A gas turbine engine (300; 400; 500) comprising: a compressor portion; a combustor fluidly connected to the compressor portion via a primary flowpath; a turbine portion fluidly connected to the combustor via the primary flowpath, wherein the turbine portion includes at least a first turbine section (310; 410; 510) and a second turbine section (320; 420; 520), the second turbine section (320... 520) being at a low pressure relative to the first turbine section (310... 510); a first shaft (330; 430; 530) connected to said first turbine section (310... 510); a second shaft (340; 440; 540) radially inward of said first shaft (330... 530) and connected to said second turbine section (320... 520); wherein the first shaft (330... 530) is supported relative to the second shaft (340... 540) by a first bearing (350; 450; 550), the first bearing (350... 550) having an inner diameter and an outer diameter, with the inner diameter being connected to one of the first shaft (330... 530) and the second shaft (340... 540) and the outer diameter being connected to the other of the first shaft (340... 540) and the second shaft (340... 540); and a static support structure (370; 470; 570) disposed partially within a transitional duct (304; 404; 504) in said primary flowpath between said first turbine section (310... 510) and said second turbine section (320... 520), wherein said static support structure (370... 570) structurally supports an outer diameter of the primary flowpath relative to said second shaft (340... 540), characterised in that: the static support structure (370; 470; 570) is connected to the second shaft (340... 540) via a second bearing (380; 480; 580; 580'), and the static support structure (370... 570) includes an overhang region (376; 476; 576) positioned radially outward of the first bearing (350... 450). a compressor portion; a combustor fluidly connected to the compressor portion via a primary flowpath; a turbine portion fluidly connected to the combustor via the primary flowpath, wherein the turbine portion includes at least a first turbine section (310; 410; 510) and a second turbine section (320; 420; 520), the second turbine section (320... 520) being at a low pressure relative to the first turbine section (310... 510); a first shaft (330; 430; 530) connected to said first turbine section (310... 510); a second shaft (340; 440; 540) radially inward of said first shaft (330... 530) and connected to said second turbine section (320... 520); wherein the first shaft (330... 530) is supported relative to the second shaft (340... 540) by a first bearing (350; 450; 550), the first bearing (350... 550) having an inner diameter and an outer diameter, with the inner diameter being connected to one of the first shaft (330... 530) and the second shaft (340... 540) and the outer diameter being connected to the other of the first shaft (340... 540) and the second shaft (340... 540); and a static support structure (370; 470; 570) disposed partially within a transitional duct (304; 404; 504) in said primary flowpath between said first turbine section (310... 510) and said second turbine section (320... 520), wherein said static support structure (370... 570) structurally supports an outer diameter of the primary flowpath relative to said second shaft (340... 540), the static support structure (370; 470; 570) is connected to the second shaft (340... 540) via a second bearing (380; 480; 580; 580'), and the static support structure (370... 570) includes an overhang region (376; 476; 576) positioned radially outward of the first bearing (350... 450).