A center body support for a gas turbine engine comprising: an outer annular wall; an aft flange extending radially outward from the outer annular wall, wherein the aft flange includes inner and outer mounting features (76, 78) spaced radially apart from one another, the inner and outer mounting feature (76, 78) configured to respectively receive first and second sets of fasteners (82, 84); a brace interconnecting a radially outer portion of the aft flange to a forward portion of the outer annular wall to provide a triangular cross-section shape, wherein the forward portion extends in a radially outward direction from the outer wall defining forward portion radially inner and outer ends; the aft flange, brace and forward portion of the outer annular wall provide a unitary, one-piece structure; and an inner annular wall radially spaced from and structurally interconnected to the outer annular wall by a circumferential array of struts, wherein the forward portion includes at the radially outer end a forward mounting feature configured to receive a third set of fasteners, and the outer and forward mounting features (78, 80) are configured to receive a fan exit guide vane mounting ring the inner and outer annular walls (66, 68), the struts and the brace are provided by a one-piece casting, characterised in that: the brace is joined to the forward portion at the radial outer end of the forward portion and the brace transfers an axial load from the aft flange to the radial outer end of the forward portion such that the configuration of the outer annular wall, aft flange, forward portion and brace transfers axial load from the aft flange to the forward portion. an outer annular wall; an aft flange extending radially outward from the outer annular wall, wherein the aft flange includes inner and outer mounting features (76, 78) spaced radially apart from one another, the inner and outer mounting feature (76, 78) configured to respectively receive first and second sets of fasteners (82, 84); a brace interconnecting a radially outer portion of the aft flange to a forward portion of the outer annular wall to provide a triangular cross-section shape, wherein the forward portion extends in a radially outward direction from the outer wall defining forward portion radially inner and outer ends; the aft flange, brace and forward portion of the outer annular wall provide a unitary, one-piece structure; and an inner annular wall radially spaced from and structurally interconnected to the outer annular wall by a circumferential array of struts, wherein the forward portion includes at the radially outer end a forward mounting feature configured to receive a third set of fasteners, and the outer and forward mounting features (78, 80) are configured to receive a fan exit guide vane mounting ring the inner and outer annular walls (66, 68), the struts and the brace are provided by a one-piece casting, characterised in that: the brace is joined to the forward portion at the radial outer end of the forward portion and the brace transfers an axial load from the aft flange to the radial outer end of the forward portion such that the configuration of the outer annular wall, aft flange, forward portion and brace transfers axial load from the aft flange to the forward portion.