A system comprising: a diffuser section configured to receive an exhaust gas from a turbine section , wherein the diffuser section comprises an outer barrel , an inner barrel , a seal interface , disposed at a downstream end of the inner barrel , an aft plate , a forward plate , and a plurality of poles ; wherein an upstream end of the outer barrel comprises an upstream lip configured to interface radially with a downstream lip of an outer wall of the turbine outlet , wherein the upstream lip and the downstream lip are configured to form a circumferential lap joint disposed about a turbine axis ; wherein the outer barrel comprises a first plurality of axial segments disposed between the upstream end of the outer barrel and the forward plate , wherein the first plurality of axial segments comprises a first continuous curve away from the turbine axis from the upstream end of the outer barrel to the forward plate ; wherein the inner barrel comprises a second plurality of axial segments disposed between an upstream end of the inner barrel and the seal interface , wherein the second plurality of axial segments comprises a second continuous curve away from the turbine axis from the upstream end of the inner barrel to the seal interface ; characterized in that , the seal interface comprises a first circumferential groove configured to receive the aft plate , wherein the first circumferential groove opens in a first direction away from the turbine axis ; and wherein the plurality of poles is circumferentially spaced about the turbine axis , and each pole of the plurality of poles couples a downstream end of the aft plate to a downstream end of the forward plate . a diffuser section configured to receive an exhaust gas from a turbine section , wherein the diffuser section comprises an outer barrel , an inner barrel , a seal interface , disposed at a downstream end of the inner barrel , an aft plate , a forward plate , and a plurality of poles ; wherein an upstream end of the outer barrel comprises an upstream lip configured to interface radially with a downstream lip of an outer wall of the turbine outlet , wherein the upstream lip and the downstream lip are configured to form a circumferential lap joint disposed about a turbine axis ; wherein the outer barrel comprises a first plurality of axial segments disposed between the upstream end of the outer barrel and the forward plate , wherein the first plurality of axial segments comprises a first continuous curve away from the turbine axis from the upstream end of the outer barrel to the forward plate ; wherein the inner barrel comprises a second plurality of axial segments disposed between an upstream end of the inner barrel and the seal interface , wherein the second plurality of axial segments comprises a second continuous curve away from the turbine axis from the upstream end of the inner barrel to the seal interface ; characterized in that , the seal interface comprises a first circumferential groove configured to receive the aft plate , wherein the first circumferential groove opens in a first direction away from the turbine axis ; and wherein the plurality of poles is circumferentially spaced about the turbine axis , and each pole of the plurality of poles couples a downstream end of the aft plate to a downstream end of the forward plate . <EOS>