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A gas turbine engine (10) configured to combust gaseous hydrogen fuel, the gas turbine engine (10) comprising: a combustor (20) comprising an annular combustion chamber outer casing (36) having an annular wall (40), surrounding an inner combustor case (34) and a fuel manifold (42) configured to provide gaseous fuel to a plurality of fuel injectors (18); wherein the fuel manifold (42) is formed integrally with the combustion chamber outer casing (36); and each fuel injector (18) is coupled to the fuel manifold (42) via a coupling (50) provided within the combustion chamber outer casing (36), wherein the fuel manifold (42) is provided on a radially outer side of the combustion chamber outer casing wall (40); characterised in that: each fuel injector (18) is coupled to the fuel manifold (42) via a respective fuel feed arm (44); the fuel manifold (42) is joined to the combustion chamber outer casing wall (40) by the fuel feed arms (44), and is spaced from the combustion chamber outer casing annular wall (40) by the fuel feed arms (44), wherein each fuel feed arm (44) is integral with the fuel manifold (42).