A rotor assembly for a gas turbine engine having an axial engine centerline, comprising: a first rotor airfoil that extends along a first radial axis relative to the engine centerline; a first rotor disk having an outer rim, a bore and a web extending between said outer rim and said bore, wherein the outer rim, the bore and the web extend along a second radial axis relative to the engine centerline and said second radial axis is axially offset from said first radial axis by an axial distance along the engine centerline; and characterised in that said first rotor airfoil extends from a bladed ring (44; 144) and by further comprising: a second rotor disk having an outer rim, a bore and a web extending between said outer rim and said bore, wherein said second rotor disk is substantially in-line with a third radial axis relative to the engine centerline of a second rotor airfoil; a third rotor disk, wherein said bladed ring (44; 144) is radially trapped between said first rotor disk and said third rotor disk, wherein an axially outermost portion of the web of the first and third rotor disk is fully axially offset from an axially outermost portion of said first rotor airfoil in a direction away from said first rotor airfoil, such that no portion of the web is positioned directly radially inwardly from the first rotor airfoil; and a spacer that extends between said first rotor disk and said third rotor disk, wherein said spacer is positioned radially inwardly from said bladed ring to provide radial load support to the first rotor airfoil. a first rotor airfoil that extends along a first radial axis relative to the engine centerline; a first rotor disk having an outer rim, a bore and a web extending between said outer rim and said bore, wherein the outer rim, the bore and the web extend along a second radial axis relative to the engine centerline and said second radial axis is axially offset from said first radial axis by an axial distance along the engine centerline; and characterised in that said first rotor airfoil extends from a bladed ring (44; 144) and by further comprising: a second rotor disk having an outer rim, a bore and a web extending between said outer rim and said bore, wherein said second rotor disk is substantially in-line with a third radial axis relative to the engine centerline of a second rotor airfoil; a third rotor disk, wherein said bladed ring (44; 144) is radially trapped between said first rotor disk and said third rotor disk, wherein an axially outermost portion of the web of the first and third rotor disk is fully axially offset from an axially outermost portion of said first rotor airfoil in a direction away from said first rotor airfoil, such that no portion of the web is positioned directly radially inwardly from the first rotor airfoil; and a spacer that extends between said first rotor disk and said third rotor disk, wherein said spacer is positioned radially inwardly from said bladed ring to provide radial load support to the first rotor airfoil. a second rotor disk having an outer rim, a bore and a web extending between said outer rim and said bore, wherein said second rotor disk is substantially in-line with a third radial axis relative to the engine centerline of a second rotor airfoil; a third rotor disk, wherein said bladed ring (44; 144) is radially trapped between said first rotor disk and said third rotor disk, wherein an axially outermost portion of the web of the first and third rotor disk is fully axially offset from an axially outermost portion of said first rotor airfoil in a direction away from said first rotor airfoil, such that no portion of the web is positioned directly radially inwardly from the first rotor airfoil; and a spacer that extends between said first rotor disk and said third rotor disk, wherein said spacer is positioned radially inwardly from said bladed ring to provide radial load support to the first rotor airfoil.