A turbomachine, comprising: a plurality of transition ducts disposed in an annular array, each of the plurality of transition ducts comprising an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis, each of the plurality of transition ducts further comprising an upstream portion having an aft end and a downstream portion having a head end,, the upstream portion extending between the inlet and the aft end, the downstream portion extending between the head end and the outlet, wherein the upstream portion and the downstream portion are coupled together by a joint configured to provide articulation for allowing movement of each of the transition ducts during operation; the turbomachine further comprising a support ring assembly (180, 182) downstream of the plurality of transition ducts along a hot gas path; and a plurality of support assemblies directly connecting the upstream portion of at least one transition duct of the plurality of transition ducts to the support ring assembly, each of the plurality of support assemblies comprising a rod extending between the upstream portion and the support ring assembly, the turbomachine being characterised in that each of the plurality of support assemblies further comprises at least one ball joint for facilitating movement of the associated upstream portion relative to the support ring assembly (180, 182). a plurality of transition ducts disposed in an annular array, each of the plurality of transition ducts comprising an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis, each of the plurality of transition ducts further comprising an upstream portion having an aft end and a downstream portion having a head end,, the upstream portion extending between the inlet and the aft end, the downstream portion extending between the head end and the outlet, wherein the upstream portion and the downstream portion are coupled together by a joint configured to provide articulation for allowing movement of each of the transition ducts during operation; the turbomachine further comprising a support ring assembly (180, 182) downstream of the plurality of transition ducts along a hot gas path; and a plurality of support assemblies directly connecting the upstream portion of at least one transition duct of the plurality of transition ducts to the support ring assembly, each of the plurality of support assemblies comprising a rod extending between the upstream portion and the support ring assembly, the turbomachine being characterised in that each of the plurality of support assemblies further comprises at least one ball joint for facilitating movement of the associated upstream portion relative to the support ring assembly (180, 182).