, at least one first stacking manifold for each fuel cell assembly in contact with a first side of the individual fuel cell assembly, at least one second stacking manifold for each fuel cell assembly in contact with a second side of the individual fuel cell assembly, and a central recess for leading an engine shaft through, wherein the fuel cells each comprise a tubular anode and a tubular cathode, wherein the fuel cell assemblies are stacked in an axial direction through pairs of first and second stacking manifolds contacting each other, wherein each first stacking manifold comprises a hydrogen inlet and is connected to first ends of the anodes of the respective fuel cells, and wherein each second stacking manifold comprises a hydrogen and steam outlet and is connected to second ends of the anodes of the respective fuel cells.